20080325002572008032500257CE  2008       3          25         0000H2484        120080318G2820                LINE                                    BEECH 35    V35         1151538CE  CONT  O550  IO550B           SO                              FUEL SYSTEM     CHAFED          B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07363BC     3                 D9763       297203R                     FUEL LINE MOUNTED ON FIREWALL FABRICATED PER STC SA8676SW WAS CHAFING THE ENGINE TAILPIPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  3A15    E3SO                 
20080403000902008040300090CE  2008       4          3          01030413         120080103G3242314901          BRAKE ASSY      BFGOODRICH              CESSNA500   560CESSNA   2076750CE                                                               MLG             LOCKED          B  PAZRO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      CE03561JS           2290        5600413                                 UPON LANDING THE AIRCRAFT YAWED TO THE RIGHT AND IN OVERCOMPENSATING THE AIRCRAFT THEN STARTED A SIDEWAYS DRIFT ENOUGH THAT THE LEFT MAIN TIRE FAILED. IT WAS FOUND THAT ONE RIGHT HAND BRAKE STATOR WAS LOCKED AND HAD GROUND THE WHEEL FLAT AND THE LEFT MAIN FAILED AS A RESULT OF TIRE SIDEWALL FAILURE. DAMAGE INCLUDES BOTH TIRES AND WHEELS. LEFT LANDING LIGHT. LEFT HAND INBOARD FLAP AND RIGHT HAND BRAKE AND BRAKE LINES.                                                                                                                                                                                                                                                                                                            2L72 4F    RTA22CE                        
20080410002602008041000260EU  2008       4          10         03252008         120080325G3233D52177          HOLDER          MESSIER                 AMD   FALC20FALCON200   2730150EU                                                               ACTUATOR        BROKEN          B      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  LDLANDING        1                      SW05                DRI76878                                            THE PACKING HOLDER P/N D52177 BROKE IN (2) PIECES CAUSING HYDRAULIC FLUID LOSS.  THIS PART HAD BEEN MODIFIED IAW SB F200-110 TO PREVENT FUTURE FAILURES.  THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WERE MODIFIED AND IDENTIFIED SRD IAW THE S/B.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA7EU                         
20080313000422008031300042SO  2008       3          13         115301           120080218G49101159AC30551103  DUCT                                    GULSTMG1159 GIV         3980115SO                                                               APU INLET       CRACKED         E  CLWAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05589HM6464                   1153                                    A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA12EA                        
20080313000442008031300044SO  2008       3          13         115302           120080218G49101159AC30551103  DUCT                                    GULSTMG1159 GIV         3980115SO                                                               APU INLET       CRACKED         E  CLWAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05589HM6464                   1153                                    A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA12EA                        
20080219000672008021900067CE  2008       2          19         20080101         120080118G2752505212234       ACTUATOR                                BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              T/E FLAP        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                            LJ833                                   RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE.  CRACK RUNS PARALLEL TO TUBE .                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3T4  T  3A20    E4EA                 
20080508001162008050800116SO  2008       5          8          20080420001      120080420G7810                BRACKET                                 MAULE MX7   MX7180A     5460186SO  LYC   O360  O360*       41514EA                              ENGINE EXHAUST  CRACKED         C      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      SO16                                                                    ON TAKE-OFF, 50 FEET, PARTIAL POWER LOSS (2,500+ RPM TO 1,100 RPM) AND ENGINE ROUGHNESS.  ABORTED TAKE-OFF.  WHEN CARBURATOR TAKEN OFF PLANE, FOUND 1 INCH X .5 INCH PIECE OF METAL LOOSE IN AIR/FUEL MIXING CHAMBER UPSTREAM OF VENTURI. PIECE WAS TOO BIG TO GO THROUGH VENTURI, BUT BIG ENOUGH TO DISRUPT FLOW THROUGH VENTURI.  FOUND SOURCE OF METAL TO BE A PIECE OF THE BRACKET FROM LEFT MUFFLER. BRACKET USED TO CONNECT SHROUD TO MUFFLER TO CAPTURE HEAT FOR USE IN DIRECTING CARB HEAT. ENTIRE BRACKET WAS ABOUT 12 INCHES LONG. THE 1 INCH LONG PIECE OF THE BRACKET BROKE OFF AND MADE ITS WAY DOWN CARB HEAT DUCTING INTO MIXING CHAMBER OF MUFFLER, UPSTREAM OF VENTURI.  BASED ON ENGINE OPERATIONS, BELIEVE PIECE HAD BROKEN F1H71 3O3  ONC3A23    E286                 
             20080519     CE  2008       5          19         20080506FA001    120080506G324610320400AN53    BOLT            PARKERHANFIN            RAYTHN36    G36         7150061CE                                                               RT MLG WHEEL    SHEARED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07222GL479  479               E3763                                   THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG).  FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT HAND MAIN LANDING GEAR ASSEMBLY.  THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4INCH.  THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED.  UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS WERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS.  DURING DISASSEMBLY OF THE WHEEL HALF RETAINING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE. THE NOSE WHEEL WAS THEN CHECKE1L71 3O    RT3A15                         
             20080701     EA  2008       7          1          2008F00016       220080415G8500                ENGINE                                  GIPPLDGA8   GA8         3900102EU  LYC   O540  IO540K1A5   41532EA                                              FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      SO237508M                       GA805094    L3095348A                   AIRCRAFT EXPERIENCED AN ENGINE FAILURE. ATTEMPTS TO RESTART ENGINE FAILED AND A SAFE LANDING WAS ACCOMPLISHED. CAUSE OF FAILURE REMAINS UNKNOWN AT THIS TIME. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT        1E4                  
             20080811     CE  2008       8          11         2008F00019       120080715G3260A46270          SWITCH                                  CESSNA500   550         2076604CE                                                               MLG             OUT OF ADJUST   D      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      EA68187JN                       5500335                                 ON DEPARTING AIRPORT, UPON GEAR RETRACTION, THE DOOR UNLOCK LIGHT ACTIVATED.  THE PILOT OPTED TO BURN FUEL AND LAND WHEN LANDING WEIGHT WAS ACHIEVED.  THE LANDING WAS WITHOUT INCIDENT.  MAINT WAS THEN CALLED.  THE SWITCH WAS DETERMINED TO BE OUT OF ADJUSTMENT.  THE SWITCH WAS THEN ADJUSTED IAW MM AND RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4F      A22CE                        
             20080811     GL  2008       8          11         2008F00020       120080711G6100                ROD                                     CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO                              PITCH CHANGE    MISINSTALLED    W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      SW99554PG                       2009        360674                      ON INSTALLATION OF PROP TO ENG MOUNTING FLANGE IAW MM 61-00-45, THE PLASTIC PROTECTIVE CAP FITTED TO THE END OF THE PITCH CHANGE ROD WAS NOT REMOVED.  ON FLIGHT TEST OF THE AC, ENGINE OVERSPEED WAS NOTED AT TAKEOFF TO 2850 RPM, NO SIGNIFICANT LOSS OF OIL PRESSURE WAS NOTED.  THE PILOT THROTTLED BACK TO REDUCE PROPELLER SPEED TO LESS THAN 2700 RPM ( WITHIN PERMITTED LIMITATIONS) ENGINE POWER WAS REDUCED TO 48 PERCENT AT THIS POINT AND THE ENGINE SUBSEQUENTLY STOPPED.  THE PILOT RESTARTED THE ENGINE, SLIGHTLY EXCEEDING 2700 RPM FOR A SHORT PERIOD.  THE PILOT RETURNED THE AIRCRAFT TO BASE, LANDING SAFELY AND REPORTED THE INCIDENT TO THE MAINT MGR.  ON INVESTIGATION THE PROP WAS REMOVED AND THE PROTECTIVE CAP WAS I1L71 3O3  ONTA00009CHE1CE                 
             20081110     EA  2008       11         10         2008F00024       220081001G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07227BH                       172S10662   L33887L2A                   EXCESSIVE MAGNETO DROP DURING RUNUP AND MAGNETO CHECK. 100 RPM DIFFERENTIAL BETWEEN LT AND RT MAGNETO, ALSO RT MAGNETO RUNNING ROUGH. CHECKED FOUND RT MAGNETO TIMING OFF. FOUND RT MAGNETO AT 20 DEGREES BEFORE TOP DEAD CENTER, SUPPOSE TO BE 25 DEGREES BTDC.  DRIVE GEAR FOR THE DISTRIBUTOR WAS FOUND UNEVEN, CAUSING IT TO WOBBLE WHEN ROTATING. THIS CAUSED UNUSUAL WEAR ON BOTH DRIVE GEAR AND DISTRIBUTOR GEAR. DRIVE GEAR MATERIAL NOT REMOVED DURING CLEANUP PROCESS FROM INJECTION MOLDING. PIECES WERE COMING OFF INSIDE MAGNETO. EXCESSIVE CAM WEAR FOR 379.9 HRS. CONTACT POINTS FOUND MISALIGNED,  BREAKER POINT ARM HAS FALLEN DOWN & IS RIDING ON THE RIDGE ON CAM. RIDGE CREATED BY EXCESSIVE CAM WEAR. CONDITION MAY CAUSE R1H71 3O3  ONT3A12    1E10                 
             20081210     NE  2008       12         10         2008F00025       120081113G2612                PROBE                                   SKRSKYS76   S76C        8143008NE                                                               FIRE WARNING    MALFUNCTIONED   G      K   NONE                                                                                            N  FALSE WARNING                                                                 CRCRUISE         1                      EA6385PS                        760489                                  NUMBER 2 ENGINE HAD A FIRE CAUTION WARNING LIGHT ILLUMINATE WITH HORN FOR TWO SECONDS. THIS OCCURRED TWICE DURING THE FLIGHT.  WHEN THE MECHANICS TRIED TO TROUBLESHOOT THE PROBLEM, COULD NOT DUPLICATE IT.  TO FURTHER TROUBLESHOOT, THE AFT NR 1 & 2 FIRE PROBES P/N 76306-07902-104 WERE SWAPPED TO SEE IF THE PROBLEM RE-OCCURRED AND FOLLOWED THE PROBE.                                                                                                                                                                                                                                                                                                                                                                                  1G72 3U    NCH1NE                         
             20090105     EU  2009       1          5          2008F00026       120081216G5311117223121151    FRAME                                   BOLKMS117   BK117B1     5626012EU                                                               ZONE 200        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19330SL                       7216                                    DURING INSP FOUND SPIDER CRACKS AROUND 1 RIVET ON THE DECK UNDER THE TANDEM HYD PACK. FURTHER INSP FOUND 2 FRAMES CRACKED UNDER THE HYD DECK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U      H13EU                        
             20090106     EU  2009       1          6          2008F00027       120081215G7797MS3126F1415S    CONNECTOR                               BRAERODH125 HS125700A   4230170EU                                                               N1 INDICATOR    DEFECTIVE       H      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19411P 117441070  549E                                                ON NOVEMBER 23, 2008, THE NR 2 ENGINE N1 GAUGE DIGITAL PORTION FAILED. THE MALFUNCTION WAS TRACED TO A DEFECTIVE CONNECTOR AT THE GAUGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F      A3EU                         
20080111002612008011100261SO  2008       1          11         2008FA0000003    120080102G321339489003        STRUT                                   PIPER PA34  PA34220T    7103420SO  CONT  O360  TSIO360RB   17025CE  MCAULY3AF32C3AF32C512   GL  RT MLG          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0169BP 2091 2091              3449085     321475      981180          DURING ANNUAL INSPECTION IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSY PN 39489-003.  THE CRACK IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS USED TO BOLT THE TORQUE PLATE PN 451-786 TO THE MLG ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOLD THEY NEVER HEARD OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONTACT A DER FOR APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. ALSO I NOTED THAT THE CASTING VARY IN THICKNESS UPTO 1L72 3O3  O  A7SO    E9CE    5  CP22EA    
20080110000122008011000012SO  2008       1          10         2008FA0000004    120080102G321339489003        STRUT                                   PIPER PA34  PA34220T    7103420SO  CONT  O360  TSIO360RB   17025CE  MCAULY3AF32C3AF32C512   GL  RT MAIN GEAR    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0169BP 2091 2091              3449085     321475      981180          DURING ANNUAL INSPECTION, IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSEMBLY PN 39489-003.  THE CRACK IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS USED TO BOLT THE TORQUE PLATE PN 451-786 TO THE MAIN LANDING GEAR ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOLD THEY NEVER HEARD OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONTACT A DER FOR APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. THIS STRUT CAME OFF A MODEL PA34-21L72 3O3  O  A7SO    E9CE    5  CP22EA    
20080114000752008011400075CE  2008       1          14         2008FA0000010    120080104G3213390810001       STRUT                                   RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              LT MLG          LEAKING         B      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CE09701KB30                     RB211                                   PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS AND METAL FILLINGS IN INNER BARREL OF STRUT.                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3F4  FRTA00010WIE3GL                 
20080114000742008011400074CE  2008       1          14         2008FA0000011    120080104G3213390810001       STRUT                                   RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              RT MLG          LEAKING         B      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CE09701KB30                     RB211                                   PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS AND METAL FILLINGS IN INNER BARREL OF STRUT.                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3F4  FRTA00010WIE3GL                 
20080111002972008011100297EA  2008       1          11         2008FA0000013    220080102G74146393            MAGNETO                                 GULSTM500   500S        0141107SW  LYC   O540  IO540E1B5   41532EA  HARTZLHCC3Y HCC3YR      GL  ENGINE          WORN            C      D   RETURN TO BLOCK                                                                                 L  NO TEST                                                                       TXTAXI/GRND HDL  1                      SO1451RF 50   50                                                        CAM LOBE INSIDE MAG THAT OPENS AND CLOSES POINTS WORN OUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3O3  O  6A1     1E4     5  CP25EA    
20080114000302008011400030CE  2008       1          14         2008FA0000018    120080108G2701                YOKE                                    CESSNA177   177B        2073708CE  LYC   O360  O360*       41514EA                                              MISINSTALLED    D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL0930673                       17701397                                WHILE DOING AN ANNUAL, FOUND LOOSENESS IN THE YOKE FOR AND AFT MOVEMENT.  AFTER MUCH CHECKING, FOUND THE LOOSENESS TO BE BETWEEN THE YOKE LEVER ASSY 1767033-7 AND 1767037-2 WHICH IS THE SHAFT. ALSO THERE WAS LOOSENESS BETWEEN THE SHAFT 1767037-2 AND THE QUADRANT 1767024-1.  FURTHER INVESTIGATION FOUND STANDARD AN4 BOLTS INSTEAD OF THE NAS464P4-17 CALLED FOR IN THE PARTS MANUAL CONNECTING THESE PARTS.  THE DIFFERENCE IN DIAMETER OF THE BOLTS CAUSED THE LOOSENESS. PARTS MANUAL, FIGURE 63.                                                                                                                                                                                                                                     1H71 3O3  O  A13CE   E286                 
20080122000462008012200046EU  2008       1          22         2008FA0000036    120080114G3210DIN47108VERZ    RETAINING CLIP                          DIAMONDA42  DA42        2990004EU                                                               DOWNLOCK PIN    MISSING         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15966WW13   13                42AC106                                 DURING PREFLIGHT THE PILOT NOTICED THAT THE MLG DOWNLOCK PIN (PN-D60-3237-11-34) HAD NO RETAINING CLIPS(PN-DIN471-08-VERZ). THE GROOVES IN THE PIN ARE VERY SHALLOW AND ALLOW THE CLIPS TO MIGRATE OFF.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3I    RTA57CE                        
20080122001942008012200194SO  2008       1          22         2008FA0000041    120080109G7120                MOUNT                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              LT ENGINE       CRACKED         B  B2ERK   NONE                                                                                            E  VIBRATION/BUFFET                                                              ININSP/MAINT     1                      EA2325EL                        28R7837087                              ENGINE MOUNT FOUND CRACKED AT BOTTOM LT WHERE SHOCK MOUNT ATTACHES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  2A13    1E10                 
20080212002362008021200236EA  2008       2          12         2008FA0000043    220080111G8520600050507       PUSHROD                                 PIPER PA60  PA60602P    7106015NM  LYC   O540  IO540*      41532EA                              ENGINE          CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25700LG                       608265043                               THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRECTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS.  AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTATIVE APPLIED.  OLDER TUBES WERE ALODINED ALUMINUM.  NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO CORROSION.  INSPECTION OF THIS  AREA IS ACCESSIBLE THROUGH THE WING FLAP ACTUATOR ACCESS PANEL.  SB 600-122 ADDRESSES THIS SUBJECT.  (K)                                                                                                                                                                                                                                    1M72 3O3  ORTA17WE   1E4                  
20080212002372008021200237EA  2008       2          12         2008FA0000044    220080111G8520600050507       PUSHROD                                 PIPER PA60  PA60601P    7106012NM  LYC   O540  IO540*      41532EA                              ENGINE          CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL2525RH 2446                   61P066979633                            THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRECTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS.  THIS AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTATIVE APPLIED.  OLDER TUBES WERE ALODINED ALUMINUM.  NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO CORROSION.  SB 600-122 ADDRESS THIS SUBJECT.  INSPECTION IS DONE THROUGH FLAP ACTUATOR ACCESS PANEL.  (K)                                                                                                                                                                                                                                                              1M72 3O3  ORTA17WE   1E4                  
20080212002392008021200239SO  2008       2          12         2008FA0000046    120080104G3297153615          WIRE                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              MLG             FAILED          D  SNSRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13878BT446                    3257402                                 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    E14EA                
20080212002402008021200240SO  2008       2          12         2008FA0000047    120080109G3297153615          WIRE                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              MLG             FAILED          D  SNSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL135354V528                    3257298                                 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILICONE TYPE WIRE COATING TENDS TO HOLE WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    E14EA                
20080131002882008013100288SO  2008       1          31         2008FA0000048    120080104G3297153615          WIRE                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              DOWNLOCK SWITCH FAILED          D  SNSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL135354V                       3257298                                 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    E14EA                
20080212002412008021200241SO  2008       2          12         2008FA0000049    120080111G3297153615          WIRE                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              MLG             FAILED          D  SNSRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13999TC                       3257356                                 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    E14EA                
20080212002422008021200242SO  2008       2          12         2008FA0000050    120080104G3297153615          WIRE                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              MLG             FAILED          D  SNSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13999TC249                    3257356                                 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETER WIRE AND ROUTING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  A3SO    E14EA                
20080212002452008021200245CE  2008       2          12         2008FA0000051    120080107G2752991434446       FLEX DRIVE                              CESSNA750   750         2076810CE  ALLSN AE3007AE3007C          GL                              T/E FLAP        WORN            B  CNQRA   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CE07953QS                       7500153                                 AIRCRAFT EXPERIENCED A FLAP FAIL MESSAGE AFTER TAKEOFF, DIVERTED FOR REPAIR AND THE PILOT ELECTED TO DECLARE AN EMERGENCY BEFORE LANDING.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  AFTER TROUBLESHOOTING, THE FLAP SYSTEM THE RT AND LT NR 5 FLAP FLEX DRIVES WERE FOUND TO BE WORN CAUSING A FLAP FAULT.  DRIVES HAVE BEEN REPLACED AND SYSTEM MECHANICAL AND ELECTRICAL OPERATIONAL CHECK ACCOMPLISHED.  NO FURTHER DEFECTS WERE FOUND.  (K)                                                                                                                                                                                                                                                                                                   2L72 4J4  FRTT00007WITE6CH                
20080131002962008013100296CE  2008       1          31         2008FA0000052    120080116G3060                BOOT                                    BEECH 60    A60         1153604CE  LYC   O541  TIO541*     41536EA                              PROPELLER       SEPARATED       B  PZ4RK   NONE                                                                                            D  INFLIGHT SEPARATION                                                           ININSP/MAINT     1                      GL114445W                       P245                                    A PROPELLER CAME IN FOR REPAIRS WHICH NECESSITATED THE INSTALLATION OF NEW DEICE BOOTS ON ALL 3 BLADES.  THE PROP WAS LATER INSTALLED BY THE OWNERS MECHANIC.  1 OF THE 3 BOOTS CAME OFF RESULTING IN A DENT ON THE AIRCRAFT FUSELAGE, REPORTED AFTER ABOUT 7 HOURS OF FLYING.  QUESTIONING OF OUR TECH THAT INSTALLED THE BOOTS REVEALED NO DEVIATIONS IN PROCEDURES OCCURRED DURING THE INSTALLATION. IT WAS DETERMINED THAT THE GLUE USED FOR THE INSTALLATION WAS RECEIVED BY OUR FACILITY ON 8/23/07 WITH AN EXPIRATION  DATE OF 9/30/08.  MM 202A LISTS THE SHELF LIFE OF 1300L ADHESIVE AS 15 MONTHS.  AS A PRECAUTION, THE ADHESIVE WAS REMOVED FROM USE EVEN THOUGH NO DISCREPANT CONDITION COULD BE FOUND.  FACILITY VISITED LOCATION1L72 3O3  O  A12CE   E10EA                
20080131002922008013100292CE  2008       1          31         2008FA0000053    120080117G21341303687         PRESSURE SENSOR                         LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              AFT BAGGAGE     MALFUNCTIONED   E      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CLCLIMB          1                      SO1155FN 11587                  202                                     LOSS OF CABIN PRESSURE AT 25K FT. PRESSURE SENSOR MALFUNCTIONED                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  F  A10CE   E6WE                 
20080131002942008013100294CE  2008       1          31         2008FA0000056    120080123G5514                ATTACH BOLT                             CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15*       52060NE                              HORIZONTAL STAB UNDERTORQUED    B  HSRRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM05570EJ                       5600164                                 DURING A ROUTINE PHASE INSPECTION WE FOUND 50 PERCENT OF THE HORIZONTAL STABILIZER AFT ATTACH BOLTS TO BE UNDERTORQUED, AND CAUSING SOME MOVEMENT AND A POPPING NOISE WHEN THE STABILIZER WAS PUSHED UP AND DOWN AT THE OB TIP.  WE RE-TORQUED ALL BOLTS AND THE NOISE AND MOVEMENT WENT AWAY. SOME OF THE BOLTS REQUIRED 180 DEGREE ROTATION TO OBTAIN PROPER TORQUE.  PERFORMED HIDDEN DAMAGE INSPECTION, NO DEFECTS WERE NOTED.                                                                                                                                                                                                                                                                                                              2L72 4F4  TRTA22CE   E1NE                 
20080129000042008012900004SO  2008       1          29         2008FA0000057    120080118G7603455322          THROTTLE CABLE                          PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                                              INFLT SEPARATIONB      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      SO15701ER4192 82                2844053                                 DURING FLIGHT, THE CREW EXPERIENCED A SEPARATION OF THE THROTTLE CABLE. THE POWER SETTING ALLOWED THEM TO MAINTAIN ALTITUDE PLUS A SLIGHT CLIMB. THE CREW POSITIONED THE AIRCRAFT FOR A LANDING ON A RUNWAY THAT HAD AMPLE LENGTH. AN UNEVENTFUL LANDING WAS MADE. THE THROTTLE CABLE WAS REMOVED AND INSPECTED AND FOUND TO BE BROKEN A FEW INCHES INSIDE THE OUTER HOUSING JUST AFT OF THE FUEL SERVO. THERE IS NO TIME/LIFE LIMIT ON THESE CABLES, HOWEVER THE OPERATOR WILL NOW CHANGE THE CABLES DURING EACH ENGINE CHANGE.                                                                                                                                                                                                                1L71 3O3  O  2A13    1E10                 
20080131002952008013100295NE  2008       1          31         2008FA0000058    220080123G72000319008000      ENGINE                                  UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIUS2F    60010NE                                              MAKING METAL    B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SW01146CB173  169               1407        34481                       ON 10, OCT. 2007 THE PILOT REPORTED THE ENGINE CHIP WARNING LAMP ILLUMINATED.  THE AIRCRAFT WAS LANDED WITHOUT INCIDENT.  THIS WAS THE FOURTH OCCURRENCE IN 10.9 HOURS.  THE ENGINE WAS REMOVED AND RETURNED TO MFG FOR EVALUATION AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G72 3U3  UNCR0001RD E34NE                
20080131003032008013100303EA  2008       1          31         2008FA0000062    220080102G73142B664           PUMP                                    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540*     41532EA                              FUEL SYSTEM     INOPERATIVE     D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      SO05202TC     2098              318152037                               ON 1/2/2008 THE PILOT WAS DEPARTING WHEN HE REPORTED THAT HE LOST SUBSTANTIAL POWER TO THE LT ENGINE JUST AFTER TAKEOFF AND THE LT LOW PRESSURE FUEL BOOST PUMP LIGHT ON THE AC ANNUNCIATOR PANEL ILLUMINATED.  PILOT LANDED AT AIRPORT AND CALLED AC TECH.  AIRCRAFT TECH ON LOCATION COULD NOT FIND ANY PROBLEMS WITH THE ENGINE DURING RUN UP OTHER THAN THE ELECTRIC LOW PRESSURE FUEL BOOST PUMP NOT SUPPLYING RATED PRESSURE.  THE ELECTRIC IN-LINE LOW PRESSURE BOOST PUMP IS INTENDED FOR FLIGHT ABOVE 15,000 FT MSL AND CAN BE DEFERRED IAW PART 91 MEL.  AC WENT TO DEPART AIRPORT AND THE LT ENGINE LOST POWER AGAIN DURING THE TAKEOFF ROLL AT ABOUT 40 KNOTS OF AIRSPEED.  TROUBLESHOOTING OF ENGINE FUEL PUMP, FUEL NOZZLES REVEAL1L72 3O3  O  A20SO   E14EA                
20080212002592008021200259CE  2008       2          12         2008FA0000063    120080116G30604E11883         BOOT                                    BEECH 60    A60         1153604CE  LYC   O541  TIO541*     41536EA  HARTZLHCF3Y HCF3YR2     GL  PROPELLER       DEBONDED        B  PZ4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL114445W4                      P245                    DA684           PROP WAS SENT FOR REPAIRS CONSISTING OF FLUSH AND RESEAL OF PROP, PAINTING OF BLADES AND INSTALLATION OF NEW DEICE BOOTS.  AC HAS FLOWN 3.5 HRS AND THREW A DEICE BOOT, DENTED THE RT NOSE SECTION OF THE AC.  SPEAKING WITH SERVICE REP, HE STATED THAT THE GLUE USED TO ADHERE THE BOOT HAD FAILED AFTER REVIEWING PHOTOS SENT TO HIM.  IF THIS IS THE CASE, A RECOMMENDATION OF FINDING OUT LOT NUMBER OF ADHESIVE, AND RECALLING ANY WORK DONE USING THIS LOT NUMBER.  (K)                                                                                                                                                                                                                                                                  1L72 3O3  O  A12CE   E10EA   5  CP31EA    
20080131002892008013100289CE  2008       1          31         2008FA0000066    120080122G3411                FITTING                                 CESSNA206   T206H       2073303CE  LYC   O360  O360E1A6D   42305EA                              STATIC SYS      FAILED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NE012095S                       T20608442                               PRIOR TO COMPLIANCE WITH FAR 91.411, A STATIC SYSTEM CHECK WAS CONDUCTED. UNDER TEST SYSTEM SHOWED APPROXIMATELY 100 FPM DESCENT RATE. INSPECTION REVEALED THE 90 DEGREE PLASTIC FITTINGS (ONE ON EACH SIDE OF THE FORWARD FUSELAGE) FOR STATIC SYSTEM PLUMBING WERE MADE OF MOLDED PLASTIC AND INCLUDED A TINY RIDGE (MOLD LINE) ALONG THE THREADED AREA. ADDITIONALLY MFG INSTALLED THE PART WITHOUT THE USE OF PIPE SEALING COMPOUND MAKING AT LEAST PARTIAL FAILURE INEVITABLE.                                                                                                                                                                                                                                                             1H71 3O3  ORTA4CE    E286                 
20080204001062008020400106    2008       2          4          2008FA0000068    120080130G6500538715          SHAFT                                                                                                                                   TAIL ROTOR      CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP23                                                                    ONE PIECE TRANSVERSE CRACK AROUND THE AREA OF PART THAT HAD LONGITUDINAL INDICATIONS (ORIGIN UNKNOWN BUT POSSIBLY RELATED TO STRESS, FATIGUE OR WEAR), OTHER 4 PIECES ONLY WITH THE SAME LONGITUDINAL INDICATIONS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20080204001082008020400108EU  2008       2          4          2008FA0000069    120080123G5510T700A5510065000 HINGE                                   SOCATATBM   TBM700      8682000EU                                                               STABILIZER      CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA13800GS857  100               149                                     HINGE FOUND CRACKED IN AREA OF CONCERN IDENTIFIED IN AD 99-07-11, PREVIOUS INSPECTION 100 HOURS EARLIER SHOWED NO SIGN OF CRACKING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T    RTA60EU                        
20080204001022008020400102EU  2008       2          4          2008FA0000070    120080131G5280D605287300      HINGE                                   DIAMONDA42  DA42        2990004EU                                                               MLG DOOR        BROKEN          B  N3XRO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      SO15902ER195  95                42278                                   DURING FLIGHT WHEN THE LANDING GEAR WAS OPERATED, THERE WAS A NOISE HEARD BY THE CREW. UPON LANDING THE LT MAIN LANDING GEAR DOOR WAS ATTACHED ONLY BY THE LOWER DOOR CONTROL LINK. THE REAR GEAR DOOR HINGE, AFT BRACKET HAD BROKEN AT THE WELD OF THE PIECE BOLTED TO THE WING STRUCTURE. THE DOOR HAD FALLEN LOW ENOUGH TO WHERE THE FORWARD CORNER WAS WORN AWAY BY CONTACT WITH THE GROUND. THIS OPERATOR OPERATES A FLEET OF 9 DA42 AIRCRAFT. ON INITIAL INSPECTION MANY OF THE OTHER AIRCRAFT HAD CRACKS DEVELOPING AT THE POINT OF FRACTURE OF THE DAMAGED AIRCRAFT. ALL OF THE HINGE POINTS ON ALL OF THE AIRCRAFT WILL BE CHANGED.                                                                                                    1L72 3I    RTA57CE                        
20080212000382008021200038NM  2008       2          12         2008FA0000071    120080204G5220                LANYARD                                 AMD   FALC50FALCON2000  2730170NM  CFE         CFE73811B        NE                              EMERGENCY WINDOWMISSING         B  CWQDK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05275QS                       75                                      ACCESS COVER FOR THE EMERGENCY WINDOW HANDLE DOES NOT HAVE A LANYARD WHEN IT IS REMOVED.  THE COVER HANGS BY THE WIRING THAT ILLUMINATES IT PUTTING STRESS ON THE SOLDERED CONNECTIONS TO BREAK CAUSING EITHER AN INOPERATIVE EMERGENCY LIGHT OR A SHORT CAUSING MORE THAN ONE EMERGENCY LIGHT TO NOT ILLUMINATE.  THIS COVER IS REMOVED ROUTINELY FOR SECURITY PINNING OF THE EXIT HANDLE AND FOR EMERGENCY WINDOW HANDLE INSPECTION.  THERE SHOULD BE A LANYARD TO PROVIDE STRESS RELIEF FOR THE ASSOCIATED WIRING MOUNTED ON THE COVER AND IN THE WINDOW ASSY.  (K)                                                                                                                                                                          2L72 4F4  FRTA50NM   E44NE                
20080212000372008021200037NE  2008       2          12         2008FA0000072    220080111G72501808M15G03      SUPPORT         CFMINT                  AIRBUS320   A320*              EU  CFMINTCFM56 CFM565B42P  13013NE                              HPT NOZZLE      ERODED          B  QEMYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35                51X79408                779408                      DURING DISASSEMBLY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE FWD INNER NOZZLE MODULE EXPOSED THE FORWARD INNER NOZZLE SUPPORT (FINS).  IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF LOCALIZED EROSION WHICH HAD RESULTED IN PENETRATION OF THE COMPONENT.  THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTION OF THE COMPONENT, JUST AFT OF THE FWD FLANGE AND ADJACENT TO THE NR 22 AND 23 BOLT HOLES (CLOCKWISE FROM TDC, ALF) THE CAUSE OF THE EROSION IS UNKNOWN.  CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN PREVIOUSLY.  ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAIL2L72 4F4  FRTA46NM                        
20080212000352008021200035SO  2008       2          12         2008FA0000073    120080114G534162448003        ATTACH FITTING                          PIPER PA28  PA28151     7102805SO  LYC   O320  O320*       41508EA                              FUSELAGE        CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA0144542                       287415662                               THIS FUSELAGE REAR WING ATTACH FITTING WAS BEING REPLACED DUE TO CORROSION PITTS ON FRONT SURFACE.  UPON REMOVAL SOME SEVERE PITTING WAS NOTED JUST IB OF THE .3125 INCH WING ATTACH BOLT HOLE ON THE REAR SIDE OF THE FITTING.  THIS AREA IS EXPOSED TO OUTSIDE AIR AND MOISTURE AND IS LOCATED IN A DIFFICULT AREA TO INSPECT.  THIS ARA IS ALSO MORE CRITICAL IN RELATION EVENTUAL PART FAILURE THAN THE FRONT SURFACE THAT IS VISIBLE FROM INSIDE THE FUSELAGE.  RECOMMEND CLEANING DIRT OUT OF AREA AND INSPECTING WITH A GOOD LIGHT.  (K)                                                                                                                                                                                                 1L71 3O3  O  2A13    E274                 
20080212000322008021200032SO  2008       2          12         2008FA0000074    220080115G8530AEC642068       CYLINDER                                CESSNA182   182H        2072718CE  CONT  O470  O470R       17026SO  MCAULY2A34C 2A34C66     GL  NR 1            DAMAGED         B  MS2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE091928X247                    18256028    288449R     822386          WHILE PERFORMING A COMPRESSION CHECK TO FIND AN OIL LEAK, FOUND NR 1 CYLINDER WITH O COMPRESSION.  PULLED CYLINDER OFF AND FOUND THE PLATING ON THE CYLINDER LOOSE AND FLAKING OFF.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A13    E273    5  CP3EA     
20080220000262008022000026SO  2008       2          20         2008FA0000077    220080207G74146310            CAM                                     BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              MAGNETO         WORN            B      D   RETURN TO BLOCK                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      WP27878JM444  444               TH2065      690181AND6                  100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP.  INSPECTED ALL (4) MAGNETOS ON BOTH ENGINES.  FOUND ALL MAGNETO CAMS WORN.  NO LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES. THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW.  MAGNETOS, SN'S: 06121306, 06121346, 06120367, AND 06121304.                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  3A16    E3SO                 
20080317002562008031700256EU  2008       3          17         2008FA0000078    120080125G2910GCH1004         HYDRAULIC SYSTEM                        UROCOPEC120 EC120B      8680987EU                                                                               CONTAMINATED    D      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      WP28179CB555  55                1412                                    HYD POWER PACK PRE-CLOGGING INDICATOR IS DISPLAYED BEFORE FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G72 3U    NCR0001RD                      
20080319002622008031900262CE  2008       3          19         2008FA0000082    120080218G3397                CAPACITOR                               BEECH 90    E90         1152914CE  PWA   PT6   PT6*        52043EA  MCAULY4HFR344HFR34C762  NE  CABIN LIGHTS    BURNED          E      B   EMER. DESCENT                                                                                   B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      SO14662JS                       LW176                                   AT CRUISE FL 150, CREW NOTICED SMOKE AND ELECTRICAL ODOR COMING FROM SIDEWALL UNDERNEATH EMERGENCY EXIT.  PIC DECLARED EMERGENCY AND LANDED AC WITHOUT FURTHER INCIDENT.  UPON INSP OF  SIDEWALL UNDER EMERGENCY EXIT, IT WAS NOTICED THAT A SMALL HOLE WHICH APPEARED TO LOOK LIKE A CIGARETTE BURN AT FIRST HAD PENETRATED THROUGH HONEYCOMB MATERIAL AND THE ULTRA SUEDE LINER THAT COVERS THE SIDEWALL.  UPON CLOSER INSP BEHIND SIDEWALL, NO ELECTRICAL COMPONENTS OR WIRING ARE LOCATED BEHIND THE AREA WHERE THE HOLE IS LOCATED.  AFTER REMOVING THE VALANCE PANEL ON THE EMERGENCY EXIT WINDOW, IT WAS NOTICED THAT THE CAPACITOR AND THE DIODE FOR THE INDIRECT LIGHTING POWER SUPPLY WAS BURNED.                                     1L72 3T3  T  3A20    E2NE    6  C3PNE     
20080403000402008040300040CE  2008       4          3          2008FA0000084    120080221G29101285094         LINE                                    CESSNA210   T210M       2073451CE  CONT  O520  TSIO520*    17040SO                              HYDRAULIC SYS   CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15761AV4400                   21062110                                REPLACED HYDRAULIC TUBE 128509-4 DUE TO CHAFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE.  THIS WAS FOUND BY INSPECTION AS DESCRIBED IN MFG SEB07-03 AND WHICH HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLEM.  THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SERVICE BULLETIN APPLICABILITY.                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A21    E8CE                 
20080225000042008022500004CE  2008       2          25         2008FA0000085    120080221G29101285094         LINE                                    CESSNA210   T210M       2073451CE                                                               HYDRAULIC SYS   CHAFED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15761AV4400                   21062110                                REPLACED HYDRAULIC TUBE (PN 128509-4) DUE TO CHAFFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE.  THIS WAS FOUND BY INSPECTION AS DESCRIBED IN SEB07-03 FOR 182 SERIES, AND WHICH 182'S HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLEM.  THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SB APPLICABILITY.                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O      3A21                         
20080225000052008022500005CE  2008       2          25         2008FA0000086    120080215G57110411129         SPAR                                    CESSNA150   150G        2071816CE  CONT  O200  O200*       17020SO                              WING            CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07     3895                   15065116                                WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSP OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAGE (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS AND THE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED. THE SAME P/N AND WING ATTACHMENT SYS IS USED ON MOST OF THE AC SERIES HIGH WING AIRCRAFT.                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A19    E252                 
20080403000222008040300022CE  2008       4          3          2008FA0000087    120080215G53110411129         SPAR                                    CESSNA150   150G        2071816CE  CONT  O200  O200*       17020SO                              WING            CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP073816J3895                   15065116                                WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSPECTION OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAGE (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS AND THE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED.                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A19    E252                 
20080402000412008040200041SO  2008       4          2          2008FA0000088    220080207G74146310            CAM                                     BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              MAGNETO         WORN            B      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      WP27878JM444  444               TH2065      690181AND6                  100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP.  INSPECTED ALL FOUR MAGNETOS ON BOTH ENGINES.FOUND ALL MAGNETO CAMS WORN. NO  LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES. THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW.  SLICK 6310 MAGNETOS, SN'S: 06121306, 06121346, 06120367, AND 06121304.                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  3A16    E3SO                 
20080310003302008031000330CE  2008       3          10         2008FA0000089    120080129G29157629001004001   PRESSURE SWITCH                         LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              HYDRAULIC SYS   FAILED          B  WMYRA   UNSCHED LANDING                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      SO09444MW2127                   131                                     LT HYDRAULIC PRESSURE SWITCH (S9) FAILED IN FLIGHT, RESULTING IN LOSS OF HYDRAULIC FLUID AND FAILURE OF BOTH LT AND RT HYDRAULIC PUMPS.  NECESSITATED A FLIGHT DIVERSION TO AN ALTERNATE AIRPORT WITH AN EMERGENCY DECLARATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTT00008WIE6WE                 
20080310003322008031000332CE  2008       3          10         2008FA0000091    120080122G3245                TUBE                                    CESSNA172   172R        2072401CE  LYC   O360  IO360A1A    41514EA                              LANDING GEAR    FAILED          B  AW4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP11784WW                       17280816                                FROM SEPT 7 TO PRESENT, AC HAS EXPERIENCED (3) LANDING GEAR TIRE TUBE FAILURES.  FAILURES ALL OCCURRED IN THE SIDEWALL OF THE TUBES.  THERE WAS NO EVIDENCE OF THE TUBES BEING PINCHED OR OTHERWISE DAMAGED DURING INSTALLATION.  DAMAGE RANGED FROM SMALL (.1250 INCH) SPLITS TO A LARGE (.5 INCH) SPLIT.  EXAMINATION OF THE TUBE SIDEWALLS EVIDENCED WHAT APPEAR TO BE SOME FORM OF (WEATHER CHECKING) THAT NORMALLY APPEARS ON OLD RUBBER COMPONENTS.  ALL TUBES WERE OF RECENT MANUFACTURE.  ONE FAILURE OCCURRED ON A G15/6.00/6 TUBE (PN 302-246-401) WITH TT OF 123 HOURS.  (2) FAILURES OCCURRED ON 5.00 X 5 TUBES (PN 302-013-400 AT 125 HOURS AND 112 HOUR RESPECTIVELY.  TUBES WERE FORWARDED TO MFG FOR EVALUATION.  EVALUATION IS 1H71 3O3  ONT3A12    1E10                 
20080310003332008031000333    2008       3          10         2008FA0000092    420080111G2564100102303       LIFE RAFT                                                                                                                               CABIN           UNWANTED DEPLOY D  JAVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA61                                                                    LIFE RAFT STARTED TO INFLATE WHILE PLACING ON AIRCRAFT WITH NORMAL HANDLING.  LIFE RAFT WAS IMMEDIATELY REMOVED AND HELD FOR VENDOR PICK-UP.  NOTE:  LIFE RAFT WAS A LOANER , OVERHAULED ON 7/26/07.  LIFE RAFT WAS RECEIVED AND INSPECTED ON 1/11/2008 WITH NO DAMAGE NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20080331000412008033100041GL  2008       3          31         2008FA0000093    320080204G6114                HUB                                     CESSNA188   A188B       2073005CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C98    GL  PROPELLER       CRACKED         B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19731VX                       18803200T               775315          PROPELLER HUB CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  A9CE    E5CE    5  CP3EA     
20080310003342008031000334GL  2008       3          10         2008FA0000094    320080204G6114                HUB             MCAULY                  CESSNA337   M337B       2075708CE  CONT  O360  IO360D      17025SO  MCAULY2AF34CD2AF34C61   GL  PROPELLER       CRACKED         D  LU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19373AZ           661450      337M0079                                RELEVENT INDICATION (CRACKED).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3O3  ORTA6CE    E1CE    5  CP5EA     
20080310003352008031000335GL  2008       3          10         2008FA0000095    320080204G6114                HUB             MCAULY                  CESSNA402   402B        207590PCE  CONT  O520  TSIO520*    17040SO  MCAULY3AF32C3AF32C87    GL  PROPELLER       CRACKED         D  LU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1995RG            779643      402B0538                                RELEVENT INDICATION (CRACKED 2 PLACES).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A7CE    E8CE    5  CP22EA    
20080310003362008031000336SO  2008       3          10         2008FA0000096    120080128G534386282010        SPAR                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              NLG             CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01856ND                       4495001                                 THE SPAR ASSY WAS CRACKED AT THE LT SIDE NOSE GEAR SUPPORT FITTING.  THE CRACK RADIATED OUT FROM THE AFT LOWER BOLT ATTACHMENT ( AS VIEWED FROM  BELOW THE NOSE STRUCTURE FLOORING) ONCE THE A-FRAME SUPPORT WAS REMOVED, THERE WAS A (2 INCH) CRACK IN THE SPAR WEB (NOT VISIBLE UNTIL THE SUPPORT WAS REMOVED).  THE LOWER EXTRUSION HAS BEEN REPLACED WITH NEW AT SOME POINT IN THE AIRPLANES HISTORY (NOT AT THIS SHOP).  THE EXTRUSION CRACKING WAS THE REASON FOR DISASSEMBLY AT THIS TIME.  THIS IS ADDRESSED IN AD 81-10-01 BUT THE AD IS NOT APPLICABLE TO THIS SERIAL NUMBER AIRCRAFT.  SB NR 1143 COVERS THE LATER SN AC.  (K)                                                                                                       1L72 3O3  O  A19S0   E286                 
20080310003462008031000346GL  2008       3          10         2008FA0000099    220080131G723023074076        SCROLL                                  BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              COMPRESSOR      BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0531PB 1082                   53569       CAC45245                    COMPRESSOR (PN 23065593 SN CAC45245) WAS RECEIVED INTO THE SHOP FOR REMOVAL AND REPLACEMENT OF THE SCROLL (PN 23074076(B) SN 40353) FOR A VISIBLE OPEN HOLE OR BROKEN OFF HEX EXTERNAL BOSS LOCATING PIN AT THE TURNING VANE LOCATION ON THE SCROLL.  THE OPERATOR CONDUCTS PATROLLING OR POLICE ACTIVITY USING THE AC AND FOUND THE DEFECT WHILE PERFORMING A 100 HR MAINT TASK.  THE AFFECTED COMPRESSOR SCROLL WAS COATED WITH SERVETEL WHICH IS AN OEM APPROVED COATING FOR PROTECTION AGAINST CORROSION AND AS INDIDCATED IN THE LOG BOOKS, THIS IS THE 2ND SCROLL TO HAVE BEEN REPLACED.  (K)                                                                                                                                             1G71 3U3  UO H2SW    E1GL                 
20080324004302008032400430CE  2008       3          24         2008FA0000100    120080205G29157629001004001   PRESSURE SWITCH                         LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              HYDRAULIC SYSTEMFAILED          D      A   UNSCHED LANDING                                                                                 JK WARNING INDICATION        FLUID LOSS                                          CRCRUISE         1                      SO09444MW                       131                                     APPROXIMATELY 40 MIN IN TO PLANNED FLIGHT, WHILE AT FL410, IN FINAL CRUISE CONDITION, A WHITE ADVISORY CAS MESSAGE APPEARED INDICATING (MAIN HYD QTY LOW).  FLIGHT CREW OPENED THE APPROPRIATE CREW CHECKLIST AND FLIGHT MANUAL AND REFERENCED THE CHECKLIST WHICH SAID (MAIN HYDRAULIC QUANTITY IS LOW), WITH NO ACTION REQUIRED.  THE PF DIRECTED THE PNF TO REFER TO ANY ABNORMAL PROCEDURES OR ANY EMERGENCY CHECKLIST PAGE PROCEDURES AS A PRECAUTION FOR LOSS OF HYDRAULIC QUANTITY OR PRESSURE.  THE CREW REVIEWED THESE PROCEDURES AND CONTINUED IN CRUISE.  APPROX 15 MIN LATER, DURING DESCENT, A WHITE (L HYD PUMP LO) CAS MESSAGE BEGAN TO APPEAR INTERMITTENTLY, AND HYD PRESSURE FLUCTUATIONS WERE NOTED ON THE PRESSURE INDICATIO2L72 4F4  FRTT00008WIE6WE                 
20080319002952008031900295    2008       3          19         2008FA0000101    420080108G2210238006679       YAW DAMPER                              LEAR  24    24          5170302CE                                                                               FAULTY          B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      WP01989TL                       160                                     THIS PART FAILED TO OPERATE DURING FIRST FLIGHT, AFTER INSTALLATION, AT CRUISE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4J      A10CE                        
20080403000552008040300055    2008       4          3          2008FA0000104    420080224G3197                WIRE HARNESS                            CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              INSTRUMENT PANELBURNED          B      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CE07227BH6                      172S10662                               WIRING HARNESS BEHIND AUDIO PANEL WAS CHAFING ON BRACKET THAT HELPS SUPPORT STANDBY BATTERY ON THE PFD SIDE AND CAUSED WIRING TO ARC AND BURN (NOTE: HARNESS IS FOR LIGHT DIMMING OF G-1000). FOUND HARNESS PULLED HARD AGAINST BRACKET.  THIS CAUSED THE WIRE TO CHAFE THROUGH THE INSTALLATION AND SHORT OUT. HOWEVER, CIRCUIT BREAKERS AND TRANSISTORS FOR THE LIGHT DIMMING CIRCUIT DID AT NO TIME POP OR FAIL AND WOULD EXPECT TO HAPPEN WHEN THEIR IS A HARD SHORT SINCE THE WIRES ARE ASSOCIATED WITH THE LIGHT DIMMING CIRCUIT. THE HARNESS WAS PULLED HARD AGAINST THE STRUCTURE AS TO CHAFE THROUGH THE INSULATION AND ARC/SCORCHED THE STRUCTURE. THE WIRE BURNED THROUGH AND ALSO, DAMAGED OTHER WIRES IN THE HARNESS. HARNESS WAS A1H71 3O3  ONT3A12    1E10                 
20080331000432008033100043CE  2008       3          31         2008FA0000106    120080211G5340                BRACKET                                 CESSNA500   550         2076604CE                                                               VOLT REGULATOR  CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP21554MB                       5500040                                 LT GENERATOR VOLTAGE REGULATOR MOUNT BRACKET FOUND TO HAVE CORROSION AT MOUNT SURFACE.  ELECTRICAL GROUND PATH AFFECTED.  CORROSION REMOVED ALLOWING GOOD GROUND AND ABLE TO ADJUST VOLTAGE REGULATOR, TO SPEC.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4F      A22CE                        
20080331000442008033100044CE  2008       3          31         2008FA0000107    120080209G291098811241        POWERPACK                               CESSNA210   T210N       2073456CE  CONT  O520  TSIO520*    17040SO                              HYD SYSTEM      WORN            C      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      LDLANDING        1                      SW17127TC3309                   21063381                                SMOKE IN COCKPIT, GEAR NOT FULLY RETRACTED, EXTENDED OK.  FOUND HYDRAULIC POWERPACK MOTOR (ORIGINAL) WORNOUT.  REMOVED AND REPLACED WITH O/H UNIT.  OPS, OK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A21    E8CE                 
20080331000452008033100045SW  2008       3          31         2008FA0000108    120080227G28415643860         GAUGE                                   MOONEYM20   M20D        5870210SW  LYC   O360  O360A1D     41514EA  HARTZLHCC2Y HCC2YK1     GL  FUEL SYSTEM     INACCURATE      D      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      GL156608U5103                   103         L533036     CH26709E        FUEL GAUGE INDICATION IS APPROX 2.5 TO 3 GAL HIGHER THAN WHAT IS IN THE TANK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A3     E286    5  CP920     
20080331000482008033100048    2008       3          31         2008FA0000110    420080215G2312                ANTENNA                                 ISRAEL1125  ASTRASPX    4500205EU                                                               VHF SYSTEM      GOUGED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP09411MM                       080                                     FOLLOWING REMOVAL OF SATCOM ANTENNA FROM UPPER FUSELAGE FOR INSPECTION, NOTICED FOOTPRINT OF PREVIOUSLY REMOVED NR 1 VHF ANTENNA.  UPON INSPECTION OF VHF ANTENNA FOOTPRINT, FOUND NUMEROUS APPARENT MECHANIC INDUCED GOUGES ON FUSELAGE OUTER SKIN.  DAMAGE WAS APPARENTLY CAUSED BY IMPROPER REMOVAL OF PREVIOUSLY INSTALLED VHF ANTENNA.  REPAIR WAS TO BLEND OUT GOUGES IAW DER EVALUATION.  (K)                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16NM                        
20080325000332008032500033GL  2008       3          25         2008FA0000111    120080304G6420ECD00213        BEARING                                 ENSTRMF28   280FX       3300506GL  LYC   O360  HIO360F1AD  41514EA                              TAIL ROTOR      SEIZED          D      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      NM03285SH1                      2120                                    THE THRUST BEARINGS IN THE TAIL ROTOR BLADE GRIPS ARE OF MATCHED SETS. THESE SETS HAVE A SPECIFIC INSTALLATION ORIENTATION. ORIENTATION OF THESE BEARINGS ARE MARKED WITH A (V). THE (V) IS TO BE ORIENTED TOWARD THE CENTER OF THE TAIL ROTOR SPINDLE HUB. ON THESE SPECIFIC BEARINGS THE (V) WAS MARKED POINTING THE WRONG DIRECTION LEADING TO A REVERSED INSTALLATION CAUSING A SEIZURE OF THE BEARINGS. ALL BEARINGS WERE INSTALLED IN ACCORDANCE WITH ENSTROM SERVICE LETTER 133 DATED JUNE 8, 1987 , SERVICE LETTER 153 DATED FEBRUARY 15, 2002 AND ENSTROM F SERIES MAINTENANCE MANUALS REVISION 1 DATED 4-3-86 AND REVISION 2 DATED 11-18-88.                                                                                          1G71 3O3  O  H1CE    1E10                 
20080317002642008031700264EU  2008       3          17         2008FA0000114    120080129G2435160SG140Q1XL    STARTER GEN                             UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIUS2F    60010NE                              ENGINE          FAILED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP28179CB558  58                1412                                    STARTER/GENERATOR FAILED TO ENERGIZE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G72 3U3  UNCR0001RD E34NE                
20080331000522008033100052    2008       3          31         2008FA0000115    420080118G6113C2365           BULKHEAD        SNSNCH                  MAULE MX7   MXT7160     5470204SO  LYC   O320  O320*       41508EA  SNSNCH74D   74DM        EA  PROP SPINNER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW1157HS 3600                   17005C      RL1318639A  A57306          THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT MOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A23    E274    5  NP88614   
20080331000532008033100053    2008       3          31         2008FA0000116    420080118G6113C2367           BULKHEAD        SNSNCH                  MAULE MX7   MXT7180A    5460187SO  LYC   O360  O360C4F     42290EA  SNSNCH76E   76EM8       EA  PROP SPINNER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11114HS300                    21092C      L4051336A   37618K          THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONC3A23    E286    5  NP4EA     
20080331000542008033100054    2008       3          31         2008FA0000117    420080118G6113C2367           BULKHEAD        SNSNCH                  MAULE MX7   MXT7180A    5460187SO  LYC   O360  O360C4F     42290EA  SNSNCH76E   76EM8       EA  PROP SPINNER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11171HS200                    21096C      L4089636A                   THE FWD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONC3A23    E286    5  NP4EA     
20080331000562008033100056    2008       3          31         2008FA0000118    420080118G6113C2367           BULKHEAD                                MAULE MX7   MXT7180A    5460187SO  LYC   O360  O360C4F     42290EA  SNSNCH76E   76EM8S5     EA  FWD SPINNER     CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11125HS200                    21093C      L4056636A   37939K          THE FWD BULKHEAD CRACKED THROUGHT THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONC3A23    E286    5  NP4EA     
20080331000572008033100057    2008       3          31         2008FA0000119    420080118G6113C2367           BULKHEAD        SNSNCH                  MAULE MX7   MXT7180A    5460187SO  LYC   O360  O360C4F     42290EA  SNSNCH76E   76EM8       EA  PROP SPINNER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11152HS200                    21095C      L4081336E   38281K          THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONC3A23    E286    5  NP4EA     
20080331000592008033100059GL  2008       3          31         2008FA0000120    120080206G3020                CONTROL ARM                             DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              CARB HEAT       BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07423FP13                     40FC023                                 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTAKE.  RECOMMEND INSTALLIING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR DIFFERENT ATTACHMENT PROVISION ALTOGETHER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA47CE   E286                 
20080331000612008033100061GL  2008       3          31         2008FA0000121    120080206G3020D4F732612001    CONTROL ARM                             DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              CARB HEAT       BROKEN          D  GO3SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07418FP31                     40FC018                                 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTAKE.  RECOMMEND INSTALLING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR DIFFERENT ATTACHMENT PROVISION ALTOGETHER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTA47CE   E286                 
20080331000622008033100062CE  2008       3          31         2008FA0000122    120080206G2197                WIRE HARNESS                            BEECH 90    C90A        1152911CE                                                               A/C START CONT  MISINSTALLED    D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE014764A                       LJ1161                                  AIR CONDITIONER NOT COOLING.  FOUND WIRING FOR AC START CONTROL PANEL AS WELL AS COMPRESSOR CLUTCH NOT IN PROPER CONFIGURATION IAW WIRING PRINT.  AFTER PROPER INSTALLATION OF WIRING AND SUBSEQUENT OPS CHECK, THE MOTOR AND SYS, THE AIR CONDITIONER WOULD CYCLE IN AND OUT OF ITS SOFT START CYCLE.  THIS IN TURN CREATED EXCESSIVE HEAT IN THE LOAD RESISTOR CIRCUIT.  THIS CYCLING CONTINUED UNTIL AT SOME POINT THE SOFT START CIRCUIT FAILED, WHICH CAUSED THE LOAD RESISTOR TO OVERHEAT AND MELT THE PHENOLIC BLOCK SHIELDS WHICH CAUGHT  FIRE AND DAMAGED THE IMMEDIATE SURROUNDING STRUCTURE OF THE NOSE COMPARTMENT.  PROBABLE CAUSE WOULD INDICATE FAILURE OF THE AC START CONTROL PANEL CIRCUITRY THAT SUBSEQUENTLY LEAD TO A NOSE 1L72 3T    RT3A20                         
20080331000632008033100063    2008       3          31         2008FA0000123    420080114G611305502366        BULKHEAD                                CESSNA172   172H        2072424CE  CONT  O300  O300*       17022SO                              PROP SPINNER    CRACKED         D  HE8SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE094987R92                     17256341                                PROP SPINNER FWD, BULKHEAD CRACKED NEAR MOUNT BOLTS.  PART PROBABLY NOT STURDY.  RECOMMEND PART BE MADE OF THICKER METAL DOUBLER INSTALLED.  ALSO, IT APPEARED THAT MOUNT BOLT HOLES MAY BE TOO LARGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E253                 
20080325000682008032500068SW  2008       3          25         2008FA0000124    120080114G6220NAS5161A        GREASE FITTING  BELDEN                  BELL  212   212         1181420SW                                                               M/R HUB         BLOCKED         W  DB5YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33                                                                    DURING LUBRICATION OF A MAIN ROTOR HUB, WE DISCOVERED THAT THE SPRING IN THE GREASE FITTING (NAS516-1A) WAS PRESSED OUT FROM THE FITTING AND BLOCKED THE GREASE PASSAGE.  THIS HAPPENED (3) TIMES.  WE FOUND THE SPRINGS AFTER EVERY ATTEMPT.  THIS COULD RESULT IN A LOOSE SPRING IN A ROTATING BEARING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 4U      H4SW                         
20080325001052008032500105WP  2008       3          25         2008FA0000125    220080212G72108937396         GEAR                                    CASA  C212  C212CC      2410204EU  GARRTTTPE331TPE33110R   0517 WP                              GEAR BOX        BROKEN          W  X1NYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP03961BW2170       P5372       248                                     ENGINE RECEIVED WITH BROKEN FEATHER VALVE, NOSE CONE NUTS LOOSE, ROTATION OF ENGINE ROTATING COMPONENTS FOUND CLUNKY AND SEIZED.  MAGNETIC PLUG CONTAMINATED WITH FINE METAL PARTICLES.  NOSE CONE AND DIAPHRAGM REMOVED TO INVESTIGATE CAUSE OF FAILURE.  WHEN DIAPHRAGM ASSY WAS REMOVED BIG CHUNKS OF METAL NOTICED AT THE GEARBOX CAVITY IDENTIFIED AS BULL GEAR PIECES.  HIGH SPEED PINION GEAR HELICAL TEETH BROKEN OFF AND CRUNCHED.   SEVERAL BULL GEAR TEETH BROKEN OFF.  BIG PIECE (2-3 INCH) OF GEAR RIM MISSING AND FOUND TRAPPED BETWEEN DIAPHRAGM HOUSING AND SCAVENGE PUMP CAUSING A RUPTURE OF THE PUMP HOUSING.  THE PRELIMINARY REASON FOR THE GEAR BOX FAILURE IS BELIEVED TO BE CAUSE BY BULL GEAR FAILURE.  THE SEPARATION 2H72 4T4  T  A43EU   E4WE                 
20080325001062008032500106NE  2008       3          25         2008FA0000126    220080111G72501808M15G03      SUPPORT         CFMINT                  AIRBUS320   A320*              EU  CFMINTCFM56 CFM565B4P        NE                              HPT NOZZLE      UNSERVICEABLE   W  QEMYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35                51X79408                799408                      DURING DISASSY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE FWD INNER NOZZLE SUPPORT (FINS).  IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF LOCALIZED EROSION WHICH HAD RESULTED IN PENETRATION OF THE COMPONENT.  THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTION OF THE COMPONENT, JUST AFT OF THE FWD (CLOCKWISE).  THE CAUSE OF THE EROSION IS UNKNOWN.  CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN, PREVIOUSLY.  ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAILURE ANALYSIS.  (K)                                                                                        2L72 4F4  FRTA46NM   E38NE                
20080331001382008033100138EU  2008       3          31         2008FA0000127    120080206G2497                WIRE                                    AMD   FALC50FALCON900   2730160EU  GARRTTTFE731TFE731*     01518WP                              ELECTRICAL      DAMAGED         B      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      NM09900VL                       60                                      WHILE TROUBLESHOOTING AC ELECTRICAL OUTLETS FOR BEING INOPERATIVE.  REMOVED FLOOR PANEL TO ACCESS AC INVERTER AND DETECTED BURNING PLASTIC.  FOUND SYSTEM HAD SELF RESETTING CIRCUIT BREAKERS INSTALLED THAT HAD BEEN AND WERE CONTINUING TO RESET AND ALLOWING THE KAPTON WIRE INSULATION AND SPIRAL WRAP TO BURN.  ONE OF THE AREAS THAT BURNED WAS ONLY 3 INCHES BELOW A CARBON FLIGHT CONTROL ROD.  THIS HAPPENED ON A VERY LONG FLIGHT, THE OUTCOME COULD HAVE BEEN VERY TRAGIC.  REPLACING THES C/B`S WITH NON SELF RESETTING CB WOULD PREVENT THE DAMAGE FROM PROGRESSING TO THE POINT IN WHICH IT DID IN THIS INSTANCE.  (K)                                                                                                            2L73 4F4  FRTA46EU   E6WE                 
20080331001392008033100139GL  2008       3          31         2008FA0000128    120080215G282251000020        PUMP                                    DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              FUEL SYS        INOPERATIVE     D  GO3SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07417FP102                    40FC017                                 AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE.  INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS.  PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA47CE   E286                 
20080331001422008033100142GL  2008       3          31         2008FA0000131    120080307G282251000020        PUMP                                    DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              FUEL SYS        INOPERATIVE     D  GO3SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07418FP                       40FC018                                 AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE.  INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS.  PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA47CE   E286                 
20080331001432008033100143GL  2008       3          31         2008FA0000132    120080227G282251000020        PUMP                                    DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              FUEL SYS        INOPERATIVE     D  GO3SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07419FP265                    40FC019                                 AFTER A PREVIOUS FLIGHT AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE.  INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS.  PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTA47CE   E286                 
20080402000402008040200040CE  2008       4          2          2008FA0000137    120080123G3250358250549       ARM                                     BEECH B300  B300B350C          CE  PWA   PT6   PT6*        52043EA                              STEERING        WORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA1357SC 6028                   FL34                                    NOSE GEAR STEERING ARM WORN EXCESSIVELY AT ROD END ATTACHMENT POINT FOR STEERING PUSH PULL TUBE. LOSS OF NOSE GEAR STEERING WOULD OCCUR IF ARM WERE TO BREAK. THE ORIGINAL .2500 INCH BOLT HOLE WAS ELONGATED TO A .5 INCH SLOT. THE ARM IS ATTACHED TO THE PILOT'S RUDDER PEDAL TORQUE SHAFT AND IS LOCATED IN A SMALL UNPRESSURIZED PANEL AREA BELOW THE PILOT SIDE FLOORBOARDS. INSPECTIONS ARE OVERLOOKED BECAUSE THIS SEALED PANEL IS NOT OPENED TYPICALLY DURING ROUTINE INSPECTIONS.                                                                                                                                                                                                                                                     2L72 4T3  TRTA24CE   E2NE                 
20080402000132008040200013CE  2008       4          2          2008FA0000146    120080129G322007436051        TORQUE LINK                             CESSNA182   182G        2072716CE  CONT  O470  O470*       17026SO                              ZONE 700        CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0582BG 2855                   18255427                                ON INSPECTION, A CRACK WAS IDENTIFIED IN THE FORGING FOR THE UPPER TORQUE LINK FOR THE NOSE LANDING GEAR. THE CRACK WAS ON BOTH SIDES OF THE BEAM SECTION ADJACENT TO THE EXTENSION STOP FOR THE GEAR.(AFT SIDE)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A13    E273                 
20080331001752008033100175EU  2008       3          31         2008FA0000148    120080327G6320C632A2103101    HOUSING                                 UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              GEARBOX         WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19179CB622        M569        1412        34224                       INPUT BOX HOUSING BEARING WORN. (SHOULDER)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G72 3U3  UNCR0001RD E34NE                
20080401001092008040100109EU  2008       4          1          2008FA0000149    120080227G2497                CONNECTOR                               DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE1250299       EU                              FUEL RAIL       ARCED           D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP284129M480                    42AC068     020201611                   CONNECTOR IS NOT MAKING GOOD CONTACT AND CAUSING ARCING.  PROBABLE CAUSE IS AUTOMOTIVE QUALITY AND NOT OF THE THREADED TYPE.  TO PREVENT OCCURRENCE RECOMMEND USING AVIATION THREADED TYPE PLUG.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3I3  BRTA57CE   E00069EN             
20080401001112008040100111CE  2008       4          1          2008FA0000150    120080307G2497S26062          WIRE HARNESS                            CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1C235 1C235LFA    GL  FLAP MOTOR      DETERIORATED    D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05467CM                       17280859    L2651551A   TJ040           UPON INSPECTION OF A PHASE II INSPECTION, IT WAS DISCOVERED THAT THE WIRE BUNDLE MOUNT PN S26062 THAT HOLDS THE FLAP MOTOR WIRE HARNESS HAD DETACHED FROM THE RIB IN THE RT WING AND HAD ALLOWED THE WIRE BUNDLE TO CHAF INTO THE INSPECTION PANEL SUPPORT ON THE WING.  THE WIRE BUNDLE HAD (2) WIRES CHAFED THROUGH THE INSULATION AND WAS IN CONTACT WITH THE BARE WIRE.  RECOMMEND INSPECTION OF THESE MOUNTS AND REPLACE AS NEEDED, OR ON CONDITION.  (K)                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10    5  NP12EA    
20080401001212008040100121EA  2008       4          1          2008FA0000151    220080305G852013B2713485      CRANKSHAFT                                                                 LYC   O360  O360A4A     41514EA                              ENGINE          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW17                                                                    CRANKSHAFT HAS VERY LARGE RADIAL CRACKS AT THE BASE OF THE FORWARD THRUST FACE, EXTENDING APPROX. 85% OF THE WAY AROUND THE SHAFT. APPEARS TO HAVE BEEN A FRONTAL IMPACT ON THE CRANKSHAFT DRIVING IT REWARD IN THE ENGINE AND IMPACTING THE CRANKCASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                3  O          E286                 
20080404000012008040400001    2008       4          4          2008FA0000152    120080304G499038809981        PUMP                                                                                                                                    APU OIL         FAILED          B      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SW99     135991468                                                      2 APUS WERE REPORTED LOP AUTO SHUTDOWN. HAVE RECEIVED APU P-195 AND P-141 FROM FOR THE SAME REASON OF REMOVAL. DISASSEMBLY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE'S BEARING DID NOT HAVE LUBRICATION AT ALL.  THE OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLATE MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQUENCE OF INSUFFICIENT OIL PRESSURE.                                                                                                                                                                                 
20080402000432008040200043CE  2008       4          2          2008FA0000153    120080212G2810                CHAIN                                   CESSNA172   172S        2072439CE  CONT  C85   C8512F      17008SO                              FUEL CAP        LOOSE           D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL155055Q4413                   8972                                    LT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CAP RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END (S) HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SENDING UNIT LOCKING IT AT A 10 GAL. INDICATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E233                 
20080403000252008040300025CE  2008       4          3          2008FA0000154    120080215G551145A2111XXXX     RIB                                     BEECH MU300 400A        1155402CE                                                               HORIZONTAL STAB CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13907JE5335                   RK107                                   FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES ,  IN 3 LT, AND 4 RT HORIZONTAL STABILIZER INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE. AFFECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4F    RTA16SW                        
20080403000262008040300026CE  2008       4          3          2008FA0000155    120080215G551145A2111XXXX     RIB                                     BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13907JE5335                   RK107                                   FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES ,  IN 3 LT , AND 4 RT HORIZONTAL STABILIZER INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE AFFECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4F4  FRTA16SW   E25EA                
20080403000462008040300046    2008       4          3          2008FA0000156    420080222G25645A320410312     LIFE RAFT                               AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE731*     01518WP                              CABIN           INOPERATIVE     B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01900KE     1                 052                                     RECEIVED SUBJECT LIFE RAFT FOR ANNUAL INSPECTION FROM REGISTERED OWNER. THE LIFE RAFT WAS RECEIVED BY THIS REPAIR STATION IN A PACKED CONDITION AND IN ITS "AS-REMOVED" CONDITION FROM THE AIRCRAFT.  DURING DISASSEMBLY AND PRELIMINARY INSPECTION OF SUBJECT LIFE RAFT, FOUND A STEEL SAFETY PIN INSTALLED IN THE LIFE RAFT INFLATION BOTTLE. THE LIFE RAFT WOULD NOT HAVE BEEN OPERABLE WITH THIS SAFETY PIN INSTALLED HAD THIS LIFE RAFT BEEN CALLED UPON TO FUNCTION IN AN ACTUAL EMERGENCY.                                                                                                                                                                                                                                               2L73 4F4  F  A46EU   E6WE                 
20080403000482008040300048    2008       4          3          2008FA0000157    420080108G2210238006679       YAW DAMPER                              LEAR  24    24          5170302CE                                                               ZONE 300        FAULTY          B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      WP01989TL                       160                                     THIS PART FAILED TO OPERATE DURING FIRST FLIGHT AFTER INSTALLATION AT CRUISE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4J      A10CE                        
20080403000492008040300049SO  2008       4          3          2008FA0000160    120080225G32450923150         TUBE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              LT TIRE         CUT             B      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      GL21359ND118                    2842187                                 UPON LANDING, LT MAIN TIRE DEFLATED UPON DISASSEMBLY TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFERENCE OF THE TUBE. THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH TUBE MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE BEEN FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA).                                                                                                                                                                                                                                                    1L71 3O3  O  2A13    E274                 
20080403000512008040300051SO  2008       4          3          2008FA0000161    120080225G32450923150         TUBE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              LT TIRE         CUT             B      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      GL21359ND118                    2842187                                 UPON LANDING, LT MAIN TIRE DEFLATED.   UPON DISASSEMBLY, TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFERENCE OF THE TUBE.  THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH TUBE MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE BEEN FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA).                                                                                                                                                                                                                                               1L71 3O3  O  2A13    E274                 
20080403000522008040300052EA  2008       4          3          2008FA0000164    220080110G74146393            MAGNETO                                 GULSTM500   500S        0141107SW  LYC   O540  IO540E1B5   41532EA                              ENGINE          WORN            B      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      GL1551RF 100                    3298                                    ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND THE CAM WORN OUT . 100.3 HRS SINCE NEW                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3O3  O  6A1     1E4                  
20080403000542008040300054EA  2008       4          3          2008FA0000167    220080226G74146393            MAGNETO                                 GULSTM500   500S        0141107SW  LYC   O540  IO540E1B5   41532EA                              ENGINE          WORN            B      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      GL1551RF 81                     3298                                    ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND THE CAM WORN OUT . 81.1 HRS SINCE NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3O3  O  6A1     1E4                  
20080403000562008040300056SO  2008       4          3          2008FA0000168    120080226G32450923080         TUBE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              TIRE            FAILED          B      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL21437ND28                     2842214                                 NOSE TIRE FOUND FLAT IN HANGER. DISASSEMBLE FOUND SMALL SLIT IN OUTSIDE CIRCUMFERENCE OF TUBE TYPICAL OF OTHER FLAT TIRES FROM SAME MFG.  SAMPLE FAILED TUBES HAVE BEEN RETURNED TO MFG FOR EVALUATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O3  O  2A13    E274                 
20080403000612008040300061CE  2008       4          3          2008FA0000169    120080220G2820057313K001301   LINE                                    CESSNA172   172S        2072439CE  THIELTTAE125TAE1250299       EU                              FUEL SYSTEM     CRACKED         C      BA  EMER. DESCENT           UNSCHED LANDING                                                         YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      SO191735L3                      172S10647   020201880                   PILOT WAS FLYING AT 5,500 FEET WHEN THE ENGINE STARTED RUNNING ROUGH. WITHIN MOMENTS THE FADEC (A) LIGHT CAME ON THEN FADEC (B) ILLUMINATED. THE PILOT TRIED TO ACTIVATE THE MANUAL OVERRIDE BUT WAS UNABLE TO PUT OUT THE WARNING LIGHTS. THE RPMS DROPPED UNTIL ENGINE STOPPED, THEN THE PROP STOPPED. THE PILOT DID A GREAT JOB AND FOUND A SAFE ROAD TO LAND ON, AND COMMUNICATED WITH ATC THAT HE PLANNED TO MAKE AN EMERGENCY LANDING. WHEN THE PILOT LANDED HE ADVISED ATC THAT HE WAS SAFE AND DID NOT REQUIRE ANY SERVICES (FIRE, PARAMEDICS). ATC NOTIFIED THE LOCAL SHERIFFS DEPARTMENT AND A DEPUTY WAS SENT OUT TO CONFIRM. THE PILOT MOVED THE AC FROM THE ROADWAY TO AVOID DAMAGE OR ANY INCIDENT WITH TRAFFIC. UPON REACHING TH1H71 3O3  BNT3A12    E00069EN             
20080403000622008040300062SO  2008       4          3          2008FA0000173    120080228G32450923080         TUBE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              TIRE            FLAT            B      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      GL21350ND70                     2842179                                 ON LANDING, RT MAIN LANDING GEAR TIRE FLAT.  UPON DISASSEMBLY FOUND A SMALL SLIT IN THE OUTSIDE CIRCUMFERENCE OF THE TUBE.  HAVE FOUND MANY SIMILAR SLITS IN OTHER FAILED TUBES FROM MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A13    E274                 
20080403000642008040300064    2008       4          3          2008FA0000177    120080229G61005038004811      RELAY                                                                      PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL                  BURNED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15964LB                                                               UPON LANDING A POWER/ TORQUE SURGE OF THE LT ENGINE WAS ENCOUNTERED.  THE INCREASED THRUST FROM THE LT SIDE AND ICE COVERED RUNWAY CONDITIONS CAUSED AN OFF RUNWAY INCURSION.  INVESTIGATION OF THE GROUND FINE SOLENOID SYSTEM RESULTED IN A BURNED K4 RELAY ON THE AFFECTED PC CARD CONTROLLING THE GROUND FINE SYSTEM ON THE LT SIDE.                                                                                                                                                                                                                                                                                                                                                                                                               4  T          E4EA    6  CP56GL    
20080403000652008040300065NM  2008       4          3          2008FA0000179    120080229G5712                RIB                                     UNIVAR415   415E        0420308NM  CONT  C85   C85*        17008SO                              RT WING         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW0587346                       519                                     COMPLIANCE WITH AD 2002-26-02 DETECT AND CORRECT CORROSION IN WING CENTER SECTION.  FOUND 5 RIVETS CORRODED OFF THE LOWER CENTER RIB ON THE RT WING WALKWAY BOX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  A787    E233                 
20080403000892008040300089CE  2008       4          3          2008FA0000180    120080229G323265412045        STUD                                    CESSNA501   501         2076603CE                                                               LT MLG ACTUATOR BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      SO09793AA                       5010106                                 LT MLG ACTUATOR TO GEAR STUD BROKEN OFF AT BASE OF THE NUT ON THE TAPER SIDE, NUT AND WASHER SET MISSING AND STUD WAS NOT TIGHT IN THE GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4F      A27CE                        
20080403000912008040300091SO  2008       4          3          2008FA0000181    220080304G8530AEC633099       PISTON                                  BEECH 35    B35         1151506CE  CONT  E225  E2258       17015SO                              ENGINE          FAILED          G      A   UNSCHED LANDING                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CE07                            D3633       03593D58                    NR 6 PISTON DISINTEGRATED.  CAUSE UNKNOWN.  PISTON P/N AEC633099 WAS ORIGINALLY MANUFACTURED BY AIRMOTIVE ENGINEERING, INC.(AEC).  ENGINE COMPONENTS, INC. (ECI) HAS SINCE BOUGHT OUT AEC.  ECI HAS NOT PRODUCED THIS P/N.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A777    E267                 
20080403000962008040300096NE  2008       4          3          2008FA0000183    220080304G7250304997801       TURBINE                                 BEECH 200   B200        1152922CE  PWA   PT6   PT6A42      52043NE                              ENGINE          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP19185XP4837 1771              BB952       93220                       DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIME IN SERVICE SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETURN TO SERVICE.  IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 6 O'CLOCK POSITIONS.  NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE.  SEVERAL CRACKS WERE ALSO NOTED IN THE OUTER SECTION OF THE COMBUSTION LINER.  AFFECTED COMPONENTS WILL BE SENT TO A P&WC APPROVED REPAIR FACILITY FOR REPAIRS OR REPLACEMENT AS NECESSARY.                                                                                  1L72 4T4  T  A24CE   E4EA                 
20080414000022008041400002NE  2008       4          14         2008FA0000184    220080304G7230304997801       COMPRESSOR                              BEECH 200   B200        1152922CE  PWA   PT6   PT6A42      52043NE                              RT ENGINE       DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP19185XP4837 1771              BB952       93220                       DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIS SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETURN TO SERVICE.  IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 6 O'CLOCK POSITIONS.  NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE.  SEVERAL CRACKS WERE ALSO NOTED IN THE OUTER SECTION OF THE COMBUSTION LINER.  AFFECTED COMPONENTS WILL BE SENT TO A MFG APPROVED REPAIR FACILITY FOR REPAIRS OR REPLACEMENT AS NECESSARY.                                                                                               1L72 4T4  T  A24CE   E4EA                 
20080403000982008040300098CE  2008       4          3          2008FA0000186    120080306G7120051351119       MOUNT BRACKET                           CESSNA172   R172K       2072431CE                                                               LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15758PX                       R1723262                                FOUND UPPER LT ENGINE MOUNT BRACKET CRACKED WHILE INSPECTING FOR CESSNA SEB07-2 REV 2.  THIS SERVICE BULLETIN DOES NOT APPLY TO THIS SERIAL NUMBER, ALTHOUGH A CRACK WAS FOUND.  RECOMMEND INCREASING THE SERIAL NUMBER RANGE OF AFFECTED AIRCRAFT.  THIS SHOP HAS ALSO NOTED SEAPLANES HAVE A DIFFERENT LOWER MOUNT BRACKET THAN THAT WHICH IS CALLED OUT IN THE SERVICE BULLETIN.  RECOMMEND INCLUDING THE PROPER SEAPLANE MOUNT BRACKET NUMBERS FOR AIRCRAFT SO EQUIPPED.                                                                                                                                                                                                                                                                    1H71 3O      3A17                         
20080410002032008041000203SO  2008       4          10         2008FA0000187    120080402G8097767391          SOLENOID                                PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              STARTER         SHORTED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21350ND                       2842179                                 DURING PRE-FLIGHT WHEN MASTER SWITCH WAS TURNED ON, THE PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO FUSED STARTER SOLENOID. THIS IS THE SECOND SOLENOID FAILURE OF THIS TYPE IN ONE WEEK TIME, SAME MODEL AIRCRAFT. REPLACED WITH NEW PART, OPS CHECKED GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A13    E274                 
20080404000062008040400006CE  2008       4          4          2008FA0000188    120080310G32332000300003      ACTUATOR                                LEAR  45    45LEAR      5170805CE  PWA   JT12  JT12A8      52042NE                              LT MLG          BYPASSING       D      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                CLCLIMB          1                      CE09828CA3137                   159                                     LT MLG ACTUATOR BYPASSING ON RETRACTION CAUSING INTERFERENCE WITH IB DOOR ROLLERS. NO EXTERNAL FAILURE INDICATION. UPON TEARDOWN, IT WAS DISCOVERED THAT THE CYLINDER WAS SCRATCHED AND THE PISTON SEAL WAS DAMAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  JRTT00008WI1E9                  
20080410002312008041000231EA  2008       4          10         2008FA0000190    220080313G7322                NUT             PREAIR                  PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUEL SERVO      LOOSE           C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13283PA     263   62760       2844059                                 AD 2008-06-51 IS NOT APPLICABLE DUE TO THE ENGINE AND FUEL SERVO WERE OVERHAULED BY MFG ON MARCH 03, 2006 (OUTSIDE THE DATE RANGE OF THIS AD).  HOWEVER, WE DECIDED TO CHECK ALL OF OUR AIRCRAFT AND DURING THIS INSPECTION FOUND THE HEX NUT WAS LOOSE ON THIS PARTICULAR SERVO.                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    1E10                 
20080410002352008041000235EA  2008       4          10         2008FA0000191    220080331G732230802           FLOAT           PREAIR      MA45        MAULE M7235 M7235C      5460110SO  LYC   O540  O540B4B5    41532EA                              CARBURETOR      BENT            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01249RD439        75103715    25069C      L2571940A                   CARBURETOR FLOAT PN 30-802 PLASTIC FLOAT, THE CARBURETOR HAD A HIGH FLOAT LEVEL TWICE AFTER SETTING THE FLOAT TO SPEC IAW MM. THE FLOAT WAS REMOVED DUE TO THE FLOAT LEVER TANG WAS BENDING UNDER NORMAL USE CONTACTING THE NEEDLE VALVE AND RESULTING IN A HIGH FLOAT LEVEL AND ROUGH RUNNING ENGINE. IT WAS NOTICED THAT THE FLOAT LEVER TANG ON THE PLASTIC FLOAT PN 30-802 MADE OF STAINLESS STEEL IS ABOUT .5 THE THICKNESS THAT OF THE BRASS FLOAT PN 30-764 WHICH HAS HAD NO PROBLEMS WITH THE LEVER TANG BENDING IN NORMAL USE. A PN 30-764 FLOAT WAS INSTALLED AND ENGINE WAS NORMAL, NO ROUGHNESS NOTED.  PLEASE LOOK IN TO THIS PROBLEM SO AS NO ONE HAS A ROUGH AND RICH RUNNING ENGINE DUE TO THIS PROBLEM AND POSSIBLE EARLIER THA1H71 3O3  ONC3A23    E295                 
20080410002412008041000241SO  2008       4          10         2008FA0000192    120080218G32309582900         LINK ASSY                               PIPER PA34  PA34200     7103405SO  LYC   O360  IO360A1A    41514EA                              NLG             SHEARED         G      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      EA171031U                       347250012                               ACFT EXPERIENCED A NLG COLLAPSE UPON LANDING.  INSPECTION OF ACFT, NLG DOWNLOCK LINK ASSY FOUND SHEARED NEAR ATTACHMENT TO DOWNLOCK ASSY BODY.  IT IS NOT KNOW WHAT CAUSED THIS LINK ASSY TO SHEAR.  DETERMINED THAT NOT ALL THE REQUIREMENTS OF AD 2005-13-16 WERE ACCOMPLISHED DURING THE LAST ANNUAL, AND IT IS POSSIBLE THIS COULD HAVE BEEN A CONTRIBUTING FACTOR.  NUMEROUS COMPONENTS OF THE NLG REQUIRE MX ACTIONS & REPETITIVE INSPECTIONS.  FRACTURE MODE OF SHEARED ASSY COULDN`T DETERMINE IF PART FAILED INSTANTANTLY OR PROGRESSIVELY, SIGNATURE SUGGESTS A FATIGUE FRACTURE MAY HAVE BEEN PRESENT. AD2005-13-16 ADDRESSES CONCERNS THAT HAVE RESULTED FROM SDR`S RELATED TO THE COLLAPSE OR INVOLUNTARY RETRACTION OF THE NLG ON 1L72 3O3  O  A7SO    1E10                 
20080410002442008041000244SO  2008       4          10         2008FA0000193    120080321G5720902010XXX       SUPPORT BRACKET GRUMAV                  AMRGENAA5   AA5A        3960106SO                                                               ZONE 600        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15     2850 100               SERIES                                  WHILE COMPLYING WITH AD 79-22-04 ON AILERON CONTROL SYS INSP AND SB 165A, 100 HOUR REPETITIVE INSP, FOUND LT OB AILERON HINGE SUPPORT BRACKET, 902010-501 CRACKED. CRACKED VISUALLY SEEN WITH OUT DISASSEMBLY USING A STRONG LIGHT AND SYSTEM LOADING.  HOWEVER, WHEN REMOVED FOR REPLACEMENT WITH NEW SUPPORT, THERE WERE 3 ADDITIONAL CRACKS GIVING A TOTAL OF (4) ON THIS COMPONENT, PAINT AND LOCATION OF CRACKS PRACTICALLY IMPOSSIBLE TO DISTINGUISH WITH COMPONENT INSTALLED.                                                                                                                                                                                                                                                            1L71 3O      A16EA                        
20080404000102008040400010NM  2008       4          4          2008FA0000194    120080319G8120                PIPE                                    COLUMBLC40  LC40550FG3005150010NM  CONT  O550  TSIO550C         SO                              TURBOCHARGER    CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA211024Z438        1CF730011   41097       802744                      RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  ONTA00003SEE5SO                 
20080404000042008040400004EA  2008       4          4          2008FA0000195    220080229G732025244509        FUEL CONTROL                            PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360C1C6   41514EA                              ENGINE          LOOSE           C      D   RETURN TO BLOCK                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      GL11540PU2900 695               2844096     L3103051A                   RAN ENGINE AFTER INSPECTION AND FOUND FUEL FLOW AT TO POWER SETTING TO BE QUITE LOW.  INVESTIGATED AND FOUND PLUG LOOSE ON SIDE OF INJECTION SERVO.  CONTACTED ENGINE SHOP FOR FIX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O  2A13    1E10                 
20080414000122008041400012EA  2008       4          14         2008FA0000197    220080321G8530                CYLINDER                                PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA  HARTZLHCE2Y HCE2YR2     GL  NR 3            SEPARATED       C      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      EA21     126                    277554157   RL77048     HCE2YR2KBS      NR 3 CYLINDER SEPARATED FROM ENGINE CASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  1A10    1E4     5  CP9EA     
20080414000082008041400008SO  2008       4          14         2008FA0000198    220080318G8530SA530348P15     PISTON                                  CESSNA150   150D        2071810CE  CONT  O200  O200A       17020SO                              NR 3 CYLINDER   CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE016029T885                    15060729                                REMOVAL OF NR 3 CYLINDER FOR REPLACEMENT REVEALED A 1.5 INCH CRACK IN THE UPPER PISTON SKIRT STARTING FROM THE BOTTOM OF THE PISTON. 885 HOURS SINCE NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  3A19    E252                 
20080414000062008041400006SO  2008       4          14         2008FA0000199    220080318G8500                CASE                                    CESSNA421   421C        2076016CE  CONT  O520  GTSIO520L   17032SO                              RT ENGINE       CRACKED         B      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      WP0912RJ 1748 937               421C0306    292115R                     REMOVED THIS ENGINE FROM THE RT POSITION FOR SHIPMENT BACK TO RAM AC DUE TO A DAMAGED CASE.  DAMAGE APPEARS TO BE CAUSED BY A FAILED CONNECTING ROD THAT BROKE APART AND PUNCTURED (2) LARGE HOLES IN THE CRANKCASE.  BRIEF ENGINE HISTORY: 347 HOURS PRIOR TO THE FAILURE THE ENGINE DEVELOPED AN OIL LEAK FROM A HAIRLINE CRACK IN THE RT CASE. THE ENGINE WAS SHIPPED TO RAM WHERE IT WAS DISASSEMBLED, CLEANED AND INSPECTED BEFORE GETTING REASSEMBLED USING A SERVICEABLE CRANKCASE, NEW CAMSHAFT, LIFTERS, MAIN AND ROD BEARINGS.                                                                                                                                                                                                        1L72 3O3  O  A7CE    E7CE                 
20080414000092008041400009SO  2008       4          14         2008FA0000200    220080318G8530                CYLINDER                                CESSNA150   150D        2071810CE  CONT  O200  O200A       17020SO                              NR 1            CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE016029T     885               15060729                                MUFFLER PRESSURE TEST REVEALED CRACKS IN NR 1 CYLINDER EXHAUST PORT, FWD SIDE. UNKNOWN CYLINDER TIME, WAS BORED .015 INCH OVERSIZE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A19    E252                 
20080414000072008041400007CE  2008       4          14         2008FA0000201    120080318G7820                FLAME TUBE      CESSNA                  CESSNA150   150D        2071810CE  CONT  O200  O200A       17020SO                              MUFFLER         RUPTURED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE016029T3900                   15060729                                RT MUFFLER P/N 0450400-26 WAS REMOVED FOR CYLINDER REPLACEMENT, INSP REVEALED DETERIORATED FLAME TUBES IN OUTLET PIPE AND NR1 INLET PIPE. OUTLET PIPE FLAME TUBE IS NOT READILY VISIBLE LOOKING UP TAIL PIPE. NO ENTRIES IN LOGBOOK INDICATING REPLACEMENT OF EITHER MUFFLER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A19    E252                 
20080414000182008041400018CE  2008       4          14         2008FA0000202    120080328G7120                MOUNT                                   CESSNA172   172D        2072410CE                                                               ENGINE          WRONG PART      C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      WP21                                                                    AN UNKNOWN AMOUNT OF AC FIREWALL ATTACH ASSEMBLIES (ENGINE MOUNTS) THAT WERE NOT FAA-PMA APPROVED. THE MIDO ATTEMPTED TO CONTACT THE OWNER OF MFG CONCERNING THIS MATTER, HOWEVER, ALL PHONE CALLS WERE NOT RETURNED, AND CERTIFIED LETTERS NOT ACCEPTED. AS OF THIS TIME, THE COMPANY HAS CLOSED DOORS, HOWEVER, A FIREWALL ASSEMBLY WAS FOUND ON AC. THE OWNER OF THE AIRCRAFT WAS ADVISED THAT THE PART WAS NOT APPROVED AND IT HAD TO BE REMOVED. THE MIDO WAS INFORMED OF THE UNAPPROVED MOUNT. THE MOUNT DOES NOT HAVE A PART NUMBER. THE MIDO WILL CONTACT THE FAA SUP OFFICE TO PUT OUT A NOTICE. RECOMMEND THAT INFORMATION BE DISSEMINATED TO THE AC MFG COMMUNITY TO ADVISE OWNERS, PILOTS, AND MECHANICS IF THEY HAVE ANY OF THESE M1H71 3O    NT3A12                         
20080408000012008040800001SW  2008       4          8          2008FA0000203    120080320G801114912LS         STARTER                                 MOONEYM20   M20F        5870214SW  LYC   O360  IO360A1A    41514EA  HARTZLHCC2Y HCC2YK1     GL  ENGINE          FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059615M     62                670192      L189451     CH388859B       THIS STARTER WAS PURCHASED NEW FROM A LOCAL VENDOR.  THE STARTER FAILED TO OPERATE AFTER LESS THAN A YEAR AND LESS THAN 100 HOURS OF SERVICE. THE OWNER\OPERATOR WANTED TO HAVE THE OLDER, HEAVIER STARTER INSTALLED HOWEVER NONE WERE AVAILABLE, AFTER CONTACTING SEVERAL PARTS VENDORS. THE OPERATOR OPTED TO HAVE THE STARTER REPAIRED BY THE MFG. THE REPAIRED STARTER WAS INSTALLED BUT FAILED AGAIN SEVEN MONTHS AND 62.3 OPERATING HOURS LATER. A SERVICABLE STARTER WAS LOCATED AND INSTALLED IAW ENGINE SERVICE INSTRUCTION 1154L DATED JANARY 27, 2006.  OUR SHOP RECOMMENDED THIS CHANGE DUE TO A TREND WE ARE SEEING IN THE LIGHT WEIGHT STARTERS. WE HAVE SEEN AT LEAST 6 FAILURES OR THE STARTER DRIVE GEAR EITHER FAILING TO ENGA1L71 3O3  O  2A3     1E10    5  CP920     
20080414000102008041400010NM  2008       4          14         2008FA0000206    120080319G8120654327E         TURBOCHARGER                            COLUMBLC40  LC40550FG3005150010NM  CONT  O550  TSIO550C         SO                              RIGHT           CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21     438                    41097       802744                      RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  ONTA00003SEE5SO                 
20080414000192008041400019SO  2008       4          14         2008FA0000208    120080328G29101159SCH2393     SHUTOFF VALVE                           GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6108          NE                              HYD SYSTEM      SEIZED          C      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      GL23312EL7509                   1105                                    WHILE AT CRUISE ALTITUDE, THE COMBINE HYDRAULIC SHUTOFF VALVE FAILED TOWARD CLOSED POSITION WHICH IS INDICATED IN THE COCKPIT ON THE EICAS WITH DASHED LINES (VALVE IN TRANSITION) THUS TAKING AWAY YOUR HYDRAULIC PRESSURE INDICATION.  WHEN THE VALVE IS FULLY CLOSED THE INDICATION ON THE EICAS IS DIAGONAL SOLID LINES.  THE ONLY WAY TO GET THIS VALVE TO MOVE CLOSED IS WITH THE FIRE L HANDLE.                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA12EA   E25NE                
20080414000362008041400036EA  2008       4          14         2008FA0000209    220080401G7414M11522          BREAKER POINTS  SLICK       6393        PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA                              MAGNETO         WORN            E      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      EA1762BA 87         0700226     274859      L1947848A                   ENGINE BECAME INCREASINGLY DIFFICULT TO START, CHECKED IGNITION TIMING AND FOUND LT MAGNETO OUT OF TOLERANCE. INSPECTED LT MAGNETO, POINTS FAILED TO OPEN DUE TO EXCESSIVLY WORN BREAKER POINT CAM. 87 HOURS SINCE NEW                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  1A10    1E4                  
20080414000132008041400013SO  2008       4          14         2008FA0000210    120080325G8011701122223       SOLENOID                                PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              STARTER         STICKS          B      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL21245ND                       2842086                                 WHEN BATTERY MASTER TURNED ON PROP BEGAN ROTATING UNCOMMANDED. TROUBLESHOT TO FUSED STATER SOLENOID. REPLACED SOLENOID WITH NEW OEM PART PROBLEM PERSISTED.  NEW SOLENOID WAS STRUCK WITH A SIDE BLOW AND CONTACTS FREED. REPLACED WITH ANOTHER NEW OEM PART, PROBLEM CORRECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A13    E274                 
20080414000042008041400004SO  2008       4          14         2008FA0000211    220080312G8500654327E         DUCT                                    LANCARLC41  LC41550FG   5150001NM  CONT  O550  TSIO550A    41516SO                              ENGINE          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21     154                    41722       914564                      RT TURBO TRANSITION DUCT CRACKED. (NOTE: THIS IS THE SECOND TIME WE HAVE SEEN THIS)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ONTA00003SEE5SO                 
20080414000112008041400011EA  2008       4          14         2008FA0000212    220080319G7322383493          GASKET          PREAIR                  CESSNA206   206H        2073301CE  LYC   O540  IO540AC1A5       EA                              FUEL SERVO      UNKNOWN         D      K   NONE                                                                                            P  NO WARNING INDICATION                                                         ININSP/MAINT     1                      NM012446X           70A59005    20608097    RL3065348A                  INSPECTED FUEL SERVO PLUG IAW SBPRS-107, REVISION 1, DATED MARCH 6, 2008. NO DAMAGE FOUND ON THE THREADS OF THE PLUG OF THE SERVO UNIT. INSTALLED PLUG AND SAFETIED IAW INSTRUCTIONS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ORTA4CE    1E4                  
20080414000052008041400005CE  2008       4          14         2008FA0000214    120080207G3040FED2000         DEFOG SYSTEM                            LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              COCKPIT         BURNED          G      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      NM0160WL                        382                                     RIGHT AFTER TAKEOFF, AUX DE-FOG UNIT ON CO-PILOT SIDE BURNED AND SMOKE FROM BLOWER FAILURE. NO WIRE PROBLEMS OR CIRCUIT BREAKER ISSUES FOUND. UNIT FAILURE CAUSED SMOKE IN COCKPIT, CREW DECLARED EMERGENCY AND RETURNED TO AIRPORT WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A10CE   E6WE                 
20080410001862008041000186CE  2008       4          10         2008FA0000215    120080204G2800                NUT                                     CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA                              FUEL SERVO      LOOSE           B  Z08RA   UNSCHED LANDING                                                                                 O  OTHER                                                                         ININSP/MAINT     1                      CE07168JS302                    T20608735                               WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT ACCESS PLUG FINGER LOOSE.  ALSO, FOUND RED DYE INSIDE FUEL SERVO AIR CHAMBER.  THIS AC HAS HAD AN ISSUE WITH LEAN IDLE MIXTURE IN THE PAST.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED UP.  SUSPECT UNDERTORQUED FROM FACTORY AND RED DYE NOT FLUSHED FROM CHAMBER.  SENT TO OVERHAUL FACILITY TO HAVE CORRECTED AND PERFORMED THE REQUIREMENTS OF PRS-107 SB.  (K)                                                                                                                                                                                                                                                                                                                 1H71 3O3  ORTA4CE    E14EA                
20080410001702008041000170EA  2008       4          10         2008FA0000216    220080204G7200                NUT                                     CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          LOOSE           B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07227BH                       172S10662                               WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT PLUG FINGER LOOSE.  OTE: HEX NUT WILL BECOME LOOSE IF ENGINE IS WARMED UP.  SUSPECT UNDERTORQUED FROM THE FACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    1E10                 
20080410001842008041000184EA  2008       4          10         2008FA0000217    220080204G7320                SERVO                                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              FUEL SYSTEM     UNDERTORQUED    C  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07719JW                       172S10527                               WHILE PERFORMING SB PRS-107, FOUND PN 383493, HEX NUT PLUG FINGER LOOSE.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED UP.  SUSPECT UNDERTORQUED FROM FACTORY                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A12    1E10                 
20080410001932008041000193EA  2008       4          10         2008FA0000218    220080204G7300                SERVO                                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENG FUEL        LOOSE           B  Z08RK   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CE07452SM                       172S10528                               WHILE PERFORMING SB PRS-107 FOUND PN 383493 HEX NUT PLUG FINGER LOOSE.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED UP.  SUSPECT UNDERTORQUED FROM THE FACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    1E10                 
20080414000432008041400043SW  2008       4          14         2008FA0000219    120080205G2820                SELECTOR VALVE                          MOONEYM20   M20C        5870208SW  LYC   O360  O360*       41514EA                              FUEL SYSTEM     SEIZED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW096529U                       2312                                    FUEL SELECTOR VALVE SEIZED IN THE (OFF) POSITION DURING A ROUTINE FUEL TANK SWITCHOVER.  FAILURE CAUSED BY CORROSION ON SELECTOR VALVE SHAFT WHERE IT PASSES THROUGH THE UPPER VALVE HOUSING.  POOR DESIGN.  NO PROVISION MADE TO PREVENT SPILLED LIQUIDS OR MOISTURE FROM CARPET FROM ENTERING UPPER HOUSING VALVE SHAFT BORE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A3     E286                 
20080414000442008041400044CE  2008       4          14         2008FA0000220    120080222G270105131682        CONTROL WHEEL                           CESSNA172   172A        2072404CE  CONT  O300  O300*       17022SO                                              BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM0834264                       625                                     ON TAXI FROM REFUELING PILOT WAS MAKING A LT TURN IN FRONT OF HANGER.  PULLED CONTROL WHEEL FULL AFT (TO TAKE WEIGHT OFF OF FRONT WHEEL) CONTROL WHEEL BROKE OFF IN HIS HAND.  (OUTSIDE TEM APPROX 20 DEGREES) BREAK WAS FROM LWR LT (7 OCLOCK) TO UPPER RT (2 OCLOCK).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A12    E253                 
20080410002462008041000246EA  2008       4          10         2008FA0000221    120080220G7921269D45031       SCROLL                                  SCWZER269   269D        8059501EA  ALLSN 250C  250C20      03013GL                              OIL COOLER FAN  CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03411HU                       0040                                    UPON INSPECTION OF OIL COOLER FAN ASSY, FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U0 4H12    E4CE                 
20080410002052008041000205CE  2008       4          10         2008FA0000223    120080308G5753052390133       SKIN                                    CESSNA182   182M        2072728CE  CONT  O470  O470*       17026SO                              TE FLAP         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW01717845800 1200              18259755                                ON INSPECTION BOTH FLAPS RT AND LT TOP AND BOTTOM FLAP SKINS WERE CRACKED 6 TO 8 INCHES ALONG THE T/E, ON THE RIVET LINE.  ALSO SHEERED RIVETS ON (3) OF THE (4) FLAP TRACK LOWER TRACK TO RIBS.  RESKINNED FLAPS AND INSTALLED MS21042 STEEL SCREWS IN REPLACEMENT OF THE SHEERED RIVETS.  PROBABLE CAUSE BY FLAP OVERSPEED WITH HIGH G, LOADS.  THIS AIRCRAFT TOWS GLIDERS ALL THE TIME.  (K)                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A13    E273                 
20080410001942008041000194SO  2008       4          10         2008FA0000224    120080321G29101159SCH5197     SIGHT GLASS                             GULSTMGVSP  GVSPG550    3980203SO  RROYCEBR700 BR700710A110     NE                              HYD TANK        CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1557UH                        5163                                    SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID.  THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DEFECT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA12EA   E00057EN             
20080410002342008041000234NM  2008       4          10         2008FA0000225    120080401G8120654327          TRANSITION DUCT                         LANCARLC41  LC41550FG   5150001NM  CONT  O550  TSIO550C         SO                              TURBOCHARGER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP19431PC                       41050                                   DURING ANNUAL INSP FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ONTA00003SEE5SO                 
20080428002982008042800298SO  2008       4          28         2008FA0000226    120080321G29101159SCH5197     SIGHT GLASS                             GULSTMGIVX  GIVXG450    3980205SO  RROYCETAY   TAY6118          EU                              HYD SYSTEM      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA25612AF224                    4069                                    SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID, THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DEFECT.   (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA12EA   E25NE                
20080410002192008041000219SO  2008       4          10         2008FA0000227    120080225G321086262003        TUBE                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              MLG             WORN            D  UC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL195341Z2193                   4496107                                 NOSE GEAR DOOR TUBE PN 86262003 FOUND WITH GROOVE WORN INTO TUBE AT APPROX 65 PERCENT OF TUBE THICKNESS IN THE AREA OF THE LT AND RT SUPPORTS PN 86262-005 AND 86262-012 RESPECTIVELY.  THIS TUBE CONNECTS TO THE LT AND RT NOSE GEAR DOOR RODS AND PIVOTS AS THE GEAR IS RAISED AND LOWERED AND IT IS AT THE PIVOT POINT OF THE TUBE WHERE THIS WEAR IS OCCURRING.  CURRENTLY THERE IS A NYLON BUSHING PN 452647 THAT IS INSERTED AT THIS PIVOT POINT TO PROVIDE FOR SOME PROTECTION OF THE TUBE.  THERE IS HOWEVER, NO WEAR TO THIS NYLON BUSHING.  IT CAN BE ASSUMED THAT THIS NYLON BUSHING IS THE CAUSE OF THE WEAR AND PROVIDES NO GUARD AGAINST PROTECTING THE INTEGRITY OF THE TUBE.  CURRENTLY THERE IS NO REQUIREMENT FOR LUBRICATION 1L72 3O3  O  A19S0   E286                 
20080414000532008041400053SO  2008       4          14         2008FA0000229    120080408G8011701122223       SOLENOID                                PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              STARTER         STICKS          B      H   DEACTIVATE SYST/CIRCUITS                                                                        S  AFFECT SYSTEMS                                                                TXTAXI/GRND HDL  1                      GL21436ND3478                   2842213                                 AFTER START, STARTER ANNUNCIATOR DID NOT EXTINGUISH. ENGINE SHUTDOWN WITH MIXTURE BUT CONTINUED TO CRANK OVER WITH MASTER TURNED ON. TROUBLESHOOTING REVEALED STARTER CONTACTOR STUCK CLOSED. WHEN STRUCK CONTACTS WOULD OPEN BUT WHEN POWER APPLIED WOULD STICK CLOSED UNTIL STRUCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  2A13    E274                 
20080414000582008041400058SW  2008       4          14         2008FA0000230    120080331G2731                CONTROL TUBE                            ECLIPSEA500 ECLIPSEEA5003350000SW                                                               PITCH TRIM      OUT OF ADJUST   B  CJ6RC   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      GL03875NA                       000018                                  AC EXPERIENCED A PITCH TRIM MALFUNCTION ON TAKEOFF ACCOMPANIED BY A WARNING MESSAGE.  AN EMERGENCY WAS DECLARED AND THE AC WAS RETURNED TO BASE.  PROBLEM WAS DUPLICATED ON THE GROUND.  AFTER TROUBLESHOOTING, IT WAS DETERMINED THAT A REPLACEMENT ACTUATOR SHOULD BE INSTALLED.  AFTER INSTALLING NEW PART, DEFECT STILL EXISTED.  FURTHER TROUBLESHOOTING REVEALED THAT THE CONTROL TUBES CONNECTED THE ACTUATOR TO THE CONTROL SURFACE WERE NOT SIMILARLY ADJUSTED.  THIS CONDITION CAUSED A BINDING OF THE SYS MECHANICS AND THE SUBSEQUENT FAILURE.  WHEN THE CONTROL TUBES WERE SIMILARLY ADJUSTED, THE SYSTEM OPERATED CORRECTLY ON GROUND AND IN SUBSEQUENT OPERATIONAL CHECK FLIGHT.  (K)                                            1L72 4J    RTA00002AC                     
20080414000602008041400060CE  2008       4          14         2008FA0000231    120080331G2820                LINE                                    CESSNA182   182P        2075816CE  CONT  O470  O470*       17026SO                              GAS COLATOR     LEAKING         C      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      SO0320935                       18261306                                FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS).  FUEL LEAKING FROM GAS COLATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONTTA13    E273                 
20080414000612008041400061WP  2008       4          14         2008FA0000232    120080331G2621130835          CARTRIDGE                               DOUG  DC3   DC3CR183090C3021466WP  PWA   PT6   PT6*        52043EA                              FIRE BOTTLE     FAILED          G  VWBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13300BF           03692C1     26744                                   THE FIRE BOTTLE WAS BEING DISCHARGED FOR AN OVERHAUL.  THE CARTRIDGE FIRED BUT DID NOT DISCHARGE THE BOTTLE.  SUSPECT IMPROPER SETUP OF CARTRIDGE IN BOTTLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4R3  T  A669    E2NE                 
20080414000622008041400062EA  2008       4          14         2008FA0000233    220080318G8530IO360AV         CYLINDER                                MOONEYM20   M20E        5870212SW  LYC   O360  IO360A1A    41514EA  HARTZLHCC2Y HCC2YR1     GL  ENGINE          WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0779337                       547                     CH42539B        PILOT REPORTED PARTIAL POWER LOSS ON TAKEOFF.  ENG INSP REVEALED THE FOLLOWING DISCREPANCIES AND CORRECTIONS AS NOTE: CYL NR 1 HAD BAD INTAKE VALVE SEAT WITH EXCESSIVE WEAR, AND FUEL INJECTOR AIR SCREEN CONTAMINATED.  THIS POSSIBLY CAUSED CYL TO BURN LEAN AND CAUSED EXCESSIVE WEARING ON VALVE SEAT.  THIS IN TURN WOULDNT ALLOW THE INTAKE VALVE TO CLOSE PROPERLY, CRATING ROUGH ENG RUNNING AND OCCASIONAL BACK-FIRING.  COMPLETE STUD ASSY WAS REPLACED WITH REBUILT ASSY SN 162, UNDER WO 032608AA.  CYL NR 4 HAD EXCESSIVE ROCKER ARM SIDE CLEARANCE.  ROCKER ARM SIDE CLEARANCE WAS RESHIMMED AS SERVICE INSTRUCTIONS IN SB NR 225B BY ADDING ADDITIONAL SHIMS TO BRING ROCKER ARM SIDE.                                         1L71 3O3  O  2A3     1E10    5  CP920     
20080414000642008041400064SO  2008       4          14         2008FA0000234    120080307G7160                VALVE                                   MAULE M4    M4210C      5460112SO  CONT  IO360 IO360*      17025CE                              ALT AIR VALVE   BROKEN          G      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      WP1151430                       1097C                                   THE ENG AUTOMATIC ALTERNATE INDUCTION AIR VALVE THAT IS PARTIALLY LOCATED INSIDE THE CYLINDRICAL PAPER INDUCTION AIR FILTER CAME APART AND SOME OF ITS PART (2 INCH LONG, .2500 INCH DIAMETER BOLT.  2 INCH LONG SPIRAL SPRING WASHER, AND COTTER PIN) WERE INGESTED INTO THE ENGINE INTAKE MANIFOLD, ENG CYL VALVES AND THE ENG CYL.  THIS CAUSED A MAJOR LOSS OF POWER AFTER TAKEOFF, THE PILOT WAS ABLE TO GET BACK TO THE RUNWAY, BUT HE GROUND LOOPED THE AIRPLANE CAUSING AN ACCIDENT DUE TO SUBSTANTIAL DAMAGES TO THE AIRPLANE.  POST ACCIDENT INVESTIGATION FOUND THAT AT AN EARLIER DATE THE PREVIOUS OWNER HAD DISASSEMBLED THE ALTERNATE AIR VALVE TO PAINT IT AND HE MAY HAVE IMPROPERLY REINSTALLED THE COTTER PIN INTO THE CASTEL1H71 3O3  O  3A23    E1CE                 
20080414000652008041400065CE  2008       4          14         2008FA0000235    120080301G2510MS27039116      SCREW                                   CESSNA182   R182        2072734CE  LYC   O540  O540*       41532EA                              UNDER REAR SEAT IMPROPER PART   D  LN7RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA13757XU                       R18201273                               MFG SB NR SEB07-3 TO CHECK THE LENGTH OF THE SCREWS IN ACCESS PLATE UNDER REAR SEAT.  THE PLATE MAY HAVE HAD TOO LONG A SCREW INSTALLED WHICH COULD CAUSE A FAILURE OF THE LANDING GEAR TO OPERATE DOWN.  THE SB LISTED THE PROPER SCREWS TO USE IN EACH HOLE IN THE PLATE.  THE SCREWS LISTED ARE THE ONES IN THE PARTS CATALOG.  THOSE ARE THE SCREWS THAT ARE TOO LONG.  IF ANYBODY PUT IN THE PROPER LENGTH SCREW, (MS27039-1-12), THEN THE AC WOULD BE LESS SAFE AFTER COMPLYING WITH THE SB.  THE PLATE NEEDS 17 EA MS27039-1-12, AND 1 MS27039-1-09.  (K)                                                                                                                                                                                1H71 3O3  ORT3A13    E295                 
20080414000662008041400066EU  2008       4          14         2008FA0000236    120080227G32225322012039      PIN                                     PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE                              NLG STRUT       MISMANUFACTURED B  Z4MRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP27672SD                       666                                     DURING NOSE STRUT RESEALING, TORQUE LINKS WERE REMOVED.  BEFORE REASSEMBLY THE PINS WERE CHECKED TO VERIFY GREASE WOULD PASS THROUGH.  GREASE WOULD PASS THROUGH THE LOWER BUT NOT THE UPPER (UPPER AND LOWER PINS THAT CONNECT THE TORQUE LINKS TO THE GEAR ARE THE SAME PN).  AFTER CLEANING, FOUND THAT THE UPPER PIN COUNTER BORE ONLY WENT PART WAY THROUGH THE PIN.  (K)                                                                                                                                                                                                                                                                                                                                                                  1L71 3T4  TRTA78EU   E26NE                
20080414000672008041400067NE  2008       4          14         2008FA0000237    120080221G64107610105017045   SPAR                                    SKRSKYS76   S76B        8143007NE  PWA   PT6   PT6*        52043EA                              T/R BLADE       CRACKED         C  CW1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA11780P 2905                   760359                                  DURING A ROUTINE INSP A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE.  BLADE ASSY PN 761005501042, SN A245-00153 WAS REMOVED FOR PRECAUTIONARY MEASURES SENT FOR INSPECTION/ EVALUATION. UPON DISASSEMBLY AND INSPECTION SPAR WAS FOUND TO HAVE CRACKS COMING FROM ELLIPTICAL PLUG AREA.  SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURNED TO SERVICEABLE CONDITION.  SCRAPED SPAR.                                                                                                                                                                                                                                                                                                                             1G72 4U3  T  H1NE    E2NE                 
20080414000762008041400076GL  2008       4          14         2008FA0000238    120080227G341151815001        BUSHING                                 CIRRUSSR    SR20        05628AJGL  CONT  IO360 IO360*      17025CE                              REDUCER         INCORRECT       C  LN7RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA13362HE                       1263                                    STATIC SYSTEM FAILED LEAK CHECK DURING 2 YEAR STATIC SYS IFR CERTIFICATION, LEAKS WERE CAUSED BY REDUCED BUSHING FAILING TO SEAL STATIC LINE SUMP.  (ON BOTH SIDES, PILOT AND COPILOT).  TO REPAIR THE LEAKAGE, PIPE THREAD TAPE (TEFLON TAPE) WAS USED ON THE REDUCER BUSHING BEFORE MATING IT WITH THE STATIC LINE SUMP.  THE TYPE OF THREAD ON THESE ITEMS SHOULD NOT REQUIRE TEFFLON TAPE TO SEAL.  SB 2X-34-22R1 (REVISED 10 OCT 2006) STEP L (FOR KIT 701164-001) STATES (APPLY THREAD SEALANT TO ALL MALE PIPE THREAD FITTINGS PRIOR TO STATIC LINE SUMP ARE NOT PIPE THREAD, AND THEREFOR WERE NOT (TAPED).  RECOMMEND CHANGING PROCEDURE TO STATE (APPLY THREAD SEALANT TO ALL MALE FITTINGS PRIOR TO ASSY).  (K)                      1L71 3O3  ONTA00009CHE1CE                 
20080414000932008041400093WP  2008       4          14         2008FA0000239    120080115G6410MHS54896        NUT                                     HUGHES369   369E        4470707WP                                                               TAIL ROTOR BLADESPLIT           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM119460T                       0238E                                   ON FINAL TORQUE OF TAIL ROTOR BLADES RETENTION BOLT, NEW NUT SPLIT PRIOR TO ACHIEVING TORQUE.  NEW NUT, IS THINNER AND LIGHTER STRENGTH THAN PREVIOUSLY MFG OLDER PN.  NEW BOLTS ALSO REQURIE A NEW HIGHT TORQUE VALUE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U      H3WE                         
20080414000942008041400094EA  2008       4          14         2008FA0000240    220080307G8520                BOLT                                    BEECH 80    65B80       1152812CE  LYC   O540  IGO540B1A   41532EA                              CONNECTING ROD  FAILED          G  KZ5RA   UNSCHED LANDING                                                                                 RYJPARTIAL RPM/PWR LOSS      ENGINE STOPPAGE           WARNING INDICATION        CRCRUISE         1                      GL15103BA                       LD435                                   NR 1 ENGINE SHUTDOWN IN FLIGHT.  SUSPECTED NR 7 CONNECTING ROD BOLT FAILURE.  CAUSING CYL SEPARATION FROM CASE AND CRANK CASE CRACK.  AC LANDED SAFELY WITHOUT OTHER DAMAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A20    1E11                 
20080414000632008041400063EU  2008       4          14         2008FA0000241    220080409G8500                ENGINE                                  DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE1250299       EU                              LEFT            POWER LOSS      D      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      SO1549OTS                       42AC090     020201763                   AFTER TAKEOFF AND PULLING LANDING GEAR UP, LT ENGINE POWER REDUCTION TO 75 PERCENT FOR ABOUT ONE MINUTE AND POWER WAS RESTORED. THIS SAME ISSUE HAS BEEN INDUCTED TWICE IN LESS THAN 24 HRS. THERE IS NO FEDAC WARNINGS SHOWN ON SYS. A REPORT HAS BEEN SENT TO MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3I3  BRTA57CE   E00069EN             
20080414000982008041400098SO  2008       4          14         2008FA0000243    120080410G8120                TURBOCHARGER                            PIPER PA28  PA28R201T   7102813SO  CONT  O360  TSIO360FB   17025SO                              ENGINE          FOD             D      K   NONE                                                                                            C  F.O.D.                                                                        ININSP/MAINT     1                      SO0547550                       28R7703397  232784B                     TURBOCHARGER COMPRESSOR DAMAGED BY FOD INGESTED THROUGH THE ALTERNATE AIR DOOR. THIS DOOR IS ON TOP OF THE AIR FILTER BOX ALLOWING ANY OBJECT THROWN UP BY THE NOSE WHEEL TO ENTER THE INDUCTION SYSTEM WHEN THE DOOR IS ACTIVATED DURING PREFLIGHT CHECKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  2A13    E9CE                 
20080414000592008041400059CE  2008       4          14         2008FA0000245    120080409G2731                TRIM SYSTEM                             BEECH 90    C90A        1152911CE  PWA   PT6   PT6*        52043EA                              ELEVATOR        ICED            P      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      EA21200TR400                    LJ1067                                  WHEN THE AIRPLANE HAS SET ON THE RAMP IN THE RAIN, THEN TAKES OFF WITH A QUICK CLIMB TO COLDER TEMPERATURES AT ALTITUDE, THE ELEVATOR TRIM FREEZES. THE AUTOPILOT KICKS OFF BECAUSE IT IS UNABLE TO RESPOND. THE PILOT THEN HANDFLYS WITH THE ELEVATOR FORCE LOADED UP AND UNABLE TO TRIM.  WITH LITTLE NUDGES BACK AND FORTH ON THE TRIM WHEEL FOR ABOUT 10 MINUTES, THE SYSTEM BECOMES FREE.  EACH TIME I REPORT THIS TO MECHANICS, THEY INSPECT AND LUBRICATE THE SYSTEM AND REPORT EVERYTHING IS SATISFACTORY.  THIS WAS MY EXPERIENCE FROM 1984 TO 2005. THE PLANE WAS NORMALLY KEPT IN A HANGAR SO OCCURRENCES WERE INFREQUENT.                                                                                                           1L72 3T3  TRT3A20    E2NE                 
20080414001042008041400104EA  2008       4          14         2008FA0000246    220080411G8530                CYLINDER                                PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540*     41532EA                              NR 5            DAMAGED         D      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      GL21476EB1400 1400              317612059   L167768A                    NR 5 CYL EXHAUST VALVE BROKEN, SENDING THE HEAD OF THE VALVE THROUGH THE EXHAUST AND LODGING ITSELF INTO THE TURBOCHARGER, EXTENSIVE DAMAGE TO THE CYLINDER, PISTON, AND TURBO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A20SO   E14EA                
20080425000572008042500057CE  2008       4          25         2008FA0000247    120080131G324522X8007008      TUBE            CLEVELAND               CESSNA208   208B        2073701CE  PWA   PT6   PT6*        52043EA                              NOSE WHEEL      TORN            G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03694MA69                     208B0694                                PILOT REPORTED NOSE TIRE FLAT.  UPON DISASSEMBLY OF NOSE TIRE, FOUND MIDDLE SEAM ON OUTSIDE OF TUBE, TORN/SPLIT, APPROX 1 INCH IN LENGTH. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3T3  T  A37CE   E2NE                 
20080417000242008041700024CE  2008       4          17         2008FA0000248    120080204G3260                THROTTLE SWITCH                         CESSNA210   210J        2073439CE  CONT  O520  IO520*      17032SO                              COCKPIT         INTERMITTENT    D      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      EA231333T                       T21059108                               GEAR WARNING HORN WAS INOPERATIVE.  AC LANDED WITH LANDING GEAR UP.  SUBSEQUENT INVESTIGATION DETERMINED THROTTLE MICROSWITCH WAS MAKING INTERMITTENT CONTACT WHEN ENGAGED AND GROUND CONNECTION WAS INSUFFICIENT.  CORRECTED BY REPLACING SWITCH AND REPAIRING GROUND CONNECTION.  HORN OPERATION SHOULD BE CHECKED VIA TEST FEATURE DURING PREFLIGHT.  (K)                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A21    E5CE                 
20080425000692008042500069CE  2008       4          25         2008FA0000249    120080207G3233MS28775112      SEAL                                    CESSNA172   172RG       2072438CE  LYC   O360  O360*       41514EA                              NLG ACTUATOR    LEAKING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO116562V                       172RG0775                               AFTER REPEATED TOUCH AND GO PROCEDURES, THE AC FAILED TO RETRACT THE LANDING GEAR DUE TO A LACK OF HYDRAULIC FLUID. THIS RESULTED IN A GEAR UP LANDING.  DURING THE ACCIDENT INVESTIGATION IT WAS DETERMINED THAT THE HYDRAULIC FLUID RESERVOIR WAS DEPLETED OF FLUID BY CYCLING THE LANDING GEAR.  THE NLG ACTUATOR WAS LEAKING STEADILY WHILE THE HYDRAULIC PUMP WAS CYCLING.  DAMAGE TO THE AC WAS LIMITED DUE TO THE PROPER EXECUTION OF EMERGENCY LANDING PROCEDURES.  THERE WERE NO INJURIES.  (K)                                                                                                                                                                                                                                        1H71 3O3  O  3A17    E286                 
20080425001062008042500106WP  2008       4          25         2008FA0000250    220080305G7200                ENGINE                                  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33110UG  01514WP  ROTOL R321  R321482F8   GL                  OVERHEATED      W  LY0FE   ENGINE SHUTDOWN                                                                                 MJ OVER TEMP                 WARNING INDICATION                                  CRCRUISE         1                      SO23139LC24465                  AC732       P44344      DRG856029       IN CRUISE TO 8000 FT, INDICATION OF RED LIGHT OF OIL PRESSURE WITH 870 DEGREE TEMPERATURE.  LIGHT TURNS OFF.  AFTER 15 SECONDS, THE LIGHT TURNS ON AGAIN WITH 870 DEGREE TEMPERATURE, BUT THE PRESSURE DOWN NEAR ZERO.  THE CREW  MADE THE SHUTDOWN ENGINE PROCEDURE.  LANDING WITHOUT NOVELTY. AT THE MOMENT THE ENGINE IS WAITING TECH INSPECTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA8SW    E4WE    6  CP61GL    
20080425001122008042500112CE  2008       4          25         2008FA0000252    120080305G8011                MOUNT                                   CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA                              STARTER         FAILED          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15214CE1                      T20608592                               ORIGINAL STARTER (TT 433.4) WAS REMOVED BECAUSE IT FAILED (SMELLED BURNED).  A REPLACEMENT WAS ORDERED FROM MFG AND INSTALLED.  CHANGED THE SPARK PLUGS AND CHECKED ENGINE TIMING, WHICH WAS FOUND GOOD.  AFTER INSTALLATION OF STARTER STARTED THE AC (5) TIMES AND OPS CHECKED GOOD.   2/29/2008 THE PILOT TRIED TO START THE ACFT AND HEARD A GROWLING SOUND.  OPENED THE COWLINGS AND FOUND THE STARTER MOUNT CRACKED THROUGH THE BELL HOUSING.  NOTIFIED MFG AND THEY ASSURED ME THIS WAS NORMAL WHEN AN AC HAS A KICKBACK.  THE PILOT STATED HE DID NOT HAVE A KICKBACK.  SENT THE STARTER FOR REPAIR AND WHEN RETURNED, INSTALL AND AGAIN CHECKED THE IGNITION SYS WITH NO ABNORMITIES FOUND.  STARTED THE AC (5) TIMES AND HAD THE OWNER1H71 3O3  ORTA4CE    E14EA                
20080425001272008042500127CE  2008       4          25         2008FA0000254    220080305G7310                SERVO                                   DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE  HARTZLHCC2Y HCC2YR1     GL  FUEL INJECTION  DAMAGED         D  U1VSK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07103UV687                    40683       L3284951A   CH40160B        WHILE PERFORMING A 100 HR INSP, THE TECH DISCOVERED FINE METAL PARTICLES COVERING THE THROAT AND VALVE OF THE FUEL INJECTION SERVO (2576568-1, SN 70B10709).  THE SERVO WAS SENT TO A REPAIR FACILITY TO DETERMINE WHETHER OR NOT ANY OF THE METAL PARTICLES ENTERED THE SERVOS BLAST TUBES.  IT HAS BEEN DETERMINED THAT THE METAL ORIGINATED FROM THE CHAFING OF THE LOOSE FITTING INLET RING (ITEM 220) WITHIN THE FLANGE (ITEM 20).  THE LOOSE FIT IS DUE TO MFG.  MFG HAS NOT COME UP WITH A FIX AS OF THIS DATE.  FOR NOW WE ARE CEMENTING THE INLET RING TO THE FLANGE WHILE AWAITING A PERMANENT FIX.                                                                                                                                   1L71 3O3  ONTA47CE   E1CE    5  CP920     
20080428003002008042800300CE  2008       4          28         2008FA0000256    120080321G252017001277        PANEL                                   CESSNA182   182Q        2072732CE  CONT  O470  O470*       17026SO                              CABIN           CORRODED        G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO099766015328                  18267161                                DURING AN AGING AC INSP OF FLEET AC, VEERING SEVERITY OF SURFACE CORROSION HAS BEEN FOUND IN AC CONTAINING SOUNDPROOFING PANELS SHOWN IN MFG IPC FIG 90.  THE HEAVIEST AND MOST SEVERE CORROSION WAS FOUND UNDER SOUNDPROOFING PANELS PN 07000762-23 ITEM 7, PN 1700127-7 AND -10, ITEMS 10 AND 13, PN 1200217-8, ITEM 14 AND 1200193-11, ITEM 15.  REMOVAL OF SURFACE CORROSION, CLEANING, BRIGHTING, AND ALODINING THE EFFECTED AREAS TO REMOVING OF COMPLETE SKIN PANELS TO RESTORE STRUCTURAL INTEGRITY OF THE AC.  PROBABLE CAUSE IS THE MFG TO PROVIDE A SUITABLE CORROSION BARRIER TO PROTECT THE AC STRUCTURAL INTEGRITY AND THE SKIN PANELS BEING EXPOSED TO CHEMICAL ACTION OF THE ADHESIVES USED TO ATTACH THE SOUNDPROOFING PANELS T1H71 3O3  ONT3A13    E273                 
20080428003042008042800304NE  2008       4          28         2008FA0000257    220080311G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              MALFUNCTIONED   E      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CE03957FE                       208B0070    17431                       AS PILOT OF FLT 7575, LEVELED OFF AT 9000 FT, HEARD A LOUD POP NOISE COME FROM THE ENGINE AND NOTICED TRQ DROPPED BELOW 600 LBS AND ITT STARTED RISING.  PILOT NEVER LOST POWER BUT DUE TO TEMP RISING HE DECLARED AN EMERGENCY AND LANDED SAFELY.  AFTER TALKING TO PILOT AND CHECKING POWER ANALYZER AND RECORDER (PAR) THE ITT TEMP REACHED 926 DEGREES.  ACCORDING TO MM, ANYTHING OVER 900 DEGREES IN CRUISE FLT REQUIRES TO BE PULLED AND SENT TO OVERHAUL SHOP FOR INSPECTION.  WE HAVE BOROSCOPED THE ENGINE AND SEE NO EVIDENCE OF ANY FOD ACCORDING TO OUR CONTRACT MAINT.  THERE IS SIGNS OF AN OVERTEMP.  FIGURED THAT WITH WHAT THE PAR SHOWS.  NOT SURE WHAT CAUSE THE LOUD POP AND THE OVER TEMP.  MAYBE THE COMPRESSOR BLEED VAL1H71 3T3  T  A37CE   E4EA                 
20080428003072008042800307CE  2008       4          28         2008FA0000258    120080228G5730                TAPE                                    CESSNA140   140         2071602CE  CONT  C90   C90*        17009SO                              WING            LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL033527V                       14796                                   DURING FLIGHT, THE FABRIC PATCH CAME OFF.  THE AC WAS LANDED WITH SOME DIFFICULTY BUT WITHOUT INCIDENT.  IT IS SPECULATED THE AIR STREAM GOT UNDER A LOOSE TAPE AND LIFTED THE ENTIRE PATCH FROM THE WING INCLUDING RIPPING THE FABRIC CLIPS OUT OF THE RIBS.  IT IS FURTHER SPECULATED THE PILOTS PREFLIGHT HAD FAILED TO IDENTIFY A POTENTIAL PROBLEM ARISING FROM A LOOSE TAPE.  NEW SYS VI DIFFERS FROM THE OLDER PROCESS IN THE TYPE OF BASE PRIMER AND FINISHING PAINT.  CURRENT SYS CALLS FOR BRUSHING A COAT OF THINNED U500 ADHESIVE WHERE THE TAPE WILL BE LAID.  THIS IS ALLOWED TO DRY.  TAPE IS THEN LAID DOWN AND BRUSHED WITH CEMENT, WORKING THE CEMENT UP INTO THE WEAVE OF THE TAPE AND PAYING SPECIAL ATTENTION TO WORKING TH1H71 3O3  ONCA768    E252                 
20080428003082008042800308GL  2008       4          28         2008FA0000259    120080314G2780                SLAT SYSTEM                             BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A110     NE                                              MALFUNCTIONED   D      O   OTHER                                                                                           J  WARNING INDICATION                                                            TOTAKEOFF        1                      SW05917GL                       9117                                    FLIGHT CREW REPORTED THAT SHORTLY AFTER ROTATION (AFTER T/O) THEY HAD A (FLICKERING) SLAT HALF SPD AND SLAT/FLAP HALF SPD EICAS MESSAGE.  SHORTLY THEREAFTER THEY HAD AN AMBER SLAT FAIL, STALL WARN ADVANCE EICAS MESSAGE, C/B TRIP (E-2 SLAT/FLAP PWR 2) AND FLIGHT SPOILER FAULT EICAS MESSAGE.  THEY WERE ABLE TO LAND AT HOME BASE WITH SLATS OUT/FLAPS 0, WITHOUT INCIDENT (SLATS WERE AVAILABLE, FLAPS WERE NOT AVAILABLE.  THE CAS MESSAGES WERE STILL PRESENT WHEN THEY PARKED THE AC AND THE FOLLOWING FDE MESSAGES: RT MFS NR 3 ACTUATOR/WRG 27656232SX; FLT CONT 2B FAULT (FCU 2 27654282SX; FLAP FAIL LATCHED FAULT NR1 2751000STD.  TROUBLESHOOTING BY MAINT AND DEBRIEF FROM THE FLT CREW REVEALED A BOTTLE OF DRINKING WATER HAD2L72 4F4  FRTT00003NYE00057EN             
20080428003092008042800309SO  2008       4          28         2008FA0000260    220080227G8530712BCA          CYLINDER                                CESSNA402   402B        207590PCE  CONT  O520  TSIO520E    17040SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW055421M544                    402B0021                                CRACKED BETWEEN FIN NR1-3, BEHIND INJECTOR.  DEFECTIVE PRODUCT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A7CE    E8CE                 
20080428003952008042800395SO  2008       4          28         2008FA0000261    220080317G8520639193          BUSHING                                                                    CONT  O520  TSIO520WB   17040SO                              COUNTER WEIGHT  BROKEN          B  VA1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19     32                                 518853                      RECEIVED ENGINE IN AFTER 32.2 HOURS SINCE MAJOR OVERHAUL.  ENGINE WAS DAMAGED BY COUNTERWEIGHT FAILURE ON CRANKSHAFT.  DAMAGED TO THE CRANKCASE, CYLINDERS AND ROD WAS FROM WHAT APPEARED TO BE A BROKEN COUNTERWEIGHT PIN OR FAILURE OF THE COUNTERWEIGHT BUSHING.  THE BUSHING WAS FOUND IN SEVERAL PIECES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E8CE                 
20080428003962008042800396CE  2008       4          28         2008FA0000262    120080401G5410                HINGE                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENG COWLING     BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP09XCBCN                       BB435       PCE80952                    ENGINE ICE VANE HINGE ASSY, BROKEN.  HINGE ASSY BREAKS AND FRAGMENTS INTO SMALL PIECES THAT TEND TO BE INGESTED INTO ENGINE, CAUSING FOD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A24CE   E4EA                 
20080428003862008042800386EA  2008       4          28         2008FA0000263    220080403G8530LW12993         CYLINDER                                PIPER PA32  PA32301     7103207SO  LYC   O540  IO540K1G5   41532EA                              NR 2            CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL058200M1311                   328006048   L1642048AC                  NR 2 CYL CRACKED FROM UPPER SPARK PLUG HOLE TO THE EXHAUST VALVE SEAT.  CRACK IN HEAD LED TO FAILURE OF EXHAUST PUSHROD HOUSING, AND DEFORMATION OF THE EXHAUST PUSHROD.  AC LANDED WITHOUT INCIDENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A3SO    1E4                  
20080428003872008042800387CE  2008       4          28         2008FA0000264    120080402G3710RA442CW12       PUMP                                    BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              VACUUM SYSTEM   FAILED          B  PZ4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL118050U                       TH1657                                  VACUUM PUMP FAILED TO DEVELOP ANY AIR OUTPUT UPON INSTALLATION.  REMOVED PUMP AND INSPECTED, SUSPECT VANES ARE NOT SLIDING OUT AGAINST CYLINDER WALL THUS NOT ALLOWING ANY AIR TO BE DEVELOPED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  3A16    E3SO                 
20080428003882008042800388WP  2008       4          28         2008FA0000265    220080322G7230307241616       COMPRESSOR                              RAYTHN900   HAWKER900XP 4220011CE  GARRTTTFE731TFE731*     01518WP                              ENGINE          SEPARATED       B  ZN3RO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CLCLIMB          1                      WP07897QS135                    HA0014      P122133                     ON CLIMB THROUGH FL140 CREW HEARD BANG FROM RT ENGINE WITH VIBRATION.  RT ITT INCREASED 150C BUT NO OVER TEMP.  REDUCED POWER, THEN BROUGHT POWER BACK UP, WITH SAME RESULT.  CREW LANDED WITHOUT INCIDENT AND ENGINE REMOVED AND SENT FOR REPAIR AND OVERHAUL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4F4  FRTA3EU    E6WE                 
20080428003892008042800389CE  2008       4          28         2008FA0000266    120080409G28201200406245      FUEL LINE                               CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              FUEL SYSTEM     DEFORMED        B  HP6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0122479732                    17264066                                DURING ANNUAL INSPECTION OF THE MAIN FUEL LINE, BELOW FLOOR, JUST AFT OF FIREWALL, WAS FOUND DEFORMED (TWISTED).  PILOT DID NOT REPORT LOW POWER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E274                 
20080428003902008042800390SW  2008       4          28         2008FA0000267    120080407G5751                RIB                                     BBAVIA7     7GCAA       21101N8SW  LYC   O320  O320B2B     41508EA  SNSNCH74D   74DM        EA  RT AILERON      BOWED           C  V36RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13872JM                       42299       L1907339A   AA57931         REMOVED THE RT AILERON DUE TO REPORTS OF BINDING BETWEEN THE AILERON AND WING DURING AEROBATIC MANEUVERS.  ON THE GROUND THE IB AILERON TO AILERON BAY RIB CLEARANCE WAS APPROX .0625 INCH.  IAW TECH SUPPORT THE CLEARANCE SHOULD BE .2500 INCH.  THE WING IB AILERON BAY RIB APPEARED TO HAVE BOWED DUE TO FABRIC SHRINKAGE OVER TIME, CAUSING THE INTERFERENCE.  THE IB AILERON RIB FABRIC WAS OPENED, THE RIB WAS RELOCATED OB .1875 INCH, AND THE FABRIC WAS REPAIRED UTILIZING NEW TAPES AND THE SUPERFLITE PROCESS.  THE REPAIR WAS PAINTED WITH FLEX AGENT ADDED.  IAW TECH SUPPORT, AILERON BALANCING WAS NOT REQUIRED.  REINSTALLED AILERON.  AILERON CLEARANCE AND OPERATION SATISFACTORY.  (K)                                      1H71 3O3  O  A759    E274    5  NP88614   
20080508000072008050800007CE  2008       5          8          2008FA0000268    120080304G3800                DRAIN                                   CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE                              FUSELAGE        PLUGGED         B  MT9RO   OTHER                                                                                           S  AFFECT SYSTEMS                                                                DEDESCENT        1                      SW059546B                       208B0126                                DURING FLT IN MODERATE TURBULENCE THE AP STARTED TO DISCONNECT, TWICE.  THIRD ATTEMPT TO ENGAGE THE AP, THE AC MADE AN UNCOMMANDED 1500 FPM DESCENT.  ATTEMPT TO CORRECT THE ATTITUDE WITH THE CWS FUNCTION WAS MADE BUT THE AP WOULD NOT DISENGAGE.  THE AP DISCONNECT BUTTON WOULD NOT LET GO EITHER.  HAD TO OVERPOWER THE AP CLUTCHES TO REGAIN CONTROL AND ATTEMPTED TO DISCONNECT THE SYS WITH THE C/B, THE AP REMAINED ON AND LIT AFTER PULLED.  RECYCLED THE C/B AND WAS SUCCESSFUL.  THIS HAPPENED ON DESCENT, THE SYS HAD BEEN FUNCTIONING NORMALLY PRIOR TO THE INCIDENT.  MX FOUND WATER ACCUMULATED BEHIND THE REAR CURTAIN.  THIS IS THE AREA THAT THE PITCH SERVO IS LOCATED.  THEY FOUND THAT THE SERVO HAD A SOLENOID STUCK CLO1H71 3T3  T  A37CE   E4EA                 
20080428003942008042800394NM  2008       4          28         2008FA0000269    120080401G8120654327          TRANSITION DUCT                         LANCARLC41  LC41550FG   5150001NM  CONT  O550  TSIO550C         SO                              TURBOCHARGER    CRACKED         B  L9ORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP19139DC714                    41056       914313                      DURING ANNUAL INSPECTION FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O3  ONTA00003SEE5SO                 
20080508000092008050800009CE  2008       5          8          2008FA0000270    120080403G322207436062        ATTACH FITTING                          CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                              NLG             CRACKED         B  7TFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07783WB1044                   18281512    L3000248                    DISCOVERED CRACK DURING ANNUAL INSPECTION.  (2) LONG CRACKS APPROXIMATELY (1) INCH ON (1) SIDE OF THE FITTING ONLY,  (1) AT THE LT LOWER ATTACHMENT AND THE OTHER JUST AFT AND LT OF THE AREA WHERE THE STRUT BARREL IS SECURED.  SUSPECT HARD LANDING BUT NO OTHER DAMAGE NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A13    1E4                  
20080508000102008050800010WP  2008       5          8          2008FA0000271    120080403G2820                LINE                                    HUGHES269   269C        4470504WP                                                               FUEL SYSTEM     LEAKING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW17111AB5    5                 S1911                                   FUEL LEAKING FROM GASCOLATOR INLET LINE, APPROX 5.0 HRS SINCE NEW.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O      4H12                         
20080508000112008050800011CE  2008       5          8          2008FA0000272    120080112G52803901104580007   DOOR                                    RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              LT MLG          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL157088S264                    RB188                                   AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIGHT.  HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED.  MECHANIC/MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS.  RECOMMENDED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS.  THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT, AS WELL AS TECH REP, DETERMINED UNREPAIRABLE.  NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFACTORILY.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)                                                                                                                                     1L72 3F4  FRTA00010WIE3GL                 
20080508000122008050800012CE  2008       5          8          2008FA0000273    120080112G5280390110458008    DOOR                                    RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              RT MLG          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL157088S264                    RB188                                   AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIGHT.  HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED.  MECH/ MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS.  RECOMMENDED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS.  THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT, AS WELL AS TECH REP, DETERMINED UNREPAIRABLE.  NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFACTORILY.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)                                                                                                                                        1L72 3F4  FRTA00010WIE3GL                 
20080508000142008050800014CE  2008       5          8          2008FA0000274    120080128G52803901104500017   DOOR                                    RAYTHN390   390         7150030CE                                                               LT MLG          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1534GN 1121                   RB58                                    THE PILOT WAS INFORMED BY THE FUEL TRUCK DRIVER THAT THE LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITION, AND THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING.  ENGINEERING DEPT RECOMMENDED THAT THE AIRPLANE BE FLOWN BACK UNDER THE AUSPICES OF FAR PART 21.197, SPECIAL FLIGHT PERMITS.  THE DOOR WAS EVALUATED BY MAINT AND QUALITY DEPT, AS WELL AS BY THE LOCAL TECH REP, AND DETERMINED UNREPAIRABLE.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)                                                                                                                                                                                          1L72 3F    RTA00010WI                     
20080508000152008050800015CE  2008       5          8          2008FA0000275    120080128G3297                WIRE                                    RAYTHN390   390         7150030CE                                                               LT MLG          BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1534GN                        RB58                                    AFTER LANDING, THE PILOT WAS INFORMED BY FUEL TRUCK DRIVER THAT LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITION, AND THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING.  ENGINEERING DEPT RECOMMENDED THAT THE AC BE FLOWN BACK UNDER AUSPICES OF FAR PART 21.197, SPECIAL FLIGHTS PERMITS.  THE DOOR WAS EVALUATED BY MAINT, QUALITY DEPT, AND BY TECH REP, AND DETERMINED UNREPAIRABLE.  ADDITIONAL TROUBLESHOOTING REVEALED THAT WIRING FOR THE UPLOCK MICROSWITCH WAS BROKEN, AND IT WAS THIS BROKEN WIRING THAT CAUSED THE MICROSWITCH TO FAIL TO ALLOW THE UPLOCK TO PROPERLY ENGAGE THE LOCKING LUG  ON THE DOOR.  MICROSWITCH AND A NEW LT MLG IB DOOR WERE ORDERED RECEIVED, INSTALLED, RIGGED AND T1L72 3F    RTA00010WI                     
20080428003242008042800324GL  2008       4          28         2008FA0000278    120080415G2100                VALVE                                   DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE                                              LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM11105UV                       40685       L3277551A                   THE ALTERNATE AIR VALVE IS VIBRATING AND CAUSING FRETTING BETWEEN THE INLET RING, PN D41-7166-20-31 AND FLANGE, PN D41-7166-20-33. THE "DUST" IS BEING INGESTED INTO THE FUEL CONTROL SERVO AND ENGINE. THERE NEEDS TO BE A TIGHTER FIT BETWEEN THESE PARTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  ONTA47CE   E1CE                 
20080428003272008042800327EA  2008       4          28         2008FA0000280    220080112G855016991000327     HOSE                                    BEECH 23    C23         1151242CE  LYC   O360  O360A4G     41514EA                              OIL COOLER      LEAKING         G      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      EA172102W     26                M1429       L1673536A                   THE AC EXPERIENCED AN EMERGENCY LANDING AFTER THE PILOT REPORTED SMOKE IN THE COCKPIT.  INSP AND INVESTIGATION REVEALED AN OIL COOLER LINE HAD BEEN MAKING CONTACT WITH THE NR4 EXHAUST STACK (RISER), EVENTUALLY CAUSED THE FIRE SHEATHING AND OIL LINE TO DETERIORATE, CAUSING THE OIL TO LEAK INTO THE HEAT EXCHANGER, WHICH CAUSED SMOKE IN THE COCKPIT OBSERVED BY THE PILOT.  UPON INSP, ALL BUT 16 OZ OF OIL LEAKED OUT OF ENGINE, WELL BELOW THE MINIMUM SAFE QUANTITY FOR THE MODEL INSTALLED ON THIS AC.  PILOT IN THIS CASE WAS ABLE TO KEEP OIL PRESSURE UPON LANDING, THUS AVOIDING A POTENTIALLY SERIOUS SITUATION.  AS A RESULT OF THIS OCCURRENCE, ENGINE HAD TO BE DISASSEMBLED, CLEANED, INSPECTED, REPAIRED AS NECESSARY, AND1L71 3O3  O  A1CE    E286                 
20080428003282008042800328CE  2008       4          28         2008FA0000281    120080416G7120051313211       MOUNT                                   CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO116620E1927 723               56120                                   INSP FOUND UPPER LT BRACKET (0513132-11) WITH A SMALL CRACK ORIGINATING FROM THE LOWER EDGE OF THE ENGINE MOUNT BOLT WASHER.  ONLY A SMALL BEND LINE WAS VISIBLE FROM THE COCKPIT SIDE OF THE BRACKET VIA BOROSCOPE.  AFTER REMOVAL OF THIS BRACKET A CRACK WAS CLEARLY VISIBLE ON THE ENGINE SIDE OF BRACKET. FOUND UPPER RT BRACKET WITH (3) CRACKS SEPARATING THE BRACKET INTO 4 PIECES.  THE THRESHOLD FOR THIS INSP SHOULD BE REDUCED FROM 2500 HRS.  A MORE FREQUENT BOROSCOPE INSP WITHOUT REMOVAL OF THE ENGINE TRUSS MOUNT BOLTS WOULD PROVIDE AN EQUAL LEVEL OF SAFETY AS LONG AS A LARGER AREA WASHER HAS NOT BEEN INSTALLED.  INSTALLATION OF A LARGER AREA WASHER MAY REDUCE THE STRESS POINT AND IMPROVE THE LIFE OF THE BRACKET. 1H71 3O3  ONT3A17    E298                 
20080508000512008050800051EA  2008       5          8          2008FA0000285    120080402G28221D217           PUMP                                    DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              FUEL SYSTEM     FAILED          B  SCIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07359AR                       359                                     BOOST PUMP FAILS AT 11,000 TO 12,000 FT OF ALTITUDE.  WORKS FINE ON GROUND.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H72 3T4  TRTA9EA    E4EA                 
20080508000522008050800052EA  2008       5          8          2008FA0000286    220080414G8530AEL61247        COVER                                   CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0998874632                    17276370    L1379939A   EF023           FOUND ROCKER BOX COVER WITH MULTIPLE CRACKS DURING AC FLEET INSPECTION, FOLLOWING DISCOVERY OF ANOTHER CRACKED COVER ON A DIFFERENT AC.  CRACKS CAUSED, DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER.  THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN ORIGINAL MFG COVER AND THE OTHER MFG COVER AT THE LOWER PORTION OF THE COVER.  RECOMMEND REPLACEMENT OF ALL SS COVERS PN AEL61247 WITH ORIGINAL MFG OR SUITABLE SUBSTITUTE.  (K)                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
20080508000542008050800054EA  2008       5          8          2008FA0000287    220080414G8530AEL61247        COVER                                   CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0963450191                    17275434    L1420839A   TK039           FOUND ROCKER BOX COVER CRACKED DURING 100 HOUR INSPECTION.  CRACKS CAUSED DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER.  THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN AN  ORIGINAL MFG COVER AND THE OTHER MFG COVER AT THE LOWER PORTION OF THE COVER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
20080508000642008050800064CE  2008       5          8          2008FA0000288    120080401G571212210628        BULKHEAD                                CESSNA177   177B        2073708CE  LYC   O360  O360*       41514EA                              RT WING         CRACKED         B  H5GRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA0799NA 6339                   17702697                                DURING ROUTINE INSPECTION, FOUND PART CRACKED.  CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1) OF THEM TO HAVE A SIMILAR CRACK.  THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR THE IB FLAP DRIVE BELLCRANK.  IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN THE LT WING.  THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE.  IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FORE-AFT FORCES BY AIR LOADS ON THE FLAPS.  SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED1H71 3O3  O  A13CE   E286                 
20080508000652008050800065CE  2008       5          8          2008FA0000289    120080401G571212210628        BULKHEAD                                CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA                              RT WING         CRACKED         B  H5GRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07525434336                   177RG1206                               DURING ROUTINE INSP, FOUND PART CRACKED.  CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1) OF THEM TO HAVE A SIMILAR CRACK.  THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR THE IB FLAP DRIVE BELLCRANK.  IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN THE LT WING.  THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE.  IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FOR-AFT FORCES BY AIR LOADS ON THE FLAPS.  SO WHY REINFORCE ONLY ONE SIDE?  IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED TO IN1H71 3O3  O  A20CE   1E10                 
20080508000592008050800059EU  2008       5          8          2008FA0000290    120080423G3210DIN47108VERZ    FASTENER        DIAMON                  DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE1250299       EU                              MLG             MISSING         B  NX4SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15966WW179  79                42106                                   DURING PREFLIGHT, THE CREW NOTICED THAT THE SMALL CIRCLIP (PN DIN471-08-VERZ) THAT SECURES THE MLG DOWNLOCK HOOK PIN IN POSITION WAS MISSING. MAINT JACKED THE AC AND INSTALLED A NEW CLIP. WHEN THIS CLIP IS NOT IN PLACE, THE PIN MIGRATES AFT AND IN SOME CASES DAMAGES THE AFT LIP OF THE WHEEL WELL MATERIAL. THIS OPERATOR HAS 9 OF THESE AIRPLANES AND THERE HAVE BEEN OTHER INSTANCES OF THIS DISCREPANCY.                                                                                                                                                                                                                                                                                                                              1L72 3I3  BRTA57CE   E00069EN             
20080508000892008050800089    2008       5          8          2008FA0000291    420080424G3425011N097200      UNKNOWN                                 CESSNA182   T182T       2072738CE  LYC   O540  TIO540*     41532EA                              COCKPIT         MALFUNCTIONED   B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP05488PJ75                     T18208333                               WHEN TURNING THE (CRS) COURSE KNOB, THE INNER KNOB (BARO) BAROMETRIC PRESSURE KNOB WOULD TURN ALSO.  CHANGING THE ALTITUDE INDICATED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A13    E14EA                
20080508000672008050800067EA  2008       5          8          2008FA0000292    220080423G7414                CAM             SLICK                   PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540AE2A  41532EA                              MAGNETO         WORN            C  UXCRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW05855P 49         07100592    4692014     L1291661A                   BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ORTA25SO   E14EA                
             20080707     EA  2008       7          7          2008FA0000293    220080423G7414                CAM             SLICK                   PIPER PA46  PA46R350T   7104610SO  LYC   O540  TIO540AE2A  41532EA                              MAGNETO         WORN            C  UXCRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW05855P 49         07100592    4692014     L1291661A                   BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ORTA25SO   E14EA                
             20080707     EA  2008       7          7          2008FA0000294    220080423G7414                CAM             SLICK                   PIPER PA46  PA46R350T   7104610SO  LYC   O540  TIO540AE2A  41532EA                              MAGNETO         WORN            C  UXCRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW05855P 49         07100592    4692014     L1291661A                   BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ORTA25SO   E14EA                
             20080707     EA  2008       7          7          2008FA0000295    220080423G7414                CAM             SLICK                   PIPER PA46  PA46R350T   7104610SO  LYC   O540  TIO540AE2A  41532EA                              MAGNETO         WORN            C  UXCRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW05855P 49         07100592    4692014     L1291661A                   BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ORTA25SO   E14EA                
20080508001092008050800109    2008       5          8          2008FA0000296    420080425G3425011N097200      UNKNOWN                                 CESSNA182   T182        2072736CE  LYC   O540  TIO540*     41532EA                              COCKPIT         MALFUNCTIONED   B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP05488PJ75                     T18208333                               WHEN TURNING THE INNER "CRS" COARSE KNOB THE OUTER "BARO" BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITUDE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  3A13    E14EA                
20080508001172008050800117    2008       5          8          2008FA0000297    220080426G8550                ADAPTER                                                                                                                                 OIL SYSTEM      MISMANUFACTURED C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      WP15                                                                    ORDERED SPIN ON OIL FILTER ADAPTER MODEL NR (TAFL).  MACHINED PART WAS NOT COMPLETELY FINISHED.  AN IMPORTANT HOLE IN THE OIL PASSAGE DID NOT CONNECT WITH THE OIL DELIVERY LINE BECAUSE IT WASN'T DRILLED DEEP ENOUGH.  MFG HAS BEEN COOPERATIVE AND AGREES TO REPLACE, HOWEVER IF ANY OF THESE DEFECTIVE PARTS HAVE BEEN INSTALLED IN THIS CONDITION, ENGINE FAILURE COULD RESULT.  (SN 28653L)                                                                                                                                                                                                                                                                                                                                                                                         
200805141    200805141    CE  2008       5          14         2008FA0000300    120080422G531245A3490111      BULKHEAD                                BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              FUSELAGE        CRACKED         B  KX5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15400SF                       RK221                                   WHILE PERFORMING AN (A-B) INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKETS PULLED FROM AFT FUSELAGE BULKHEAD RESULTING IN CRACKS IN THE BULKHEADS AT FRAME STA 329.92.  RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION.  RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS.  THIS IS THE 5TH AIRCRAFT IN A ROW THAT THE BULKHEAD HAS BEEN CRACKED.  THE CRACK HAS BEEN FOUND ON BOTH SIDES OF THE AC.  (K)                                                                                                                                                                                                                                                                                                                    2H72 4F4  FRTA16SW   E25EA                
200805141    200805141    SO  2008       5          14         2008FA0000301    120080418G7160U086126         MUFF                                    LUSCOM8     8E          8190112SO  CONT  C85   C8512F      17008SO                              RT CARB         FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM012004 561                    5937        2244612C                    AFTER A FLIGHT, IT WAS NOTED THAT A PORTION OF SCAT HOSE WAS HANGING FROM THE BOTTOM OF COWLING OPENING.  UPON INSPECTION IT WAS FOUND THAT THE CARBURETOR HEAT FLANGE HAD SEPARATED WITH THE SCAT HOSE ATTACHED WITH CLAMP FRO THE IB HALF OF THE RT CARB HEAT MUFF.  THE CARB HEAT MUFF HALVES WERE REMOVED AND INSPECTED.  EXAMINATION OF THE FAILED ROUND DUCT FLANGE FOUND THE ENTIRE TUBE BROKE OFF AT THE CIRCUMFERENCE ALONG THE EDGE OF THE WELD.  SECONDLY, THERE WERE ABOUT (6) SPIDER LIKE CRACKS AROUND THE BROKEN HOLE WHICH PROPAGATED OUTWARD.  A TOTAL OF APPROX 16 CRACKS, BROKEN TABS INCLUDING A PREVIOUS (PATCH) REPAIR WERE NOTED ON BOTH IB AND OB MUFF HALVES.  AN INNER MUFF RIB WHICH WAS TACK WELDED IN (3) PLACES HA1H71 3O3  O  A694    E233                 
             20080520     CE  2008       5          20         2008FA0000302    120080419G7921649964          GASKET                                  CESSNA210   210L        2073448CE  CONT  O520  IO520*      17032SO                              OIL COOLER      FAILED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      SW09132WB140                    21060114    295375R                     THE OIL COOLER ADAPTER GASKET TAILED IN FLIGHT CAUSING (2) QUARTS OF OIL IN ONE HOUR TO BE PUMPED INTO THE ENGINE COWLING.  THIS ENGINE IS A FACTORY REMANUFACTURED ENGINE WITH 140 HOURS SINCE REMAIN.  ON INSPECTION AND DISASSEMBLY THE OIL COOLER ADAPTER BOLTS DID NOT APPEAR TO BE TORQUED ENOUGH BUT THE GASKET ITSELF WAS BRITTLE AND LEAKING.  THE ENGINE AND ADAPTER SURFACE WERE FLAT AND CLEAN.  THE REPLACEMENT GASKET APPEARS TO BE A BETTER QUALITY.  (K)                                                                                                                                                                                                                                                                        1H71 3O3  O  3A21    E5CE                 
             20080520     SO  2008       5          20         2008FA0000303    120080421G322286280003        DRAG LINK                               PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              NOSE GEAR       CRACKED         B  UC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL195328L                       4496108                                 NOSE GEAR DRAG LINK (PN 86280-003) CRACK LOCATED IN PIVOT BOLT HOUSING ON DRAG LINK WHERE A STANDARD (AN175-22A) BOLT ATTACHES NOSE GEAR DOWN LOCK (PN 86275-004).  PROBABLE FATIGUE CRACK FROM NORMAL CYCLE TIME ON GEAR.  RECOMMEND VISUAL INSP OF AREA AT A SPECIFIC PERIOD OF TIME TO BE DETERMINED BY THE MFG.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A19S0   E286                 
             20080520         2008       5          20         2008FA0000304    420080125G2300G6860113        CONTROL HEAD                            AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE731*     01518WP                              COCKPIT         BURNED          D      G   O2 MASK DEPLOYED                                                                                O  OTHER                                                                         DEDESCENT        1                      SO15970S                        238                                     DURING NORMAL DESCENT, AT JUST PRIOR TO 18000 FT, CREW NOTICED DISTINCT BURNING ELECTRICAL ODOR, OXY MASK PULLED AND THE SMOKE CHECKLIST WAS RUN.  EMERGENCY PRIORITY REQUESTED UPON ARRIVAL, POSSIBLE LIGHT SMOKE IN COCKPIT ONLY WITH NONE IN THE CABIN.  IN LESS THAN (1) MINUTE THE ODOR WAS NOT INCREASING AND SUBSEQUENTLY BEGAN TO CLEAR.  THROUGH 10000 FT IT WAS NOTED THAT THE NR 2 NAV CONTROL HEAD WAS BLANK AND SUSPECTED AS THE PROBABLE CAUSE AS IT WAS CLOSE TO THE STRONGEST SMELL.  NO CIRCUIT BREAKERS POPPED.  REMOVAL OF UNIT NAV/COM CONTROL HEAD (PN G6860113 SN298)  NOTED ELECTRICAL BURNED SMELL WITH UNIT.  PART HAS 9 HOURS SINCE REPAIR/MODIFICATION.  UNIT TO BE SENT BACK FOR REPAIR.  (K)                       2L73 4F4  F  A46EU   E6WE                 
200805141    200805141    CE  2008       5          14         2008FA0000305    120080429G3246FN22A524        NUT                                     RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE731*     01518WP                              WHEEL           MISMANUFACTURED C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO01733A                        258687                                  WHEEL LOCK NUT (P/N FN22A-524) WAS BEING INSTALLED TO COMPLY WITH SB 32-1374 AND WAS FOUND TO HAVE ZERO RUN ON TORQUE. THIS IS A NEW PART AND HAS NEVER BEEN INSTALLED. ONLY ONE OF 24 BOUGHT FROM MFG THAT WAS BAD. THIS BOLT/NUT COMBINATION IS WHAT HOLDS THE (2) HALVES OF THE WHEEL TOGETHER.                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA3EU    E6WE                 
             20080520     EU  2008       5          20         2008FA0000306    120080501G352017408031        OXYGEN MASK                             ISRAEL1124  1124        4500102EU  GARRTTTFE731TFE731*     01518WP                              CABIN           COLLAPSED       H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15                                                                    DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN IN QUESTION IS A 174080-31 REV "K".                                                                                                                                                                                                                                                                                                                                    2M72 4F4  F  A2SW    E6WE                 
             20080520     GL  2008       5          20         2008FA0000307    120080225G7921646880          OIL COOLER                              CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO                                              WORN            C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15476DA300                                                            THE OIL COOLER SUPPORT SHOE RUBBER COATING IS FAILING AND EATING INTO THE OIL COOLER .020 TO .040 OF AN INCH.  IAW MM IT IS INSTALLED AT ENGINE ASSY AND ADJUSTED AFTER INITIAL TEST RUN. THERE IS NO PUBLISHED IN SERVICE INSTRUCTION FOR IT. IF THIS CONDITION IS NOT ADDRESSED BY REPLACEMENT OF SHOE AND OIL COOLER THE POSSIBILITY OF LOSS OF ENGINE OIL IS HIGH. THE 5 AIRCRAFT THAT WE HAVE FOUND, ON THOSE AC THE OIL COOLER HAD TO BE REPLACED. IN ADDITION TO THAT WE HAVE TO REPLACE 18 OIL COOLER SHOE'S PN 632983. THE FAILURE TIME FROM NEW TO HAVING WORN INTO THE ENGINE OIL COOLER IS LESS THEN 600HRS TTAF. THIS IS DUE TO THE RUBBER PORTION OF SHOE FAILING AND ALLOWING THE STEEL PART TO CUT INTO THE OIL COOLER.         1L71 3O3  ONTA00009CHE1CE                 
             20080520     EU  2008       5          20         2008FA0000308    120080501G352017408031        OXYGEN MASK                             ISRAEL1124  1124        4500102EU  GARRTTTFE731TFE731*     01518WP                              CABIN           COLLAPSED       H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15                                                                    DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN IN QUESTION IS A 174080-31 REV "K".                                                                                                                                                                                                                                                                                                                                    2M72 4F4  F  A2SW    E6WE                 
20080508000012008050800001SO  2008       5          8          2008FA0000309    120080507G27202223900         TORQUE TUBE                             PIPER PA24  PA24260     7102406SO                                                               RUDDER CONTROL  BROKEN          B      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM059506P3404                   245023                                  DURING MAINTENANCE RUNUP AND TAXI CHECK AFTER MAINTENANCE THE LEFT RUDDER TORQUE TUBE BROKE OFF. IT APPEARED TO HAVE BEEN CRACKED FOR SOME TIME PRIOR TO FAILING DURING TAXI.  IT IS SUGGESTED THAT THE AREA BE CLEANED AND INSPECTED WITH A 10X MAGNIFYING GLASS. A BORESCOPE WITH A SIDE VIEW END COULD ALSO BE INSERTED IN THE TUBE TO INSPECT IT FROM THE INSIDE. IF THIS HAD HAPPENED DURING LANDING AND HAD BROKEN AT INITIAL BRAKE APPLICATION, THE AIRCRAFT WOULD PROBABLY HAVE DEPARTED THE RUNWAY.                                                                                                                                                                                                                                    1L71 3O      1A15                         
             20080522     NE  2008       5          22         2008FA0000310    220080506G72000319008000      ENGINE                                  UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIUS2F    60010NE                                              MAKING METAL    D      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            DEDESCENT        1                      SO07197CB278  84                1448        34546                       ENGINE CHIP DETECTOR LIGHT ILLUMINATED.  INSPECTED CHIP DETECTORS, AND FOUND METAL SLIVERS ON MODULE NR 1 CHIP DETECTOR. ENGINE REMOVED FROM SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G72 3U3  UNCR0001RD E34NE                
             20080522     NE  2008       5          22         2008FA0000311    220080502G7261                LINE                                    AEROSPSA365 SA365N1     8680668EU  TMECA ARRIELARRIEL2C    60054NE                              P2 OIL          LOOSE           C      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        NRNOT REPORTED   1                      EA0795MD 2551 50                6320        24072                       ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U4  U  H10EU   E00054EN             
             20080522     NE  2008       5          22         2008FA0000312    220080502G7261                LINE                                    AEROSPSA365 SA365N1     8680668EU  TMECA ARRIELARRIEL2C    60054NE                              P2 OIL          LOOSE           C      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        NRNOT REPORTED   1                      EA0795MD 2551 50                6320        24072                       ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U4  U  H10EU   E00054EN             
             20080522     NE  2008       5          22         2008FA0000313    220080502G7261                LINE                                    AEROSPSA365 SA365N1     8680668EU  TMECA ARRIELARRIEL2C    60054NE                              P2 OIL          BACKED OUT      C      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        NRNOT REPORTED   1                      EA0795MD 2551 50                6320        24072                       ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U4  U  H10EU   E00054EN             
             20080522     NE  2008       5          22         2008FA0000314    220080502G7261                LINE                                    AEROSPSA365 SA365N1     8680668EU  TMECA ARRIELARRIEL2C    60054NE                              P2 OIL          BACKED OUT      C      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        NRNOT REPORTED   1                      EA0795MD 2551 50    NA          6320        24072                       ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U4  U  H10EU   E00054EN             
             20080602     CE  2008       6          2          2008FA0000317    120080506G324610320400AN53    BOLT            PARKERHANFIN            RAYTHN36    G36         7150061CE                                                               ZONE 700        SHEARED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07222GL479  479               E3763                                   THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG).  FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT MAIN LANDING GEAR ASSEMBLY.  THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4 INCH.  THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED.  UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS WERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS.  DURING DISASSEMBLY OF THE WHEEL HALF RETAINING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE.  THE NOSE WHEEL WAS THEN CHECKED F1L71 3O    RT3A15                         
             20080603     EA  2008       6          3          2008FA0000318    220080422G852013B27134        CRANKSHAFT                              PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA                              ENGINE          CRACKED         B  UC2RA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      GL194149T                       2843192                                 AC WAS FLYING AT 5000 FT, WHEN ENGINE STARTED TO LOSE POWER AND FAILED.  AC LANDED SAFELY IN A FIELD.  ENGINE WAS FOUND TO BE LOCKED UP.  ENGINE WAS DISASSEMBLED AND COMPONENTS INSPECTED.  CRANKSHAFT WAS FOUND TO HAVE CRACK, CAUSING ENGINE TO LOCK UP.  PROBABLE CAUSE: UNDERTERMINED AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  2A13    E286                 
             20080603     CE  2008       6          3          2008FA0000320    120080425G5100S34691          BEARING                                 CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA  MCAULY2D34C B2D34C207   GL  ACTUATOR        FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP09521564247       1533        177RG1180   L1699351A   771391          WHERE THE ROD END BEARING ATTACHES TO THE LATERAL BOLT, FWD.  THIS BEARING (S34691 FAILED AT THE BEARING END.  THIS BEARING IS UNDER EXTREEM TENSION LOAD AND WAS ORIGINAL.  AGE WAS A FACTOR IN FAILING.  REPLACING THIS BEARING AT 1000 HR INTERVALS IS NECESSARY.  DATE OF THE ACTUATOR WAS 10/77.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  A20CE   1E10    5  CP7EA     
20080515000012008051500001CE  2008       5          15         2008FA0000321    120080425G571100011001316     SPAR CAP        BEECH                   BEECH 90    E90         1152914CE                                                               RT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM05692M 8812 400               LW228                                   THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, (4TH RIVET FROM END OF SPAR CAP)IN THE REAR ROW OF RIVETS, & EXTENDS TO THE TRAILING EDGE OF CAP. THE A/C PASSED 2-400 HR WING SIRM INSPECTIONS. THE CRACK WAS DETECTED AT THE CURRENT 400 HR INTERVAL WING SIRM INSPECTION. NOTE:BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INSPECTION ITEM OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM. REF 8110-4 FOR N776DC FOR SIMILAR DETAILS. A/C IS ON USFS CONTRACT.                                                                                                                                                                                                                              1L72 3T      3A20                         
             20080602     SO  2008       6          2          2008FA0000322    120080505G8010701122223       SOLENOID                                PIPER PA28  PA28161     7102803SO                                                               STARTER         SHORTED         B      H   DEACTIVATE SYST/CIRCUITS                                                                        S  AFFECT SYSTEMS                                                                TXTAXI/GRND HDL  1                      GL21238ND817                    2842101                                 WHEN MASTER SWITCH TURNED ON PROP BEGAN TO ROTATE UNCOMMANDED.  TROUBLESHOT TO STUCK STARTER SOLENOID.  SOLENOID REPLACED, OPS CHECK GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O      2A13                         
             20080602     SW  2008       6          2          2008FA0000323    120080504G2720183M            SLEEVE                                  BBAVIA7     7GCBC       1220601SW  LYC   O320  O320A2D     41508EA                              RUDDER CABLE    CRIMPED         D      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO0353718                       86775                                   RIGHT RUDDER CABLE SEPARATED AT RUDDER BELLCRANK DURING RECOVERY OF INTENTIONAL LEFT SPIN.  CABLE APPARENTLY PULLED OUT OF NICOPRESS SLEEVE.  AIRPLANE WAS LANDED AT KCHA, WITHOUT INCIDENT, AFTER DECLARING AN EMERGENCY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONCA759    E274                 
             20080602     SW  2008       6          2          2008FA0000324    120080507G3110011097203       DISPLAY                                 BBAVIA7     7DC         2110116SW                                                               INSTRUMENT PANELDEFECTIVE       D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM03555Y 93                     7DC2078                                 PRIMARY FLIGHT DISPLAY PANEL HAS A MALFUNCTION IN THE COARSE/BAROMETRIC PRESSURE ADJUSTMENT KNOB.  THE DESIGN INCORPORATES A DUAL FUNCTION TYPE CONTROL KNOB.  THE CENTER KNOB ADJUSTS THE DESIRED NAVIGATIONAL COARSE DISPLAYED ON THE HSI NAV DISPLAY.  THE OUTER KNOB ADJUSTS THE PRIMARY ALTIMETER BAROMETRIC PRESSURE SETTING.  AT TIMES DURING FLIGHT ADJUSTMENT OF THE INNER COARSE KNOB RESULTS IN AN INADVERTENT CHANGE IN THE BAROMETRIC PRESSURE.  THIS MALFUNCTION CAN BE QUITE DANGEROUS, ESPECIALLY WHEN SHOOTING AN INSTRUMENT APPROACH, PILOT CHANGES COARSE HEADING DURING AN APPROACH AND MAY, WITHOUT KNOWING, CHANGE THE BAROMETRIC PRESSURE THUS CAUSING THE ALTITUDE DISPLAY TO BE INACCURATE.                            1H71 3O      A759                         
             20080602     CE  2008       6          2          2008FA0000326    120080425G571100011001316     SPAR CAP                                BEECH 90    E90         1152914CE                                                               WING            CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM05776DC8204 181               LW235                                   THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, 4TH RIVET FROM END OF SPAR CAP, IN THE FRONT ROW OF RIVETS, AND EXTENDS TO THE LEADING EDGE OF CAP.  THE A/C PASSED 2-400 HOUR WING SIRM INSPECTIONS.  181 HRS INTO NEXT INTERVAL WAS WHEN CRACK WAS DETECTED DURING ROUTINE MAINTENANCE.  BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INSP OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM REF 8110-4 FOR N692M FOR SIMILAR DETAILS.  A/C IS ON USFS CONTRACT.                                                                                                                                                                                                                                 1L72 3T      3A20                         
             20080603     EU  2008       6          3          2008FA0000330    120080502G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL                  BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05708AF1656       0563        708         PR0583      KX309           WHILE REMOVING RIGHT MAIN WHEEL ASSEMBLY DISCOVERED THE OUTBOARD BRAKE DISC OF THE RIGHT BRAKE BROKEN INTO TWO PIECES.  REPLACED RIGHT BRAKE ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080603     EU  2008       6          3          2008FA0000331    120080506G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL                  BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05776AF1103       0715        776         PR0657      KX423           FLIGHT CREW REPORTS RIGHT BRAKE GRABBING.  REMOVED RIGHT MAIN TIRE ASSEMBLY AND DISCOVERED THE OUTBOARD BRAKE DISC WAS BROKEN INTO TWO PIECES.  REPLACED THE RIGHT BRAKE ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080603     EU  2008       6          3          2008FA0000332    120080506G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  BRAKE ASSY      BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05591AF875  875   0213        591         PR0454      KX164           FLIGHT CREW REPORTS LEFT BRAKE GRABBING.  REMOVED LEFT MAIN TIRE ASSEMBLY TO INVESTIGATE DISCREPANCY AND DISCOVERED THE OUTBOARD BRAKE DISC BROKEN INTO THREE PIECES.  REPLACED THE LEFT BRAKE ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080603     EU  2008       6          3          2008FA0000333    120080425G3520                INDICATOR                               ISRAEL1124  1124        4500102EU                                                               OXYGEN MASK     INOPERATIVE     C      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      AL05500KE379                    360                                     PASSENGER OXYGEN MASK FLOW INDICATOR INOPERATIVE.  THIS UNIT CAME FROM LOT LC 0521 K OR LOT LC 0526K                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2M72 4F      A2SW                         
             20080701     CE  2008       7          1          2008FA0000335    120080418G214088D7015EL       TUBE                                    BEECH 58    58          1152740CE  CONT  O550  IO550C           SO  MCAULY3AF32C3AF32C512   GL  HEATER          CRACKED         B  YWBRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP17873AN453        A04010003   TH1680                                  WHILE PERFORMING A PRESSURE DECAY TEST IAW AD2004-21-05, THE COMBUSTION TUBE WOULD NOT AINTAIN PRESSURE AND AIR LEAKING WAS NOTED. INVESTIGATION FOUND A .75 INCH LONG CRACK IN THE AFT END OF THE COMBUSTION TUBE NEAR THE RADIUS. CRACK MAY HAVE BEEN CAUSED BY STRESS INDUCED WHILE FORMING  THE END CAP ALONG WITH NORMAL HEATING AND COOLING OF THE HEATER. HEATER HAD 98 HOURS SINCE LANST PRESSURE TEST. A FACTORY REBUILT UNIT WAS INSTALLED AND AIRCRFAT RETURNED TO SERVICE.                                                                                                                                                                                                                                                          1L72 3O3  O  3A16    E3SO    5  CP22EA    
             20080701     EU  2008       7          1          2008FA0000336    120080527G7920307194912       PUMP                                    AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE7313     01518WP                              ENGINE OIL      FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15970S 70                     238                                     IAW MFG RECOMMENDATION, WE REMOVED THE ENGINE OIL PUMP, PN 3071949-11,  AND INSTALLED PN 3071949-12 PUMP BECAUSE OF AN ISSUE (ENGINE HIDING OIL) NOT ABLE TO GET A PROPER OIL QUANITITY READING AFTER SHUTDOWN. MFG SAID THE PN 3071949-12 PUMP SHOULD CORRECT THAT, WHICH IT DID. THE PUMP WE INSTALLED PN 3071949-12, SN 7018, TSO 20 HOURS WITH A ZERO TIME SINCE REPAIRED 8130 FROM MFG TRACKING NR 41056, WO NR 877515-001, DATED 2-4-2008 WITH NO FAULT FOUND. AFTER APPROXIMATELY 10 HOURS, WE HAD WRITE UP OF OIL PRESSURE FLUCTUATING. GROUND RUN AND COULD NOT DUPLICATE, SO WE SWAPPED OIL PRESSURE TRANSMITTERS AND GAUGE WITH OTHER ENGINES FOR TROUBLESHOOTING. THEN THE AIRCRAFT FLEW APPROXIMATELY 38 HOURS WITH EVERYTHING NORM2L73 4F4  F  A46EU   E6WE                 
             20080701     SW  2008       7          1          2008FA0000337    120080701G6400206011725011    ROD                                     BELL  206   206L3       1182108SW  ALLSN 250C  250C30      03013GL                              TAIL ROTOR      CHAFED          B  ULXRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0183WP                        51359                                   DURING AN INSPECTION THE THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206-001-763-001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206-011-725-001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 206-011-722-105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD. THE MM DOES NOT TELL YOU WHICH WAY TO INSTALL THE ROD, HOWEVER, ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK. PLEASE SEE BHT-206L-SERIES-IPB, FIG 64-1 AND FIG 67-12 AND BHT-206L-MM, PARA 67-63, FIG 67-17 DETAIL D, PARA 64-20 AND FIG 64-14. THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE LEVER.                     1G71 3U3  U  H2SW    E1GL                 
             20080701     SW  2008       7          1          2008FA0000338    120080530G6200407310104103    SPRING          BELL                    BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              FRAHM ASSY      DAMAGED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP01701WP                       53542                                   ONE OF EIGHT SPRINGS BROKEN CAUSING DAMAGE TO LOWER HOUSING. LOWER HOUSING, SPRINGS 2 EA. AND PLUGS WERE REPLACED. UNKNOWN WHI SPRING BROKE, SPRING WAS FOUND BROKEN ON SCHEDULED 300 HOUR INSPECTION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UO H2SW    E1GL                 
             20080701     CE  2008       7          1          2008FA0000339    120080512G561010138402521     WINDSHIELD                              BEECH 90    C90         1152913CE                                                               COCKPIT         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25585R 4772                   LJ1169                                  PILOT WAS ON TAKEOFF AND HAD JUST LEVELED OUT FOR FLIGHT AND WINDSHIELD CRACKED ON THE INNER PANE. PILOT RETURNED TO BASE AND THE WINDSHIELD WAS REPLACED. WINDSHIELD WAS SENT TO INSURANCE CO. LAB FOR EVALUATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3T      3A20                         
             20080701     EU  2008       7          1          2008FA0000340    120080512G3233C239251103      ACTUATOR                                AMD   FALC50FALCON50MYST2730106EU                                                               MALF            MALFUNCTIONED   B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09900KE9497                   052                                     WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MAIN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESHOOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THE ACTUATORS NORMALLY FREE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATOR WERE REPLACED WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MFG REPAIR FACILITY FOR TEARDOWN AND EVALUATION. THE ACTUATOR PART AND SERIAL NUMBER ARE AS FOLLOWS: LT ACTUATOR/ PN C23925-1103, SN U22, RT ACTUATOR/ PN C23926-1103.          2L73 4F      A46EU                        
             20080701     EU  2008       7          1          2008FA0000341    120080512G3233C239261103      ACTUATOR                                AMD   FALC50FALCON50MYST2730106EU                                                               MLG             MALFUNCTIONED   B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09900KE                       052                                     WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MAIN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESHOOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THESE ACTUATORS NORMALLY FREE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATORS WERE REPLACED WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MANUFACTURER`S REPAIR FACILITY FOR TEARDOWN AND EVALUATION.  LT ACTUATOR, PN C239251103, SN U22 / RT ACTUATOR PN C239261103, SN U22. (K)                                     2L73 4F      A46EU                        
             20080715     GL  2008       7          15         2008FA0000343    120080618G5210                HINGE                                   DIAMONDA40  DA40        2990002GL  LYC   O360  IO360LYC*   41514EA  HARTZLHCC2Y HCC2YR1     GL  DOOR            CRACKED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07686US                       40640       L3262751A   CH39554B        FOUND CRACKS IN AFT DOOR HINGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTA47CE   1E10    5  CP920     
             20080715     GL  2008       7          15         2008FA0000345    120080616G5210DA4522100002    DOOR                                    DIAMONDA40  DA40        2990002GL  LYC   O360  IO360LYC*   41514EA  HARTZLHCC2Y HCC2YR1     GL  PAX DOOR        DEPARTED        G      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      WP07605US536                    40675       L3276151A   CH399768        ON TAKEOFF CLIMB OUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA47CE   1E10    5  CP920     
             20080715     GL  2008       7          15         2008FA0000346    120080625G5210D4152210000     HINGE                                   DIAMONDA40  DA40        2990002GL                                                               REAR CABIN DOOR CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP074189U991                    40768                                   REAR HINGE DEVELOPING CRACKS IN FIBERS.  NORMAL OPERATING CONDITION.  PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING STRESS ON HINGE POINT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000347    120080625G5210D4152210000     HINGE                                   DIAMONDA40  DA40        2990002GL                                                               REAR CABIN DOOR CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP074191M                       40769                                   REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING STRESS ON HINGE POINT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O    NTA47CE                        
             20080715     CE  2008       7          15         2008FA0000348    120080318G2711EM408810        ACTUATOR                                RAYTHN390   390         7150030CE                                                               ROLL TRIM       MALFUNCTIONED   B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03837JM758                    RB169                                   IN CONJUNCTION WITH REPAIRS FOR UNCOMMANDED ROLL, TRIM ACTUATION AT KMDW REPLACED RT ROLL TRIM ACTUATOR (HBC PN 390-3810090010) WITH RAPID SUPPLIED REPAIRED UNIT. ATTEMPTED TO PERFORM ROLL TRIM FUNCTIONAL CHECKS IAW THE 390 MM 27-10-00-501 AFTER ACTUATOR REPLACEMENT BUT FOUND ROLL TRIM CIRCUIT BREAKER TRIPPING UPON POWER APPLICATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                            1L72 3F    RTA00010WI                     
             20080715     CE  2008       7          15         2008FA0000349    120080502G322012434262        TORQUE LINK                             CESSNA210   210M        2073450CE                                                               NLG             CRACKED         B  ONFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA0570HG 4609                   21062120                                OUR REPAIR STATION HAS REPLACED SEVERAL OF THESE SAME UPPER TORQUE LINKS DUE TO FINDING THEM BENT AT INSPECTION (APPROX 5 TOTAL) THIS IS THE FIRST ONE FOUND CRACKED.  PROBABLE CASUE IS WHAT I BELIEVE IS LANDING IMPACT WITH MORE THAN RECOMMENDED STRUT ESTENSION (5.00 INCH MAX) IAW SRM FIGURE 5-15 WHICH IS ADJUSTABLE BY ADDING SHIMS (ITEM 15) MAXIMUM OF THREE, PN 12436182 IAW THE NOTE OF FIGURE 5-18 OF THE SRM. (K)                                                                                                                                                                                                                                                                                                                1H71 3O      3A21                         
             20080715     CE  2008       7          15         2008FA0000350    120080429G352038101550360     HOSE                                    CESSNA500   560CESSNA   2076750CE                                                               LAV OXYGEN      LEAKING         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03501CW                       5600050                                 DURING SCHEDULED PHASE INSPECTION NOTED HOSE ASSY.  SUPPLYING OXYGEN TO LAVATORY OXYGEN MASK COMPARTMENT FROM MAIN UPPER CABIN OXYGEN LINE ASSY LEAKING. FURTHER INVESTIGATION SHOWED MULTIPLE HOLES IN OXYGEN HOSE ASSY FLEXIBLE HOSE SECTION. SUSPECT HOSE ASSY DETERIORATED FROM AGE AND POSSIBLY HEAT FROM AIRCRAFT BEING PARKED OUTDOORS FOR EXTENDED PERIODS. RECOMMEND TECH CLOSELY INSPECT CABIN OXYGEN SYSTEM COMPONENTS DURING SCHEDULED INSPECTIONS ON OLDER AND HIGH-TIME SERIES AC FOR AGE RELATED DEFECTS. (K)                                                                                                                                                                                                                    2L72 4F    RTA22CE                        
             20080715     CE  2008       7          15         2008FA0000351    120080429G5230991434317       LATCH                                   CESSNA500   560CESSNA   2076750CE                                                               CARGO DOOR      BROKEN          B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03501CW                       5600050                                 DURING SCHEDULED PHASE INSPECTION, FOUND AFT BAGGAGE COMPARTMENT DOOR AFT LATCH ASSY, NOT LOCKING. FURTHER INVESTIGATION FOUND AFT DOOR LATCH ASSY, BROKEN.  REPLACED LATCH ASSY W/ SERVICEABLE LATCH ASSY, OPERATIONS NORMAL. RECOMMEND FURTHER INVESTIGATION BY MFG TO DETERMINE IF MFGED LATCHES PRONE TO EARLY FATIGUE FAILURE AND ISSUE SB TO REPLACE IF HIGH FAILURE RATES NOTED.  TECHS SHOULD INSPECT THESE LATCHES CLOSELY DURING SCHEDULED PHASE CHECKS TO PREVENT POSSIBLE DOOR OPENING IN FLIGHT. (K)                                                                                                                                                                                                                               2L72 4F    RTA22CE                        
             20080715     NM  2008       7          15         2008FA0000352    120080514G571241513017        RIB                                     UNIVAR415   415D        0420306NM                                                               LT WING         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09940523674                   1375                                    SUBJECT PART WAS FOUND TO BE CORRODED WHILE PERFORMING INSPECTION IAW AD 2002-26-02 (D) (3 YEAR REQUIREMENT). LEFT REAR CENTER SECTION RIB, CORRODED AROUND LARGE HOLE THROUGH WHICH PITOT AND STATIC LINES, AND NAV LITE WIRE PASS TO OUTER WING PANEL. REMOVED DEFECTIVE PART AND INSTALLED NEW PART (415-13017) SUPPLIED BY MFG.  CAUSE OF CORROSION UNKNOWN, AS SURROUNDING STRUCTURE WAS NOT AFFECTED. CORRODED PART IS UNTREATED (NOT CORROSION PROOF IN ANY WAY). SUGGEST WING CENTER SECTION OF THESE AIRCRAFT BE CORROSION PROOFED WITH ACF-50 OR WITH CORROSION X OR EQUIVALENT COMPOUND TO PREVENT FURTHER PROBLEMS OF THIS NATURE. (K)                                                                                              1L71 3O      A787                         
             20080715     CE  2008       7          15         2008FA0000353    120080516G3233                SHAFT                                   BEECH 80    65A80       1152808CE  LYC   O540  IGSO540B1A  41532EA                              NLG ACTUATOR    LACK OF LUBE    D      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      SW136AQ  4434                   LD214                                   NOSE LANDING GEAR WOULD NOT DEPLOY ON APPROACH TO LANDING. AFTER NLG REMOVAL, IT WAS DISCOVERED THAT THE NLG ACTUATOR DRIVE SHAFT PN 50820218 INTERNAL SPLINE WAS WORN AND SHEARED.  LUBE POINTS ON DRIVE SHAFT TO LUBE SPLINES TO REDUCE WEAR. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  3A20    1E7                  
             20080715     NE  2008       7          15         2008FA0000354    320080603G61107826691         BOLT                                    DHAV  DHC8  DHC8202     2809007NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  PROPELLER       SHEARED         B  S88RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19802MR1613       20050318    612         PCEAG0125   20050318        WHILE DOING A RGB CHANGE ON THE NR 1 ENGINE OF DASH-8, N802MR, DURING REINSTALLATION OF THE PROPELLER WHILE DOING THE TORQUE SEQUENCE, WE BROKE ONE PROP MOUNTING BOLT. WE SENT THE HUB OUT FOR REPAIR AND SENT THE TORQUE WRENCH TO THE CAL PLACE TO BE VERIFIED. THEY REPLACED 3 MOUNTING BOLTS. WHEN THE HUB CAME BACK FROM REPAIR WE PROCEEDED TO INSTALL THE BLADE USING A DIFFERENT TORQUE WRENCH. AS WE WERE DOING THE CRISSCROSS PATTERN, I NOTICED THAT THE BOLTS THAT WERE NOT REPLACED WOULD NOT GRAB TORQUE THE TORQUE WRENCH WOULD  CLICK ONCE BUT ON THE SECOND CLICK IT WOULD MOVE OVER .2500 OF A TURN, THE 3 NEW SCREWS CLICK FINE CLICK CLICK.  WE FIGURED THAT THE BOLTS HAD JUST BEEN REMOVED AND REINSTALLED AND THEY WERE 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080715         2008       7          15         2008FA0000355    420080513G2215L109BBM         ACTUATOR                                SKRSKYS76   S76B        8143007NE                                                               AUTOPILOT SYS   MALFUNCTIONED   G      O   OTHER                                                                                           FP FLT CONT AFFECTED         NO WARNING INDICATION                               CRCRUISE         1                      EA63150US                       760312                                  PILOT HSI SPINS WILDLY TO THE RIGHT AND DISPLAYS A HEADING FLAG. PILOT`S FLIGHT DIRECTOR MAINTAINS HEADING AND ALTITUDE FOR APPROXIMATELY 30 SECONDS THEN LOSES ALL INPUT. THE AIRCRAFT THEN TURNS AND DESCENDS AT WILL.  WHILE THIS HAPPENS THE LEFT ANTI-TORQUE PEDAL DRIVES FORWARD PLACING THE HELICOPTER OUT OF TRIM. THE PILOT SIDE HEADING COMMAND BARS JUMP WILDLY AND TURN TO THE LEFT WHILE THE AIRCRAFT IS IN STRAIGHT AND LEVEL FLIGHT. ONCE THE FLIGHT DIRECTOR LOSES INPUT THE CYCLIC TRIM WILL NOT RESPOND IN THE PITCH OR ROLL CHANNEL. TRIED TO DISENGAGE AND RE-ENGAGE THE SYSTEM BUT THE SAME PROBLEM RETURNS. THE AIRCRAFT REQUIRES MANUAL PEDAL INPUT TO REMAIN IN TRIM. NO EMERGENCY ACTIONS WERE TAKEN OR NEEDED DURING T1G72 4U      H1NE                         
             20080715     GL  2008       7          15         2008FA0000357    120080501G322211907005        STRUT                                   CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO                              NLG             CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15241CP516                    201713      360239                      AFTER INSPECTION OF AIRCRAFT AFTER A REPORT OF NOSE WHEEL PANT DAMAGE ON LANDING. I FOUND THE UPPER LEFT ARM ON THE NOSE STRUT WAS SERIOUSLY CRACKED. THE CRACK RAN FROM THE TOP OF THE ARM ON THE NOSE STRUT WAS SERIOUSLY CRACKED. THE CRACK RAN FROM THE TOP OF THE ARM. JUST FORWARD OF THE STRUT DATA PLATE, THROUGH THE ENTIRE  ARM  AND STOPPED AT THE BOTTOM WHERE A GUSSET WAS WELDED.  THE CRACK CONTINUED TO RUN PARALLEL TO GUSSET FOR ABOUT .5 OF AN INCH. A SMALLER CRACK WAS ALSO FOUND ON THE RIGHT ARM STARTING AT THE SAME POINT AS THE LEFT ARM BUT ONLY MEASURED ABOUT .5 OF AN INCH. ALSO FOUND NOSE WHEEL STOP AND NOSE FORK WAS DAMAGED. POSSIBLE CAUSE COULD BE REPEATED UNREPORTED HARD LANDINGS. WOULD RECOMMENDED ALL1L71 3O3  ONTA00009CHE1CE                 
             20080715     EA  2008       7          15         2008FA0000358    120080519G275060093000123     CONTROL BOX                             CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A      30066NE                              T/E FLAPS       FAILED          C      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      SO03779AZ12                     5176                                    CREW REPORTED FLAP FAILURE DURING APPROACH APPROXIMATELY 8 HOURS AFTER INSTALLATION. RESET SYSTEM AND FLAPS WORKED FINE. FLEW AIRCRAFT HOME AND NO DISCREPANCIES. UNABLE TO DUPLICATE PROBLEM UNTIL SEVERAL WEEKS LATER DURING MAINTENANCE RUN. FLAPS WOULD IMMEDIATELY FAIL, INTERMITTENTLY. PLACED ELECTRICAL RECORDER  ON SYSTEM WITH BREAKOUT BOX AND FOUND INTERMITTENT SIGNAL LOSS ON SIGNAL 2 WHEN INSTALLED ON LEFT WING. SWAPPED UNIT TO RIGHT WING AND FLAPS WOULD CONSISTANTLY FAIL INTERMITTENTLY. THIS TIME FOUND SIGNAL LOSS ON RIGHT WING, SIGNAL 1. INSTALLED REPAIRED UNIT, SYSTEM WORKING OK RIGHT NOW. THIS UNIT HAD LESS THAN 13 HOURS TT SINC REPAIR ON IT. (K)                                                            2L72 4F4  FRTA21EA   E15NE                
             20080715     EA  2008       7          15         2008FA0000359    120080521G2750600930035       CONTROL HANDLE                          CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A1     30068NE                              COCKPIT         DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO03779AZ3502                   5176        807241                      AIRCRAFT HAD BEEN EXPERIENCING MULTIPLE INFLIGHT FLAP FAILURES WHICH WERE NOT DUPLICATED ON THE GROUND. DURING TROUBLESHOOTING OF THE FLAP SYSTEM, FLAPS WOULD NOT MOVE FROM 45 DEGREES TO 30 DEGREES WHEN SELECTED. NO FAILURE WAS DISPLAYED BY THE AIRCRAFT. FLAP HANDLE WAS JOGGLED AND FLAP MOVEMENT WOULD BEGIN. REPLACED FLAP CONTROL HANDLE. (K)                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20080715     CE  2008       7          15         2008FA0000360    120080515G5720662121126       STIFFENER                               CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                              LT MLG WW       MISINSTALLED    B  X07RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07698QS                       5605653                                 FOUND RT STIFFENER (PN 662121126) INADVERTENTLY INSTALLED IN LT POSITION. WITH LANDING GEAR IN THE STOWED POSITION, THE ACTUATOR CONTACTED THE STIFFENER AND CAUSED MINOR CHAFFING. NEITHER THE ACTUATOR NOR THE STIFFENER WERE DEFORMED/ DAMAGED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA22CE   E00059EN             
             20080715     EA  2008       7          15         2008FA0000361    120080521G275060093000117     FCU                                     CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A1     30068NE                              T/E FLAPS       FAILED          D      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      SO03779AZ                       5176        807245                      AC HAS BEEN EXPERIENCING INTERMITTENT FLAP SYSTEM FAILURES IN DIFFERENT MODES OF FLIGHT, PRIMARILY DURING APPROACH. TROUBLESHOOTING IAW MM RECOMMENDED REPLACEMENT OF FLAP CONTROL UNIT DUE TO IMMEDIATE ( INTERMITTENT) FAILURES AFTER FLAP MOVEMENT SELECTION. AFTER INSTALLATION OF THIS UNIT IN AIRPLANE, FLAPS FAILED TAKEOFF CONFIGURATION WARNING SYSTEM CHECK WHEN UTILIZING LEFT POWER LEVER (THROTTLE LEVER). UNIT NOT RETURNED TO SERVICE. NO FLIGHT TIME PLACED ON UNIT.  THIS PART HAD A FRESH INSPECTION TAG FROM VENDOR. (K)                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
             20080715     CE  2008       7          15         2008FA0000362    120080507G2910620701098       HYDRAULIC LINE                          CESSNA650   650         2076802CE                                                               HYDRAULIC SYSTEMLEAKING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15126MT3822                   6500044                                 NOTED HYDR FLUID LEAKING FROM RT WING IN THE MLG AREA. TROUBLESHOOTING REVEALED A GROUND SPOILER HYD LINE. LOCATED ON THE REAR FACE OR THE AFT SPAR AT WS 84 (APPROX). HAD BEEN CHAFED THROUGH BY THE AILERON CABLES. DUE TO THE CLOSE PROXIMITY OF THE LINE AND CABLES, THIS AREA SHOULD BE CLOSELY INSPECTED TO DETECT ANY CHAFING PROBLEM. (K)                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A9NM                         
             20080715     EU  2008       7          15         2008FA0000363    120080406G6320350A32030004    GEARBOX                                 SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1A2   60030NE                              MAIN ROTOR      DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13111AK4093 2110              3092        4571                        HAD A MAIN GEARBOX CHIP EVENT. PERFORMED CHECKS IAW MM TO INCLUDE OIL DAIN, STRAIN AND FLUSH. HAD FIVE SCALE TYPE CHIPS THE LARGEST BEING 1.5MM AND SENT IN FOR ANALYSIS. RETURNED AIRCRAFT TO SERVICE.  AT RECEIPT OF ANALYSIS DATA PERFORMED A BORESCOPE OF PINION AND BEVEL WHEEL. FOUND FROSTING DAMAGE ON PINION GEAR AND REMOVED AIRCRAFT FROM SERVICE. (K)                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH9EU    E19EU                
             20080715     CE  2008       7          15         2008FA0000364    120080509G2731                TRIM SWITCH                             CESSNA206   P206B       2073309CE  CONT  O520  IO520F      17032SO                              PILOTS YOKE     INOPERATIVE     D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM014711F                       P2060311    248025R                     PILOT REPORTED IN FLIGHT WHEN AUTOPILOT/ELECTRIC TRIM ENABLE, TRIM SERVO "RAN ON", WHEN ELECTRIC TRIM TURNED OFF MANUAL TRIM WHEEL OPERABLE AND NO MALFUNCTION OF SYSTEM NOTED, UPON INSPECTION NOTICED SOLDERED CONNECTION ON BASE OF SWITCH BENT AND JUMPED BETWEEN WIRE POSTS ON BASE OF SWITCH. RESOLDERED CONNECTION, SEAL WITH HEAT SHRINK AND OPERATED SYSTEM OK. (K)                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  A4CE    E5CE                 
             20080715     EA  2008       7          15         2008FA0000365    220080522G8530SLC36005        CYLINDER                                CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              ENGINE          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0121295681                    17263925                                ENGINE WAS OVERHAULED NOV 2001 USING NEW CILINDER ASSEMBLES. BREAK-IN OPERATION PERFORMED WITH MFG SERVICE INSTRUCTION 1427B AND MINERAL OIL. ENGINE OPERATED NEAR DAILY FLIGHTS AVERAGEING .5 HOUR EACH. REGULAR OIL CHANGES USING 15W50 OIL AND ADDITIVE, POST BREAK-IN TIME OF 25 HOURS. OIL SAMPLE RESULTS INDICATED PREMATURE WEAR OF RINGS AND WALLS STARTING WITH FIRST SAMPLE AT 111.0 HOURS AND EVERY 30-50 HOURS THERE AFTER. REMOVED CYLINDERS FOR INSPECTION AFTER DISCOVERING VISIBLE METAL IN SCREEN AT 681 HOURS SINCE OVERHAUL. CYLINDER WALLS ON ALL FOUR ENGINE CYLINDERS WORN/DETERIORATED TO DEGREE THAT THE PISTON PIN PLUGS WERE SCRAPING ON RIDGES FROM PISTON RINGS.  NOTABLE ALUMINUM FROM PISTON PIN PLUGS WAS FOUND I1H71 3O3  ONT3A12    E274                 
             20080715     CE  2008       7          15         2008FA0000366    120080524G7603                ARM                                     CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              THROTTLE CABLE  BROKEN          B  O6WRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0575528                       17267783    L153076T                    BOLT CONNECTING CARBURETOR THROTTLE ARM TO THROTTLE CABLE FAILED RESULTING IN THROTTLE STICKING OPEN. PILOT PLACED MIXTURE CONTROL IN IDLE CUTOFF POSITION AND ATTEMPTED TO GLIDE TO RUNWAY AT AIRPORT. AIRCRAFT IMPACTED POWER LINES SHORT OF RUNWAY. BOLT WAS NOT RECOVERED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E274                 
             20080715     CE  2008       7          15         2008FA0000367    120080522G275099105863        MOTOR                                   CESSNA208   208B        2073701CE                                                               TE FLAPS        BURNED          D      B   EMER. DESCENT                                                                                   B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      NM04110WY295                    208B1020                                ON 5/7/08 DEPARTED AT APPROXIMATELY 8:30 LOCAL TIME. FLAPS SET TO 10 DEGREES FOR TAKEOFF. TAKEOFF & CLIMB NORMAL. AFTER 10 TO 15 MINUTES INTO FLT WITH AUTOPILOT ENGAGED, NOTICED A BURNING ODOR & SAW A SMALL AMOUNT OF SMOKE THAT LASTED FOR A SECOND OR TWO. DISENGAGED AUTOPILOT & LOOKED AT CIRCUIT BREAKERS & NOTICED STALL WARNING CIRCUIT BREAKER HAD POPPED. AFTER RETURNING TO AIRPORT, FOUND SEVERAL CIRCUIT BREAKERS HAD POPPED & FLAPS WERE INOPERATIVE & STUCK AT 10 DEGREES. AVIONICS SHOP REPORTED THE FOLLOWING: HIDDEN DAMAGE INSPECTION PERFORMED. BURNED WIRES FOUND IN WIRE BUNDLE RUNNING FROM MAIN FLAP MOTOR TO CIRCUIT BREAKER PANEL & FROM MAIN FLAP MOTOR TO GROUND BLOCK J66. INSULATION OF ADJACENT WIRES ALONG SAM1H71 3T      A37CE                        
             20080715     CE  2008       7          15         2008FA0000368    120080509G2430DOFFO10300J     ALTERNATOR                              CESSNA206   206CESSNA   2073302CE  CONT  O520  IO520F      17032SO                              ENGINE          SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM014711F                       P2060311    248025R                     BODY THRU SCREWS BACKING OUT CAUSING ALTERNATOR HALVES TO START TO SEPARATE, THOUGH NO IMMEDIATE ISSUES WITH AICAFTS CHARGING SYSTEM, NOTICED DISCREPANCY UPON VISUAL INSPECTION AFTER LANDING. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  A4CE    E5CE                 
             20080715     SO  2008       7          15         2008FA0000369    220080322G7414                GEAR                                                                       CONT  O550  IO550N      17042SO                              MAGNETO         STRIPPED        G      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      EA612354B                       0077        685811                      A PRE-TAKEOFF ENGINE RUNUP WAS SATISFACTORY. SHORTLY AFTER LIFTOFF THE AIRCRAFT BEGAN VIBRATING SUBSTANTIALLY. AFTER REACHING PATTERN ALITUDE, REDUCED POWER AND SWITCHED TO LT MAGNETO OPERATION AND THE ENGINE RAN SMOOTHLY. SWITCHED TO RT MAGNETO OPERATION THE ENGINE ESSENTIALLY DIED AND UPON RETURNING TO "LT" THE ENGINE EXPERIENCED AN AFTER FIRE (AKA BACKFIRE) THEN RAN SMOOTHLY ONCE AGAIN. RETURNED TO THE DEPARTURE AIRPORT AND REMOVED THE ENGINE COWLING. REMOVED THE TIMING PLUG ON THE RT MAG AND FOUND THE DISTRIBUTOR GEAR WOULD TURN FREELY. REMOVED THE MAGNETO. PARTIAL DISASSEMBLY REVEALED THE DISTRIBUTOR GEAR WAS STRIPPED OF NEARLY HALF ITS TEETH. BOTH MAGNETOS HAVE SINCE BEEN REPLACED. EACH MAGNETO HAS A THRE       3  O          E3SO                 
             20080715     CE  2008       7          15         2008FA0000370    120080507G3220                LEG ASSY                                CESSNA170   170A        2072304CE  ROTAX 912   ROTAX912UL       EU                              NLG             BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE015455C                       19489       5645575                     NOSE LANDING GEAR LEG BROKEN AT FORWARD WELD ON SHOCK ABSORBER ATTACHMENT BRACKET. EXISTING INTERNAL CRACK. PROBABLE CAUSE, BAD WELD. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A799    EXPE3I               
             20080718     SO  2008       7          18         2008FA0000371    220080510G8500                ENGINE                                  CESSNA172   172G        2072420CE  CONT  O300  O300D       17022SO                                              VAPOR LOCK      D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW19172BX                       17254216    24635D1D                    AC WAS BEING FLOWN ON RT FUEL TANK. AFTER RUNNING TANK DRY, PILOT SELECTED RT FUEL TANK AND MOMENTS LATER THE ENG STOPPED PRODUCING POWER AND MADE AN EMERGENCY LANDING.  AC FUEL SYS WAS INSPECTED FOR CONTAMINATES AND FAILURES, NONE WERE FOUND. POSSIBLE CAUSE IS VAPOR LOCK IN FUEL SYS FROM RUNNING FUEL TANK TRY. TO PREVENT THIS FROM RECURRING, WOULD BE TO SELECT ANOTHER FUEL TANK PRIOR TO RUNNING THE SELECT FUEL TANK DRY. (K)                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    E253                 
             20080715     WP  2008       7          15         2008FA0000372    120080514G633023688           RETAINER                                HILLERUH12  UH12E       4360122WP  LYC   O540  VO540*      41532EA                              M/R TRANSMISSIONMISMANUFACTURED B  ZYEGK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA251523T                       1740                                    RETAINER SUSPECTED LOCALLY MADE INSTALLATION WORD "UP" IS NOT STAMPED ON PART BUT ETCHED ON BY HAND. THICKNESS OF RETAINER IS .045, ACTUAL PART THICKNESS OF NEW RETAINER IS .051.  FOUND SHAFTS THAT ARE SHIMMED WITH BAD RETAINERS TO BE SHIMMED IMPROPERLY DUE TO RETAINER THICKNESS AS REQURIED BY MFG O/H MANUAL. SHAFTS WERE OUT OF TOLERANCE BY .014 TO .020. (K)                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  4H11    E304                 
             20080715     SO  2008       7          15         2008FA0000373    120080515G3010488699          TIMER                                   PIPER PA31T PA31T1      7103126SO                                                               WING DE-ICE SYS MISMANUFACTURED D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM1093CN                        31T8004029                              THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECOND TIMER UNIT WAS PURCHASED AND THE SAME PROBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND WIRING, IT WAS FOUND THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING OPPOSITE AS IS INTENDED.  THERE ARE FOUR WIRES. RED, BLACK, WHITE AND BLUE. THE WHITE AND BLUE WIRES ARE REVERSED. (K)                                                                                                                           1L72 3T      A8EA                         
             20080715     SO  2008       7          15         2008FA0000374    120080515G3010488699          TIMER                                   PIPER PA31T PA31T1      7103126SO                                                               WING DE-ICE     MISMANUFACTURED D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM1093CN                        31T8004029                              THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECONDTIMER UNIT WAS PURCHASED AND   THE SAME PORBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND WIRING, IT WAS FOUDN THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING OPPOSITE AS INTENDED. THERE ARE FOUR WIRES, RED, BLACK, WHITE AND BLUE, THE WHITE AND BLUE WIRES ARE REVERSED.  (K)                                                                                                                             1L72 3T      A8EA                         
             20080715     CE  2008       7          15         2008FA0000377    120080701G5730501102715       SKIN                                    BEECH 200   B200C       1152924CE  PWA   PT6   PT6A42      52043NE                              RT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP197232R8914                   BL69                                    DURING A PREFLIGHT INSPECTION, MAINTENANCE TECH NOTED A 3.75 INCH LONG CRACK IN THE RT WING LOWER WING SKIN JUST FWD OF THE IB SECTION OF THE OB FLAP. ADDITIONALLY A SUPPORT/ ANCHOR TAB THAT ATTACHES THE LOWER WING SKIN TO THE IB MOST FLAP WELL RIB OF THE OB WING, WITHIN THE FLAP WELL, WAS FOUND CRACKED THROUGH/FAILED. WE BELIEVE THIS TAB FAILURE ALLOWED THE SKIN TO VIBRATE GENERATING THE RAPID CRACK GROWTH. THIS CRACK IS DIRECTLY AFT OF THE LOWER AFT WING BOLT. THIS CRACK HAS JUST APPEARED WITHIN THEPAST (2) HOURS OF FLIGHT TIME.  CAN PINPOINT THIS TIME FRAME SINCE THE 5 YEAR WING BOLTS REMOVAL AND INSPECTION PROCESS WAS COMPLETED JUST 2 FLIGHT HOURS AGO AND NO WING SKIN CRACKS WERE NOTED/ DOCUMENTED AT THAT T1L72 4T4  T  A24CE   E4EA                 
             20080718     GL  2008       7          18         2008FA0000378    120080415G7931                TRANSMITTER                             CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              OIL PRESSURE    MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO13748CD                       0086                                    FOLLOWING ACTIONS WERE TAKEN AS A RESULT OF A PRECAUTIONARY LANDING, WHERE PILOT REPORTED A LOSS OF OIL PRESSURE.  AT CRUISE, AT 8000 FT,  OIL PRESSURE ANNUNCIATOR LIGHT ILLUMINATED, OIL PRESSURE GAUGE INDICATED NO OIL PRESSURE.  AFTER LANDING, OIL PRESSURE RETURNED TO NORMAL. TECH SUPPORT WAS CONTACTED, RECOMMENDED CHECKING OIL PRESSURE SWITCH CONNECTORS. THEY FEED BOTH ANNUNCIATOR AND GAUGE. CONNECTORS WERE CLEANED, CHECKED FOR INTEGRITY AND RECONNECTED. NO PROBLEMS WERE FOUND. OIL LEVEL WAS FOUND AT APPROX (6) QTS. (1) QUART 20X50 WAS ADDED.  ENGINE STARTUP AND OIL PRESSURE WAS NORMAL, WITH  READING AT  TOP OF THE GREEN, COLD, DECREASING TO 50 PSI, HOT.   ALL OTHER ENG PARAMETERS APPEAR NORMAL.  SUSPECT A CO1L71 3O3  ONTA00009CHE3SO                 
             20080715     EA  2008       7          15         2008FA0000379    120080530G5541                SPAR                                    SCWZERG164  G164B       3952802EA  PWA   R1340 R1340*      52016NE                              RUDDER          CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP253628D                       735B                                    FOUND EXTERNAL CORROSION ON RUDDER MAIN TUBULAR SPAR APPROXIMATELY (2) INCHES ABOVE RUDDER CONTROL HORN. POST WAS SEVERELY CORRODED WITH HOLES THRU TUBE. AD 78-08-09 ADDRESSES THIS PROBLEM BUT NOT FOR THIS MODEL AIRCRAFT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1Q71 3R3  R  1A16    5E2                  
             20080715     SO  2008       7          15         2008FA0000380    220080303G8520                ENGINE                                                                     CONT  O520  IO520CB     17032SO                                              MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     2400                               502                         OH ENGINE AND RETURNED TO SERVICE APROX (2) YEARS AGO, 600 HOURS OPERATION.  ENGINE FAILED WHEN POWER WAS REDUCED ON LANDING. THE COUNTERWEIGHT MANAGED TO HOOK ON THE CYLINDER DECK STUD AND DRAG IT INTO THE CASE, GETTING INVOLVED WITH THE ROTATING COMPONENTS.  MASSIVE DAMAGE TO THE ENTIRE ROTATING MASS.  IT WAS NOTED ON TEARDOWN THAT AT THE CYLINDER DECK STUDS (NECK STUDS) DO EXTEND THRU THEIR HOLES IN THE CYLINDER PAD APPROX .1875 TO .3125 BELOW THE BOTTOM OF THE HOLE IN THE CASTING.  THE LATER CASTINGS HAVE .2500 TO .3125 THICKER MATERIAL CAUSING THE STUDS TO BE EVEN WITH THE BOTTOM OF THE HOLES, AND TO HAVE SEVERAL MORE THREADS IN THE CASTING.  AFTER EXAMINING THE CASE, NOTED, BASED ON THE DESIGN OF THE STUD       3  O          E5CE                 
             20080718     CE  2008       7          18         2008FA0000381    120080401G531212210628        BULKHEAD                                CESSNA177   177RG       2073709CE                                                               FUSELAGE        CRACKED         B  H5GRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA077582V2340                   177RG0873                               DURING ROUTINE INSP, FOUND PART CRACKED. CHECKED (2) OTHER AC THAT HAPPENED TO BE IN SHOP, FOUND (1) OF THEM TO HAVE A SIMILAR CRACK.  THIS SECTION OF BULKHEAD IS  ATTACH STRUCTURE FOR LWR ATTACH ANGLE FOR IB FLAP DRIVE BELLCRANK. IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN LT WING.  THERE ARE EVEN SOME "PILOT DRILL" (PD) HOLES DRILLED AT FACTORY IN RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE. IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE SAME FORE-AFT FORCES BY AIR LOADS ON FLAPS.  SO WHY REINFORCE ONLY ONE SIDE? IT IS POSSIBLE THAT FACTORY ASSY LINE NEGLECTED TO INSTALL AN INTENDED SIMILAR REINFORCEMENT ON THE RT SIDE?  (1H71 3O      A20CE                        
             20080715     EU  2008       7          15         2008FA0000382    120080424G79221586108         REGULATOR                               BRAERODH125 BAE125800A  1500285EU  GARRTTTFE731TFE7315R    01518WP                              OIL SYSTEM      DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07626CG                       258041      P91187                      RECEIVED O/H OIL TEMP REGULATOR FROM MFG UNDER THEIR WO 815978-001, DATED 04/22/2008.  WHILE PERFORMING INCOMING PARTS INSPECTION ON 04/24/2008, FOUND FUEL INLET PORT SMASHED.  THERE WAS NO DAMAGE TO THE SHIPPING CONTAINER.  PROBABLE CAUSE OF DAMAGE WAS MOST LIKELY PRIOR TO PACKING OF UNIT FOR SHIPMENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA3EU    E6WE                 
             20080715     WP  2008       7          15         2008FA0000383    220080523G721031020474        HOUSING                                 MTSBSIMU2   MU2B25      5780409CE  GARRTTTPE331TPE33110    01514WP                              GEARBOX         CRACKED         B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SW15856JT                       306                                     PILOT REPORTED LOW AND FLUCTUATING OIL PRESSURE FROM LEFT ENGINE IN FLIGHT AND ELECTED TO SHUT THE ENGINE DOWN. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE.  THE ENGINE OIL BYPASS VALVE WAS FOUND TO BE IN THE "POPPED" CONDITION, THE OIL FILTER WAS THEN REMOVED AND FOUND TO BE BLACK IN COLOR WITH THE FORWARD SEALING SURFACE BROKEN IN SEVERAL SMALL PIECES.  THE REDUCTION GEAR BOX WAS DISASSEMBLED AND THE OIL PRESSURE PUMP REMOVED.  THE FORWARD HOUSING WAS CRACKED APPROXIMATELY (3 INCH) RADIALLY AT FWD DETAIL.  (K)                                                                                                                                                                                                          1H72 3T4  T  A2PC    E4WE                 
             20080718     GL  2008       7          18         2008FA0000384    220080519G726123063413        GEAR                                    BELL  206   OH58B       1181503SW  ALLSN 250C  T63A720     03002GL                              AIR/OIL SEPARATRBROKEN          D      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      SO05     600                                AE405555                    PILOT REPORTED ENGINE CHIP LIGHTS ON TAKEOFF.  ABORTED MISSION AND RETURNED TO HELIPAD. ENG WAS REMOVED AND SENT FOR INVESTIGATION.  ENG RECEIVED FOR REPAIR DUE TO ENG CHIP LIGHTS AND METAL IN OIL.  DISASSEMBLY REVEALED AIR OIL SEPARATOR GEAR SHAFT HAD BROKEN WHERE STEM MEETS THE BASE.  THIS IS THIRD OCCURRENCE ON THIS PARTICULAR ENG ASSY OF SIMILAR GEAR FAILURES.  HAVE SEEN AT LEAST 8 OF THESE FAILURES IN T63 ENGINES SINCE THEY HAVE BEEN RELEASED TO PUBLIC.  (K)                                                                                                                                                                                                                                                             1G71 3U3  U  H2SW    E4CE                 
             20080715     CE  2008       7          15         2008FA0000385    120080605G322166426119        TRUNNION                                CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              NLG             CORRODED        B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05640QS6122                   5605240                                 (REF CWQR200806) WHILE WORKING AN UNSCHEDULED NOSE GEAR VIBRATION, POPPING, DISCREPANCY.  FOUND BEARING PN MS2464268G TO BE ROUGH WHEN TURNING.  UPON FURTHER INSPECTION FOUND CORROSION AND PITTING BETWEEN STEEL BEARINGS AND ALUM NLG TRUNNION ASSY.  NLG TRUNNION SHOULD BE TREATED TO PREVENT DISSIMILAR METAL CORROSION.  FILED SLR NR 363322.  (K)                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA22CE   E00059EN             
             20080715     NM  2008       7          15         2008FA0000387    120080610G5340                ATTACH ANGLE                            BOEING737   737448      13844BUNM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                                                               (REF DU4R2008212) DURING SCHEDULED INSPECTION, FOUND CORROSION IN AFT LOWER CARGO COMPARTMENT AT STA 727A ATTACH ANGLE GBGETWEEN S-27R AND S-26R.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000388    120080610G5310                DOOR FRAME                              BOEING737   737448      13844BUNM                                                               FUSELAGE        CRACKED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   (REF DU4R2008213) DURING SCHEDULED INSPECTION, FOUND 1 INCH LONG CRACK ON FWD CARGO DOOR CUT-OUT AFT FRAME INNER CHORD RADIUS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000389    120080610G5330                SKIN                                    BOEING737   737448      13844BUNM                                                               BS 887  S19R    DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   (REF DU4R2008214) DURING SCHEDULED INSPECTION, FOUND DENT ON LWR RT LOWER AFT FUSELAGE BS 887 S-19R.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000390    120080610G5347                CARGO TRACK                             BOEING737   737448      13844BUNM                                                               CARGO BAY       CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSPECTION, FOUND CORROSION IN THE AFT CARGO COMPARTMENT LT TIE DOWN TRACK LBL 17.20 FROM STA 727B - STA 727E.  PARTICULARLY IN FASTENER HOLE UPPER AND LOWER SURFACE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000391    120080620G5320141A5505        FLOOR SUPPORT                           BOEING737   73783N      13844HINM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39318TZ                       28247                                   (REF DU4R2008219) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN STA 344, BL-0 TO BL-12L.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000392    120080613G5320                FLOOR SUPPORT                           BOEING737   737448      13844BUNM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   (REF DU4R2008216) DURING SCHEDULED INSPECTION, FOUND CORROSION ON UPPER SURFACE OF FLOOR SUPPORT BEAM BS 328, RBL-16 TO RBL-60.  S/O NR 312001, OPS NR 24738.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000393    120080613G5311                FRAME                                   BOEING737   737448      13844BUNM                                                               FUSELAGE        DAMAGED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   (REF DU4R2008217) DURING SCHEDULED INSPECTION, FOUND DOUBLE-DRILLED HOLE ON MAIN FRAME UPPER CAP AT BS 986.5 AT FLOOR LEVEL RT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000394    120080620G5320141A5410        FLOOR SUPPORT                           BOEING737   73783N      13844HINM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39318TZ                       28247                                   (REF DU4R2008220) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN. STA 340, LBL 11.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000395    120080623G5230                SKIN                                    BOEING737   73783N      13844HINM                                                               AFT CARGO DOOR  DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39304TZ                       30675                                   (DU4R2008221) DURING SCHEDULED INSPECTION, FOUND AFT CARGO DOOR EXT SKIN HAS DENT 11 INCHES AFT FROM FWD EDGE 5 INCHS UP FROM BOTTOM EDGE WIDTH OF DENT 1.25 INCHES OF DENT .070 INCH W/Y=17 DENT MEASURES WITH DEPTH GUAGE A-1979.  S/O NR 245010, OPS NR 26681.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000396    120080623G5230                SKIN                                    BOEING737   73783N      13844HINM                                                               FWD CARGO DOOR  DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39304TZ                       30675                                   (REDF DU4R2008222) DURING SCHEDULED INSPECTION FOUND DENT IN EXT SKIN OF C-1 DOOR 25 INCH DOWN FROM TOP EDGE OF DOOR AND 22 INCHES AFT FROM FWD EDGE OF DOOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000397    120080624G5230                SKIN                                    BOEING737   73783N      13844HINM                                                               AFT CARGO DOOR  DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39304TZ                       30675                                   (DU4R2008223) DURING SCHEDULED INSPECTION, FOUND DENT IN AFT CARGO DOOR (C-2) EXT. SKIN.  S/O NR 245010, N/R 26678.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
             20080718     NM  2008       7          18         2008FA0000398    120080630G5340                NUT CLIP                                BOEING737   73783N      13844HINM                                                               BS 967          CHAFED          B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   (DU4R2008225) DURING SCHEDULED INSP, FOUND AFT CABIN BS 967, RBL 24, TO LBL 49 FLOORBOARD ATTACH POINTS, CLIP NUTS HAVE WORN GROOVES/CHAFE MARKS. S/O NR 245010, N/R NR27070 (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
             20080718     NM  2008       7          18         2008FA0000399    120080630G5315                FLOORBEAM                               BOEING737   73783N      13844HINM                                                               BS986           CORRODED        B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   (DU4R2008226) DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN WET AREA ON FLOORBEAM FASTENERS AND FASTENER HOLES AT BS 986 FORM RBL45 TO LBL 45.  S/O 245010 , N/R 27072  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000400    120080630G5512                SKIN                                    BOEING737   73783N      13844HINM                                                               LT HORIZ STAB   DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39308TZ                       28244                                   (REF DU4R2008227) DURING SCHEDULED INSPECTION, FOUND OUT OF LIMITS DENT IN LT HORIZ STAB L/E STA 280.  S/O 245008, N/R 21578  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000401    120080630G5512                SKIN                                    BOEING737   73783N      13844HINM                                                               HORIZ STAB      DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39308TZ                       28244                                   DURING SCHEDULED INSPECTION, FOUND DENT IN LT L/E OF HORIZ STAB STA 105.  S/O 245008,  N/R 21591.  S/O 245008, N/R 21591.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
             20080715     NM  2008       7          15         2008FA0000402    120080630G5315                FLOORBEAM                               BOEING737   73783N      13844HINM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39318TZ                       28247                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON AFT CABIN FLOORBEAM, BS947, RBL 5 TO LBL5. S/O 245009, N/R 26378 (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
             20080715     EA  2008       7          15         2008FA0000403    220080616G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          OUT OF POSITION B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07987AP                       172S10710                               CHECKED THE MAGNETO TIMING AND FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES.  CURRENTLY SET AT APPROX 30 DEGREES BEFORE TOP DEAD CENTER. MFG SPEC IS 25 DEGREES BTDC. THE AIRCRAFT ENGINE TO MAGNETO TIMING WAS CHECKED WHEN NEW, SHORTLY AFTER DELIVERY 4/14/2008- 3.5 HRS TIS AND FOUND OK.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE ADVANCED POSITION.  ORANGE FACTORY PUTTY NOTED ON MAGNETO HOLDOWN NUTS. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE ADVANCED POSITION IN 80 HRS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH MFG.  SB SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE.                     1H71 3O3  ONT3A12    1E10                 
             20080715     EA  2008       7          15         2008FA0000404    220080617G7414M3820           DISTRIBUTOR BLK SLICK                   CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                              MAGNETO         MISREPAIRED     B  Z08RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE07658PW           08011866    18282098                                DURING INTERNAL MAGNETO INSPECTION, FOUND DISTRIBUTOR BLOCK SPOT FACED AREA FOR POLES.  APPEARS TO BE INCORRECTLY SPOT FACED.  MATERIAL THAT WAS LEFT BEHIND HAS THE SAME LOFT AS BEARING BOSS AREA ON DISTRIBUTOR BLOCK.  THIS CAUSES THE FINGER ON THE DISTRIBUTOR GEAR TO RUB ON THE DISTRIBUTOR BLOCK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A13    1E4                  
             20080715     EA  2008       7          15         2008FA0000405    220080616G7414                MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          OUT OF POSITION B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07227BH                       172S10662                               DURING A PHASE 2 (100 HR) CHECK THE MAGNETO TIMING AND FOUND THE RT MAGNETO ADVANCED TO APPROXIMATELY 27 DEGREES.  MFG SPECS CALL FOR 25 DEGREES.  LAST CHECK AT 90 HOURS PRIOR, FOUND TO BE OK.  SUSPECT MAGNETO DRIFTING IS OCCURING.  THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH ENGINE AND MAGNETOS.  SB SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE.  (K)                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    1E10                 
             20080715     EA  2008       7          15         2008FA0000406    220080611G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              POWERPLANT      OUT OF POSITION B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07712DS98                     172S10711   L3404451                    DURING THE AC FIRST PHASE 2 INSPECTION (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROXIMATELY 5 DEGREES.  CURRENTLY SET 30 DEGREES BEFORE TOP DEAD CENTER PLUS (MFG SUM SAYS 25 DEGREES BTDC) THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, SHORTLY AFTER DELIVERY 4/25/2008, 4.3 HRS TIS.  IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITION.  ORANGE PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE ADVANCED POSITION IN 93 HOURS TIS.  THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH MFG OF ENGINE AND MFG OF MAGNETO SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS C1H71 3O3  ONT3A12    1E10                 
             20080715     EA  2008       7          15         2008FA0000407    220080611G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                                              OUT OF POSITION B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07712DS                       172S10711   L3404451E                   DURING THE AC FIRST PHASE 2 INSP (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET 30 DEGREES BEFORE TOP DEAD CENTER PLUS MFG SRM SAYS 25 DEGREES BTDC).  THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, SHORTLY AFTER DELIVERY  4/25/2008. 4.3 HOURS TIS.  IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITION. ORANGE PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE ADVANCED POSITION IN 93 HRS TIS.  THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH ENGINE MFG AND MAGNETO MFG, SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS CASE.  (K)         1H71 3O3  ONT3A12    1E10                 
             20080715     SO  2008       7          15         2008FA0000408    120080528G32463080D           WHEEL                                   PIPER PA23  PA23250     7102308SO  LYC   O540  IO540*      41532EA                              LT MLG          CORRODED        C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO27959C                        278154029                               DURING A ROUTINE INSPECTION THE AMT ENCOUNTERED DIFFICULTY WHILE REMOVING THE LT MAIN GEAR WHEEL ASSEMBLY AXLE RETAINING NUT.  HE STOPPED AND DEFLATED THE TIRE.  THE WHEEL WAS THEN REMOVED EASILY. FOLLOWING REMOVAL THE WHEEL WAS FOUND TO BE SEVERELY CORRODED AND ALL BUT ONE WHEEL-HALF RETAINING BOLT HAD FAILED.  THE LOG BOOK ENTRY INDICATED THAT THE WHEEL HAD LSAST BEEN DISASSEMBLED 217 HOURS AGO. (K)                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  1A10    1E4                  
             20080715     SO  2008       7          15         2008FA0000409    120080607G243432C22491        ALTERNATOR                              PIPER PA32  PA32R301    7103218SO  LYC   O540  IO540K1G5   41532EA                                              DAMAGED         D      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                NRNOT REPORTED   1                      EA1330969                       3246230     L3047448A                   4 SCREWS THAT HOLD THE RECTIFIER PLATE INTO THE BACK CASE OF ALTERNATOR CAME LOOSE AND CONTACTED THE ROTOR, DESTROYED ALTERNATOR. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  A3SO    1E4                  
             20080715     EA  2008       7          15         2008FA0000410    220080527G72503013411         TURBINE                                 AYRES S2    S2RT34NORMAL0970106SO  PWA   PT6   PT6A34      52043EA                              ENGINE          DAMAGED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW113105E1026                   T34177      PCE56299                    06/20/2008 REPORT: ON 5/27/08 AC UNDER LOAD IN TURN EXPERIENCED ENGINE FAILURE RESULTING IN ACCIDENT.  LOUD BANG! ENGINE QUIT.  CT TURBINE TEETH MISSING, NR 2 BEARING DESTROOYED.  1026.1 HOURS ON PMA BLADES PQ0812NE. (K)(NTSB: DFW08CA155)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3T4  T  A3SW    E4EA                 
             20080715     CE  2008       7          15         2008FA0000411    120080612G3230                ROD END                                 CESSNA310   T310Q       2074244CE  LYC   O360  IO360A1A    41514EA                              LANDING GEAR    BROKEN          G      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      EA397044Q                       T310Q0204                               AFTER TAKEOFF, WHEN RETRACTING GEAR, PILOT HEARD LOUD CRACK.  NOSE GEAR WOULD NOT RETRACT.  AIRCRAFT LANDED WITH NOSE GEAR TRAILING AFT.  NOSE GEAR COLLAPLSED ON LANDING.  INSPECTION REVEALED ROD END UNDER PILOT`S FLOOR THAT CONNECTS NOSE GEAR RETRACT ROD TO BELLCRANK SEPARATED CAUSING NOSE GEAR TO BECOME DISCONNECTED FROM LANDING GEAR TRANSMISSION.                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  3A10    1E10                 
             20080717     NE  2008       7          17         2008FA0000412    220080528G7510101910026191    CONTROL ARM                             BEECH 200   B200        1152922CE  PWA   PT6   PT6A42      52043NE                              LT NACELLE      WORN            B  CWNRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP096604L100                    BB1121                                  LT ENGINE NACELLE ICE-VANE CONTROL ARM HAD WORN OUT OR DESTROYED BUSHINGS AT ALL 3 ACTUATING CONTROL ARM DRIVE POINTS AND LINKS, CAUSING POTENTIAL FOR F.O.D. TO ENGINE.  WHEN ICE VANE IS IN THE RETRACTED POSITION THERE ARE NO HARD STOPS TO KEEP IT FROM VIBRATING. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4T4  T  A24CE   E4EA                 
             20080715     GL  2008       7          15         2008FA0000413    320080423G611405522311        BULKHEAD                                CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA  MCAULY1A170 1A170E      GL  PROPELLER       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA23897LP570                    172S8897                                REPEATED FINDINGS OF CRACKS AT EDGE OF WASHER FOOT PRINT.  ALLOY CHANGE, OR HARDWARE CHANGE MAY HELP. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    1E10    5  NP857     
             20080715     EA  2008       7          15         2008FA0000414    220080701G7310RSA5AD1         INJECTOR                                CESSNA182   182T        2072703CE  LYC   O540  TIO540AK1A       EA                              FUEL SERVO      CLOGGED         G      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      EA23101LP569                    T18208265   L1165861A                   PLANE LOST ENGINE POWER, BECAME VERY LEAN, COULD NOT GET FUEL FLOW> 9 GPH. TURNED OUT TO BE ALUMINUM SHAVING FROM ORIGINAL MFG OF FUEL SERVO.  CLOGGED MIXTURE HOLE INSIDE FUEL SERVO.  THIS WAS A DEFECT FROM TIME OF MANUFACTURE OF FUEL SERVO.  EMERGENCY LANDING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A13                         
             20080718         2008       7          18         2008FA0000415    220080505G7414S6LSC204T       MAGNETO                                 BEECH 58    58          1152740CE                                                               ENGINE          FAILED          B  NW4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15142DR4                      TH1458                                  SMOKE WAS REPORTED IN COCKPIT.  UPON INVESTIGATION, FOUND PIN HOLE CORRODED IN METAL LINE CLOSE TO AIR CONDITIONER BLOWER MOTOR. ALCOHOL SOAKED INSULATION NEAR FRONT BULKHEAD.  BURNED SOME INSULATION AND AIR CONDITION FILTER HAD HOLE BURNED IT ALSO.  WAS UNABLE TO FIND LEAK WITHOUT LINE REMOVAL AND PRESSURE TEST.  CONTACT POINT PN 10-382585 WAS FOUND IN MAGNETO.  POINT CONTACT SURFACE WAS DEBONDED FROM BASE.  RESULT WAS FAILED MAGNETO.  FOR INFO ONLY - TO SEE IF MORE BREAKER POINTS SHOW SAME TYPE OF FAILURE MAY BE MFG PROCESS. (K)                                                                                                                                                                                        1L72 3O      3A16                         
             20080715     SO  2008       7          15         2008FA0000416    120080609G5720494718          TAPE                                    PIPER PA28  PA28161     7102803SO                                                               WING            PEELING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE028369A                       288116198                               STUDENT PILOT DECLARED AN EMERGENCY AS HE THOUGHT NOISE HE WAS HEARING WAS HIS ENGINE COMING APART.  AFTER SAFELY LANDING IT WAS FOUND THAT THE NOISE WAS THE ANTI-SLIP WINGWALK MATERIAL SLAPPING THE WING, IN THE SLIP STREAM.  WIND GOT UNDER THE MATERIAL AND LIFTED UP A SECTION OF IT, PEELING IT BACK ENOUGH TO MAKE THE "SLAPPING- BANGING" NOISE HE HEARD.  REMOVED THE OLD WING WALK MATERIAL AND INSTALLED NEW PIECE.  (K)                                                                                                                                                                                                                                                                                                           1L71 3O      2A13                         
             20080715     SO  2008       7          15         2008FA0000418    120080628G3246                WHEEL                                   PIPER PA23  PA23250     7102308SO  LYC   O540  IO540*      41532EA                              RT MLG          BROKEN          D  PP4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39959C 217                    278154029                               DIFFICULTY WAS ENCOUNTERED WHILE AN AMT WAS REMOVING THE RETAINING NUT FROM THE AXLE ON THE RT MAIN GEAR OF AC.  HE STOPPED  AND DEFLATED THE TIRE. THE WHEEL ASSEMBLY WAS THEN REMOVED WITHOUT RESISTANCE.  AFTER REMOVAL ALL BUT ONE OF THE ASSEMBLY RETAINING BOLTS WERE FOUND BROKEN AND THE WHEEL HALVES WERE ALSO BROKEN.  CORROSION CAUSED THE PROBLEM.  THE WHEEL HAD ACCUMULATED 217 HOURS SINCE IT WAS LAST DISASSEMBLED AND INSPECTED.  TT ON THE WHEEL IS UNKNOWN.  THE ENTIRE WHEEL ASSEMBLY WAS REPLACED.  (K)                                                                                                                                                                                                                    1L72 3O3  O  1A10    1E4                  
             20080715     GL  2008       7          15         2008FA0000419    120080618G5210DA4522100002    DOOR                                    DIAMONDA40  DA40        2990002GL                                                               REAR PAX DOOR   DEPARTED        G      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           TOTAKEOFF        1                      WP28686US615                    40640                                   ON TAKE-OFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000420    120080618G5344                HINGE                                   DIAMONDA40  DA40        2990002GL                                                               DOOR            CRACKED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP28686US                       40640                                   FOUND CRACKS IN AFT DOOR HINGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000421    120080618G5210DA4522100002    DOOR                                    DIAMONDA40  DA40        2990002GL                                                               REAR PAX DOOR   DEPARTED        G      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           TXTAXI/GRND HDL  1                      WP28605US225                    40675                                   WHILE TAXIING INOT TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000422    120080616G5210DA4522100002    DOOR                                    DIAMONDA40  DA40        2990002GL                                                               AFT PAX DOOR    DEPARTED        G      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      WP28605US536                    40675                                   ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000424    120080616G5210DA4522100002    DOOR                                    DIAMONDA40  DA40        2990002GL                                                               REAR PASSENGER  DEPARTED        G      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      WP28605US                       40675                                   ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O    NTA47CE                        
             20080715     GL  2008       7          15         2008FA0000426    120080618G5344                HINGE                                   DIAMONDA40  DA40        2990002GL                                                               DOOR            CRACKED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP28686US                       40640                                   FOUND CRACKS IN AFT DOOR HINGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O    NTA47CE                        
             20080717     NM  2008       7          17         2008FA0000427    120080601G275118195816        TRANSMITTER                             BOEING767   767241      1385115NM  GE    CF6   CF680C2*         GL                              FLAP POSITION   FAULTY          W  TAMFA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SO23770QT                       23802                                   LT FLAP DID NOT MOVE FROM 1 TO UP POSITION. FLIGHT RETURNED TO DEPARTURE.  REMOVED AND REPLACED PROXIMITY SENSORS S282 AND S283 IAW SWPM 20-30-12 AND AMM 27-88-01, BITE TEST PSEU WAS PERFORMED AND IT WAS FOUND NORMAL IAW FIM 32-09-03, FIG 103. FLAP POSITION TRANSMITTER NR 5 WAS REMOVED AND REPLACED IAW MM 27-51-45, PG 201-222, OPS CHECK NORMAL, OVERWEIGHT LANDING INSPECTION WAS ACCOMPLISHED IAW MM 05-51-35 PHASE I, OPTION A, PG 201-203, NO DAMAGES WERE FOUND.  (K)                                                                                                                                                                                                                                                            2L72 4F4  FRTA1NM    E23EA                
             20080718         2008       7          18         2008FA0000428    420080610G3420                LIGHT                                   BOEING767   767241      1385115NM  GE    CF6   CF680C2*         GL                              ALTITUDE INDICATILLUMINATED     W  TAMFO   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SO23770QT                       23802                                   CABIN ALT AND CABIN ALTITUDE LIGHTS ILLUM, EICAS MSG CABIN ALTITUDE WAS DISPLAYED.  UNABLE TO RESTORE CABIN PRESS USING MANUAL MODE. AIRPLANE RETURNED TO DEPARTURE. IAW FIM 21-31-00, FIG 103 BLOCKS 1,2,22,23,23A, 24, 44, PLN U3 IN CONNECTOR D2712A WAS REPAIRED. REF WDM 21-31-11/21-31-21.  TEST WITH AIRCRAFT PRESSURIZED ON GROUND IS SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA1NM    E23EA                
             20080717     CE  2008       7          17         2008FA0000429    120080605G322266420003        PISTON                                  CESSNA500   560CESSNA   2076750CE                                                               NLG             LOOSE           B  CWQRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL05351QS1556                   5600451                                 ( REF CWQR200801)  DURING A1-5 PHASE INSPECTION, FOUND EXCESSIVE PLAY INT HE NOSE GEAR FWD AND AFT PLAY CHECK.  AFTER FURTHER INSPECTION , FOUND THE NOSE GEAR FORK LOOSE ON THE PISTON. THEN THE SAFETY BOLT WAS REMOVED THE FORK FELL FROM THE PISTON.  THIS SHOULD BE AN INTERFERENCE FIT.  THIS IS A LOW TIME AC AND APPEARS TO BE A MFG PROBLEM.  FILED SCR NR 363222 WITH MFG. (K)                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA22CE                        
             20080717     EA  2008       7          17         2008FA0000430    120080625G32307455025         CONTROL PANEL                           CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF34*       30015NE                              MLG             MALFUNCTIONED   B  RO3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE03614BA1176                   5614                                    LANDING GEAR HANDLE DIFFICULT TO ACTUATE TO UP POSITION.  REQUIRED MULTIPLE ATTEMPTS TO ACTUATE GEAR HANDLE.  FOUND LIGHTED COVER PANEL LOOSE ON GEAR HANDLE ASSEMBLY.  REMOVED LIGHT PANEL TO INVESTIGATE.  FOUND ONE SCREW FROM BACKSIDE OF PANEL HAD FALLEN OUT AND WAS INTERFERING WITH GEAR UP RELEASE MECHANISM.  REINSTALLED SCREW AND TIGHTENED ALL OTHERS .  REINSTALLED LIGHT PANEL. PREFORMED MULTIPLE GEAR SWINGS, NO FAULTS NOTED.  (K)                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA                        
             20080718     NM  2008       7          18         2008FA0000431    120080630G5320715K9004507     ANGLE                                   BOEING717   717200      1383700NM                                                               BS 26           CRACKED         A  MWEAO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13970ME                       65171                                   RT UPPER BUCKET, FWD OB Z-FRAME IS CRACKED AT STA 26 APPROXIMATELY 1 INCH LONG.  FABRICATED AND INSTALLED ANGLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    TRA6WE                         
             20080717     CE  2008       7          17         2008FA0000432    120080602G3260602EN166B       DOWNLOCK SWITCH                         CESSNA501   551         2076605CE  PWA   JT15  JT15D4      52112NE                              RT MAIN GEAR    INOPERATIVE     B  UPWRO   OTHER                                                                                           P  NO WARNING INDICATION                                                         LDLANDING        1                      GL03502CL                       5510002                                 RT MAIN GEAR GREEN INDICATOR DID NOT ILLUMINATE WHEN GEAR EXTENDED GOING INTO LAND.  CYCLED GEAR AND GREEN INDICATOR LIGHT REMAINED OUT.  AC LANDED WITHOUT INCIDENT.  RT MAIN GEAR DOWNLOCK SWITCH FOUND TO BE FAULTY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4F4  F  A27CE   E1NE                 
             20080717     EA  2008       7          17         2008FA0000433    120080521G275160093000123     ASYMMETRY SWITCH                        CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        FAILED          D      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CE21779AZ                       5176                                    FLAPS FAIL FOUR DEGREES AFTER SELECTION.  USING BREAKOUT BOX, SELECTED THIS BDU AND FLAPS WOULD CONSISTENTLY FAIL. SELECTED OTHER SIDE BDU AND FLAPS WOULD OPERATE NORMALLY.  UNIT ALSO RATTLES ON BENCH WHEN CHECKING DRAG TORQUE (UNLOCKED).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
             20080717         2008       7          17         2008FA0000434    120080605G2560                RELEASE MECH                                                                                                                            SEAT BELT       FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP25                                                                    SEAT BELT WILL RELEASE WITHOUT PULLING ON THE RELEASE BUCKLE.  DURING FLIGHT THE SEAT BELT CAME UNDONE WITHOUT ANYONE PHYSICALLY UNLATCHING THE BELT.  CAUSE WAS DUE TO DEFECTIVE LATCH MECHANISM.  ALL BELTS WITH CERTAIN BATCH NUMBERS ARE DEFECTIVE.  (1-954/784-3178 MFG) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
             20080717     NM  2008       7          17         2008FA0000435    120080627G3213656174010       CYLINDER        BOEING                  BOEING737   7373B7      1384580NM                                                               MLG             CRACKED         B      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      WP07514AU           XC92439     23700                                   AFTER AIRCRAFT TOW, FLUID WAS OBSERVED LEAKING FROM .5 INCH CRACK (APPROXIMATE) IN THE OUTER CYLINDER OF THE LT MLG SHOCK STRUT.  THE CRACK IS LOCATED APPROXIMATELY 26 INCHES BELOW THE SHOCK STRUT AIR VALVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
             20080717     SO  2008       7          17         2008FA0000436    220080506G8530SA52006A1       CYLINDER                                BEECH 35    V35         1151538CE  CONT  O520  IO520BA     17032SO                              NR 4            CRACKED         B  BJFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA232024W                       D8078       241723R                     CRACK VISIBLE AT NR 4 CYLINDER. CRACK APPEARS TO START AT CASTING ANOMALY, CONTINUES TO EDGE OF FINS, AND IS VISIBLE AT THE FIRST FOUR COOLING FINS. ALSO VERIFIED, THROUGH USE OF EDDY CURRENT, THAT THE CRACK CONTINUES TO THE SPARK PLUG HOLE. ALL OTHER CYLINDERS HAVE SIMILAR CASTING ANOMALIES WITH INDICATIONS OF DISCONTINUITIES FOUND WITH EDDY CURRENT EQUIPMENT. THIS FACILITIES OPINION IS THAT POOR CASTING TECHNIQUES BY THE MFG LEFT STRESS POINTS FOR THE FORMATION AND CONTINUATION OF CRACKS, AND MORE THAN LIKELY, ANY CYLINDER NOT YET CRACKED, PROBABLY WILL. (K)                                                                                                                                                          1L71 3O3  O  3A15    E5CE                 
             20080717         2008       7          17         2008FA0000437    420080618G221131B641          TRIM SWITCH                             BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              CONTROL WHEEL   FAILED          B  QPIDO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19362MC           3188E       LJ760                                   AFTER INSTALLATION OF NEW MFG AUTOPILOT SYS, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND RETURNED TO MFG. MFG TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. SWITCHES IN ASSY FAILED ALLOWING BOTH UP & DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY MFG, WAS REPLACED & COMPUTER REPAIRED & REINSTALLED.  TRIM CIRCUITRY FAILED AGAIN AFTER 3 HOURS OF FLT.  COMPUTER REPAIRED & REINSTALLED. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT.  COMPUTER REMOVED FOR REPAIR & TRIM SWITCH CONFIRMED TO BE CAUSING FAILURE AGAIN. TRIM UP SWITCH STUCK I1L72 3T4  T  3A20    E4EA                 
             20080717     CE  2008       7          17         2008FA0000438    120080630G2910605700311       HOSE                                    LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              HYD SYSTEM      FAILED          E  JBGAO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW11260AN5025                   124         PCECA0083                   PILOT REPORTED A LOSS OF HYDRAULICS DURING FLIGHT AT CRUISE FL400.  INSPECTION REVEALED THAT THE RT ENGINE DRIVEN HYDRAULIC PUMP, PRESSUE SIDE HYDRAULIC LINE WAS LEAKING, AND ALLOWED THE AIRCRAFT`S HYDRAULIC SYSTEM FLUID TO BE DEPLETED.  FURTHER INSPECTION REVEALED THAT THE LINE HAD FAILED INTERNALLY AND WHEN PRESSURE WAS APPLIED THE HOSE WOULD SWELL AND BEGIN TO LEAK.  THE PROBABLE CAUSE OF THE FAIURE IS AGE AND POSSIBLE EMBRITTLEMENT OF THE HOSE.  TO POSSIBLY PREVENT RECURRENCE OF SUCH FAILURES AT TIME INTERVAL FOR REPLACEMENT OF AGEING TEFLON HOSES MAY BE NEEDED.  (K)                                                                                                                                               2L72 4F4  FRTA10CE   E35NE                
             20080717     GL  2008       7          17         2008FA0000439    120080701G2430                BEARING CAP                             CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO  HARTZLHCJ3Y PHCJ3YF1    GL  ALTERNATOR CASE CRACKED         B  YD5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL15391CP           1042440     3072        691753      FP6720B         PILOT REPORTE TO HAVE AN ALTERNATOR NR 1 FAILURE DURING GROUND PRE-FLIGHT RUN-UP.  AC WAS BROUGHT IN FOR MAINTENANCE TO TROUBLESHOOT ALTERNATOR ISSUE. ALTERNATOR BEARING END CAP WHICH IS PART OF THE ALTERNATOR CASE COMPLETED CRACKED OFF AND WAS LYING ON THE ENGINE BAFFLING.  AC WAS FURTHER INSPECTED WITH NO OTHER DISCREPANCIES FOUND. ALTERNATOR WAS REPLACED WITH NEW.  GROUND AND FLIGHT TESTS CHECK GOOD. (K)                                                                                                                                                                                                                                                                                                                      1L71 3O3  ONTA00009CHE3SO    5  CP36EA    
             20080717     SW  2008       7          17         2008FA0000440    120080610G6720206011725001    ROD                                     BELL  206   206L3       1182108SW  ALLSN 250C  250C30      03013GL                              T/R PITCH       CHAFED          B  ULXRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP01600W                        51250                                   DURING AN INSPECTION OF THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206001763001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206011725001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 206011722105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD.  THE MM DOES NOT TELL YOU WHICH WAY TO INSTALL THE ROD, HOWEVER ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK.  PLEASE SEE BHT 206L SERIES IPB, FIG 64-1 AND FIG 67-12 AND BHT 206L MM, PARA 67-63, FIG 67-17 DETAIL D. PARA 64-20 AND FIG 64-14.  THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE BELLCRANK AND THE RIVETED END CONNE1G71 3U3  U  H2SW    E1GL                 
             20080717     GL  2008       7          17         2008FA0000441    220080604G723023009670        BEARING                                 BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              COMPRESSOR      FAILED          B      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SO053WV             CAC45603    53713       CAE847787                   PILOT REPORTED ENGINE CHIP LIGHT PRECAUTIONARY LANDING MADE TO INVESTIGATE. A CONSIDERABLE AMOUNT OF FERROUS MATERIAL WAS ON THE TOP AND BOTTOM CHIP DETECTORS.  NO PENALTY RUNS WERE PERFORMED. AIRCRAFT WAS PLACED ONTO A TRAILER AND MOVED BACK TO BASE WHERE THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR INVESTIGATION.  THE DISMANTLE AND INVESTIGATION REVEALED THE NR 2 BEARING THAT SUPPORTS THE REAR OF THE IMPELLER HAD FAILED. THE BALL BEARING KEEPER HAD FRACTURED COMPLETELY ACROSS THE SURFACE. AT LEAST ONE OF THE BALLS HAD SPALLED AND ALSO THE OUTER RACE HAD SEVERAL AREAS OF SPALLING.  THE FAILED BEARING WAS REPLACED, THE REMAINDER OF THE ENGINE OIL SYSTEM WAS FLUSHED WITH NO DISCREPANCIES NOTED.  E1G71 3U3  UO H2SW    E1GL                 
             20080717         2008       7          17         2008FA0000442    120080701G3610AS18954175      COUPLING                                                                   CFMINTCFM56 CFM567B26US      NE                              ENGINE DUCT     MISSING         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA33                                        894464                      DURING GROUND RUN AFTER INSTALLATION, HOT AIR ESCAPED FROM THE NOSE COWL ANTI-ICE DUCT AT THE 12 O`CLOCK POSITION CAUSING THERMAL DAMAGE TO THE C-DUCT THERMAL BLANKETS AND TRUST LINK TEFLON WASHERS.  INVESTIGATION FOUND DUCT COUPLING PN AS1895-4-175 MISSING.  ENGINE WAS RELEASED FOLLOWING MAINTENANCE TO RECTIFY HIGH OIL PRESSURE INDICATIONS IN FEB 2008.  (K)                                                                                                                                                                                                                                                                                                                                                                               4  F          E00055EN             
             20080717     EA  2008       7          17         2008FA0000443    220080617G8530                GUIDE                                   CESSNA210   T210N       2073456CE  CONT  O550  IO550P      17216EA                              EXHAUST VALVE   OUT OF TOLERANCEC  B3ORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW036621A                       21063559                                AFTER NUMEROUS ATTEMPTS TO TROUBLESHOOT FREQUENT ENGINE MISFIRES OCCURRING PRIMARILY IN THE INITIAL CLIMB STAGES OF FLIGHT, THE ENGINE VALVE TRAIN WAS INSPECTED FOR STICKING VALVES.  DIMENSIONAL INSPECTIONS OF THE EXHAUST VALVE GUIDES IN ALL 6 CYLINDERS REVEALED THAT THE EXHAUST VALVE GUIDES WERE BELOW THE MINIMUM ACCEPTABLE DIAMETERS AS PUBLISHED IN THE APPLICABLE O/H MANUAL.  IT IS BELIEVED THAT THE EXCESS MATERIAL EXISTS BECAUSE THE GUIDES WERE NOT MEASURED OR REAMED DURING THEMFG ASSY PROCESS.  CORRECTIVE ACTION NOT AVAILABLE AT THIS TIME.  (K)                                                                                                                                                                      1H71 3O3  O  3A21    E3SO                 
             20080717         2008       7          17         2008FA0000444    420080609G6113                BULKHEAD                                CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              PROP SPINNER    CRACKED         B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03537SP                       172S8393                                DURING A 100 HR INSPECTION, PROPELLER SPINNER FWD BULKHEAD WAS FOUND TO BE CRACKED FROM A PROP BOLT HOLE OUT TOWARD THE OUTER EDGE OF THE BULKHEAD, APPROX 1.5 INCH LONG. THE PROP BOLTS AND THE BULKHEAD WERE REMOVED FRO THE AIRCRAFT.  CLOSER INSPECTION SHOWED THE CRACK ORIGINATED FROM THE OUTER APEX OF THE WASHER MARK, NOT THE BOLT HOLE ITSELF.  ALSO, ALL BOLT HOLES WERE FOUND TO BE CRACKED IN THE SAME LOCATION (OUTER APEX OF WASHER IMPRESSION), RANGING FROM .2500 TO 1.0 IN LENGTH.  THE MM HAS A NOTE THAT SAYS, "THE MOUNTING BOLT HOLES IN THE FORWARD BULKHEAD MAY BE UNDERSIZED DUE TO THE ORIGINAL TORQUING OF THE MOUNTING BOLTS".  IT IS PLAIN TO SEE THIS CRUSHES THE ALUMINUM, CASUING STRESS CONCENTRATIONS AROUND 1H71 3O3  ONT3A12    1E10                 
             20080717     CE  2008       7          17         2008FA0000445    120080611G52101014300329      PIN                                     BEECH B300  B300        1159232CE  PWA   PT6   PT6*        52043EA                              PAX DOOR        MISSING         B  XA14O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW1710TX 3132                   FL1                                     UPPER AFT ENTRANCE DOOR BAYONET SHIFTED OB .7500 INCH CAUSING AC TO DEPRESSURIZE.  THIS WAS CAUSED BY A PIN (PN 101-430032-9) FALLING OUT OF PLATE (101-4300323) CAUSING ROLLER (PN 50-430037-7) TO FALL OUT.  THIS CAUSED ROD (PN 50-430016-11) WITH BOLT (PN 50-430177-5), (ASSY CALLED A DOOR BAYONET), TO SHIFT OUTBOARD .7500 INCH THROUGH AFT DOOR FRAME (PN 50-430032-3 INSTALLED 180 DEGREE OUT.  THE PINS THAT HOLD THE ROLLERS IN PLACE ARE STAKED.  IT LOOKS AS THOUGH OVER TIME THAT THE PIN WORE THE STAKES SMOOTH AND THUS ALLOWING PIN AND ROLLER TO FALL OUT..  STAKED PINS SHOULD BE CHANGED TO COTTER KEYED TYPE PINS TO KEEP THIS FROM HAPPENING ON OTHER AC.  CHECK MFG AND THESE HAVE THE COTTER PIN TYPE PINS.  (K)       2L72 4T3  TRTA24CE   E2NE                 
             20080717         2008       7          17         2008FA0000446    120080109G350080130700        CYLINDER                                                                                                                                                OUT OF TOLERANCEB  AY54O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35GEZJO                                                               OXYGEN CYLINDER (PN 801307-00, SN ST26121) ARRIVED AT WORKSHOP ON 9TH JAN, 2008, REMOVED OFF OF G-EZJO FOR HAVING LOW CONTENTS PRESSURE.  ON CLOSE INSPECTION, IT WAS DISCOVERED THAT THE CYLINDER NECK HAD BEEN MARKED WITH HIGH STRESS STAMPS.  CYLINDER LAST OVERHAULED BY AVOX.  IN THE RIN STAMP, THE NUMBER 1 CLEARLY SHOWS THAT THE INCORRECT STAMPS HAVE BEEN USED. (K)                                                                                                                                                                                                                                                                                                                                                                                                           
             20080717     GL  2008       7          17         2008FA0000447    220080529G725023073853        TURBINE WHEEL                                                              ALLSN 250C  250C20B     03013GL                              ENGINE          FAILED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05     1036                               CAT34953                    TURBINE ASSY RECEIVED FOR REPAIR DUE TO METAL IN OIL.  UPON DISASSEMBLY, IT WAS NOTED THAT THE 1ST STAGE TURBINE WHEEL BLADES WERE MISSING PIECES OF BLADE MATERIAL.  THE APPARENT IMBALANCE OF THE GP ROTOR ASSY PRODUCED BY THE MISSING BLADE PIECES CAUSED THE GP STATOR SEAL TO FRACTURE.  ONE PORTION OF THE STATOR SEAL BEGAN TO ROTATE WITH THE NR 8 BEARING OUTER RACE.  THE DOWNSTREAM PORTION OF THE STATOR SEAL BELOW THE FRACTURE REMAINED STATIONARY AND THE GRINDING BETWEEN THE STATIONERY PORTION OF THE SEAL AND THE ROTATING PORTION APPEARS TO BE THE SOURCE OF THE METAL.  THE TURBINE WHEEL BLADE TIPS APPEAR TO HAVE FAILED DUE TO HOT - CORROSION SULFIDATION AS DEFINED IN MFG CSL-1210.  SOME DOWNSTREAM PORTIONS OF TH       3  U          E4CE                 
             20080717     NE  2008       7          17         2008FA0000448    220080618G72501975M56G03      NOZZLE                                  BOEING777   777224      1385225NM  GE    GE90  GE9092B     30036NE                              ENGINE          FAILED          B  QEMYO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35780083927717271             29478       900240                      ENGINE SUFFERED AN OVERTEMP AND HPC/HPT ROTOR VIBRATION EXCCEEDANCE.  THE CUSTOMER REPORTED METAL PARTICLES IN THE EXHAUST.  DURING ENGINE MODULE DISASSEMBLY AT MFG, IT WAS NOTED THAT THE HPT STAGE 2 NOZZLE ASSY EXHIBITED SIGNIFICANT HARDWARE DAMAGE TO THE NOZZLE SEGMENTS, STAGE 1 AND STAGE 2 SHROUDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTT00001SEE00049EN             
             20080718     SO  2008       7          18         2008FA0000449    120080701G53407955300         FITTING                                 PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              FUSELG TO WNDSHDCORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15602FT                       2841196                                 STEEL FITTINGS (PN 79553-00) LT AND (PN 79553-01(RT) WERE FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVAL, THOSE FITTINGS CARRY STRUCTURAL LOADS AND LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTION, PROBABLE CAUSE COULD BE DISSIMILAR METAL CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH KEEP MOISTURE IN, FOUND SAME PROBLEM IN OTHER AC.  (K)                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  2A13    E274                 
             20080717     SO  2008       7          17         2008FA0000450    120080701G53407955301         FITTING                                 PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              FUSLG TO WNDSHLDCORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15602FT                       2841196                                 STEEL FITTING FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVAL, THOSE FITTING CARRY STRUCTURAL LOADS AND LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTION, PROBABLE CAUSE COULD BE DISSIMILAR METAL CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH KEEP MOISTURE IN, I HAVE FOUND THE SAME PROBLEM IN OTHER AC.  (K)                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  2A13    E274                 
             20080718     GL  2008       7          18         2008FA0000451    120080609G7810                ELBOW                                   CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              RT EXHAUST      MISINSTALLED    G      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM04266SR                       2626                                    WHILE ACCOMPLISHING SERVICE ADVISORY 08-03 IT WAS DISCOVERED THAT RT SIDE EXHAUST ELBOW WHICH IS INSERTED BETWEEN WASTEGATE OUTLET FITTING AND TAILPIPE WAS ORIGINALLY INSTALLED BACKWARDS A THE FACTORY. THIS INCORRECT INSTALLATION RESULTED IN ELBOW HAVING ONLY A .1875 INCH ENGAGEMENT WITH WASTEGATE FITTING AND A 2.2500 INCH ENGAGEMENT IN TAILPIPE.  THE .3750 INCH ENGAGEMENT COULD HAVE RESULTED IN SEPARATION OF JOINT.  THE 2.2500 INCH ENGAGEMENT CAUSED A 1 INCH OBSTRUCTION IN EXHAUST GAS PATH.  (K)                                                                                                                                                                                                                           1L71 3O3  ONTA00009CHE3SO                 
             20080717     EU  2008       7          17         2008FA0000452    120080610G3411                PITOT TUBE                              AEROSPATR72 ATR72212    8680945EU  PWA   PW120 PW127            NE                                              OBSTRUCTED      D      C   ABORTED TAKEOFF                                                                                 P  NO WARNING INDICATION                                                         TOTAKEOFF        1                      EA21820FX                       248                                     ON TAKEOFF ROLL THE F/O AIRSPEED INDICATOR REMAINED AT ZERO.  THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE.  MAINTENANCE FOUND FOD (SPIDER) IN THE PITOT TUBE.  THE TUBE WAS CLEARED AND THE SYSTEM CHECKED GOOD.  THE AIRCRAFT WAS RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE                
             20080717     SO  2008       7          17         2008FA0000453    120080510G3220                BUNGEE                                  PIPER PA28  PA28R201T   7102813SO                                                               LT NOSE WHEEL   BROKEN          G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP119581C                       28R7803267                              THE PILOT SLOWED FOR LANDING AND DEPLOYED THE GEAR. A SAFE CONDITION WAS INDICATED FOR THE MAINS, BUT NOT  FOR THE NOSE. THE GEAR WAS CYCLED; HOWEVER AGAIN, NO SAFE NOSE INDICATION. AN EMERGENCY GEAR DEPLOYMENT WAS ATTEMPTED BUT STILL, NO GREEN NOSE LIGHT.  THE PILOT ASSUMED THAT DUE TO PREVIOUS PROBLEMS WITH THE LANDING GEAR INDICATOR LIGHTS THAT THE NOSE GEAR HAD PROBABLY DEPLOYED AND CONTINUED THE LANDING. IMMEDIATELY AFTER TOUCHDOWN, THE NOSE LANDING GEAR COLLAPSED.  POS INCIDENT INVESTIGATION REVEALED THE LT NOSE WHEEL BUNGEE ASSY; PN 76425-03 HAD BROKEN AND WEDGE IN THE NOSE LANDING GEAR PREVENTING EXTENSION. THE FAILURE APPEARS TO HAVE OCCURRED WHEN THE GEAR WAS IN THE RETRACTED POSITION.  (K)           1L71 3O      2A13                         
             20080718     CE  2008       7          18         2008FA0000454    120080630G551045A21085003     BRACKET                                 BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03184AR4512                   RK34                                    HORIZ STAB IB RIBS LT AND RT ROLLER BRACKETS FOUND CRACKED. REPLACED PN 45A21085-003 LT FWD BRACKET.  PN 45A21086-003 LT AFT BRACKET, PN 45A21085-004 RT FWD.  BRACKET PN 45A21086-004 RT AFT BRACKET WITH IMPROVED PN 128-620021-0001 (LT) AND PN 128-620021-0002 (RT) BRACKETS IAW MFG COMMUNIQU NR 83.  REPLACED PN 45A21146-005 RIB (LT) AND PN 45A21146-006 RIB   (RT) WITH IMPROVED PN 128-620022-0001 (LT) AND PN 128-620022-0002 (RT) RIBS IAW MFG COMMUNIQU NR 83. INSPECTION NEWLY INCORPORATED INTO MM 5-20-02 INSP GUIDE AND SECTION 55-30-00.  (K)                                                                                                                                                                               2H72 4F4  FRTA16SW   E25EA                
             20080718     CE  2008       7          18         2008FA0000455    120080626G2435M835366026L     RELAY                                   RAYTHN390   390         7150030CE                                                               STARTER GEN     STUCK           B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03404JM444                    RB167                                   INVESTIGATED PILOT REPORT OF RT ENG STARTER/GEN NOT DISENGAGING FROM START FUNCTION AFTER ENG START. FOUND 80K5 RT ENG START LATCH RELAY STUCK IN START FUNCTION.  RT STARTER/GEN TERMINAL COVER AND COOLING AIR INLET DUCT SHOW SIGNS OF OVERHEATING. INSPECTED STARTER/GEN, REPLACED 80K5 RELAY, STARTER/GEN FUNCTIONS NORMAL. HAVE REPLACED NUMEROUS 80K3 AND 80K5 START LATCH RELAYS IN 390 SERIES AC THAT HAVE FAILED WITH SHORT TIS. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A RELAY QC OR DESIGN/INSTALLATION ISSUE.  (K)                                                                                                                                                                                                              1L72 3F    RTA00010WI                     
             20080718     CE  2008       7          18         2008FA0000456    120080626G30205188001         VALVE                                   RAYTHN390   390         7150030CE                                                               ANTI ICE SYSTEM STUCK           B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03404JM                       RB167                                   REPLACED FAILED RT ENGINE ANTI-ICE VALVE WITH 0 TSOH VALVE ASSY SUPPLIED BY HBC/RAPID; O/H BY MFG, WO R73432, DATED 5/22/2008.  VALVE ASSY FAILED IN STUCK IN OPEN POSITION, WHEN INITIALLY TESTED FOLLOWING INSTALLATION.  REPLACED VALVE WITH ANOTHER RAPID-SUPPLIED VALVE ASSY, OPERATIONS NORMAL. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A QC ISSUE OR IF VALVE ASSY SUBJECTED TO HIDDEN INTERNAL DAMAGE DUE TO ROUGH HANDLING DURING SHIPPING.  (K)                                                                                                                                                                                                                                                                                     1L72 3F    RTA00010WI                     
             20080718     SO  2008       7          18         2008FA0000457    220080710G741407010003        MAGNETO                                 CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO                              LEFT            BURNED          D  GICRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01662AJ                       1632                                    DURING ROUTINE MAINT, THE LT MAGNETO WAS DISCOVERED OUT OF TIME TO ENGINE.  WAS UNABLE TO RE-TIME MAG WITHOUT RE-STABBING.  WHEN REMOVED, OPENED COVER AND FOUND INTERNAL PLASTIC COMPONENTS BURNED WITH SIGNIFICANT AMOUNT OF LOOSE (BURNED) PLASTIC PARTS LOOSE WITHIN MAGNETO.  THIS MAGNETO WAS SUPPLIED WITH NEW ENGINE 261.3 HOURS AGO, OTHER THAN MAG TO ENGINE TIMING BEING OFF, THERE WAS NO INDICATION (OPERATIONALLY) OF A PROBLEM.  THIS IS FIRST TIME HAVE SEEN THIS KIND OF DAMAGE TO MAGNETO AND HAVE IT STILL OPERATE.  PERFORM 500 HR INTERNAL INSP OF MAGS AND BEING HALF WAY THERE, IT THEORETICALLY WOULD NOT HAVE BEEN DISCOVERED UNTIL 500 HOUR MARK OR TOTAL FAILURE OF MAGNETO.  (K)                                    1L71 3O3  ONTA00009CHE1CE                 
             20080718     CE  2008       7          18         2008FA0000458    120080702G323050452112        FORK                                    CESSNA340   340A        2076405CE  CONT  O520  TSIO520*    17040SO                              MLG             FRACTURED       G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1760PP                        340A0073                                LANDING GEAR DOWN ACTUATION ON 7/2/2008 PRODUCED AN INDICATED UNSAFE NOSE LANDING GEAR LIGHT.  AN ATTEMPT TO ACTUATE MANUAL EXTENSION OF THE LANDING GEAR PROVED UNSUCCESSFUL SINCE THE NOSE LANDING GEAR DID NOT EXTEND TO A DOWN AND LOCKED POSITION.  SUBSEQUENT DAMAGE RESULTED TO THE AIRCRAFT WHEN THE NOSE LANDING GAR COLLAPSED UPON LANDING.  AN INSPECTION OF THE AC REVEALED THAT NLG LINKAGE "ADJUSTING FORK" FRACTURED THEREBY DISABLING THE EXTENSION OF THE NLG FROM EXTENDING TO A DOWN AND LOCKED POSITION.  EVIDENCE SUGGESTS THAT THE FRACTURE WAS PROGRESSIVE IN NATURE DUE TO INDICATIONS THAT A DEGRADATION TO THE STRUCTURE OF THIS COMPONENT EXISTED PRIOR TO FAILURE OF THIS COMPONENT. (K)                            1L72 3O3  O  3A25    E8CE                 
             20080718     SW  2008       7          18         2008FA0000459    120080701G2400102149          METER                                   BELL  206   206B        1181511SW  ALLSN 250C  250C20J     03013GL                                              MALFUNCTIONED   C  DDZRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE036BU  7003                   4034        CAE270422                   AC MAINT HOBBS METER FOUND RUNNING SLOW.  THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT.  THIS PROBLEM CAUSED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM.  PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WORN OUT.  RECOMMENDATION TO PREVENT THIS PROBLEM: MAINT HOBBS METER, TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE METER IS RUNNING PROPERLY. (K)                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H2SW    E4CE                 
             20080718     SW  2008       7          18         2008FA0000460    120080701G2400102149          METER                                   BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                                              MALFUNCTIONED   B  DDZRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0375TV 7845                   52095       CAE895710                   AC MAINT HOBBS METER FOUND RUNNING SLOW.  THIS PROBLEM CAUSES THE  ACTUAL TT OF THE AC TO BE INCORRECT.  THIS PROBLEM CAUSED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM.  PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WORN OUT.  RECOMMENDATION TO PREVENT THIS PROBLEM; MAINT, HOBBS METER TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE METER IS RUNNING PROPERLY.                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH2SW    E1GL                 
             20080718     NM  2008       7          18         2008FA0000461    120080703G5315                FLOORBEAM                               BOEING737   73783N      13844HINM  GE    CFM56 CFM56*      13802NE                              BS294           CORRODED        B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AROUND FASTENERS AT BS 294 FROM RBL-2 TO RBL 43.  SO NR 245010  NR 27077. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2GL                 
             20080718     NM  2008       7          18         2008FA0000462    120080704G5315                FLOORBEAM                               BOEING737   73783N      13844HINM  GE    CFM56 CFM56*      13802NE                              BS 328, RBL26   CORRODED        B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328, RBL 26 AFT SIDE OF BEAM FOUND TO BE BEYOND LIMITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E2GL                 
             20080718     NM  2008       7          18         2008FA0000463    120080703G5315                FLOORBEAM                               BOEING737   73783N      13844HINM  GE    CFM56 CFM56*      13802NE                              BS328           CORRODED        B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328 FROM RBL 13 TO RBL 50.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E2GL                 
             20080718     NM  2008       7          18         2008FA0000464    120080707G5315                FLOORBEAM                               BOEING737   73783N      13844HINM  GE    CFM56 CFM56*      13802NE                              BS 344          CHAFED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39304TZ                       30675                                   DURING SCHEDULED INSP, FOUND CLIP NUTS CHAFING FLOORBEAM IN FWD CABIN BS 344, LBL 0 TO LBL 55.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E2GL                 
             20080718     NM  2008       7          18         2008FA0000465    120080707G5315                FLOORBEAM                               BOEING737   73783N      13844HINM  GE    CFM56 CFM56*      13802NE                              BS344, LBL10    CORRODED        B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39304TZ                       30675                                   DURING SCHEDULED INS, FUND FWD CABIN BS 344, LBL10, FLOORBEAM CORRODED.  (K)  SO 245010, NR27110                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E2GL                 
             20080718         2008       7          18         2008FA0000466    420080711G34604052500927      COMPUTER                                BOEING767   767*               NM                                                               FMC             FAILED          W  ANCFO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO23421AV                       25421                                   AIR TURNBACK DUE PILOT REPORT 4273256-1; EICAS MSG L FMC FAIL DISPLAYED.  FIM 34-61-00 FOLLOWED L FMC PWR RESET ALL INDICATIONS NORMAL. PLS MONITOR FURTHER.  AS A PREVENTIVE ACTION DURING OVERNIGHT; IAW AMM 34-61-01/401 WAS REMOVED AND REPLACED THE FLIGHT MANAGEMENT COMPUTER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA1NM                         
             20080718     GL  2008       7          18         2008FA0000467    120080512G6100                SNAP RING                               NAMER T6    AT6F        6400420GL                                   HAMSTD23D   23D40       NE  PROP GOVERNOR   MISSING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15767WB                       12142537                                PROPELLER WAS INSTALLED IMPROPERLY.  SNAP RING THAT HOLDS ON PROP NUT AND CRANKSHAFT EXTENSION WAS NOT INSTALLED.  THIS ALLOWED CRANKSHAFT EXT TO UNSCREW AND LET PROP GOVERNOR PRESSURE OF 180 LBS TO BE PUT ON ENGINE AND PROPELLER.  THIS CAUSED PROPELLER AND ENG TO LEAK OIL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3R      A2575           6  CP719     
             20080718     CE  2008       7          18         2008FA0000468    120080701G5344NAS405          HINGE                                   BEECH 80    65B80       1152812CE  LYC   O720  IO720A1B    41546EA                              CABIN DOOR      CRACKED         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP1344MA                        LD412       L15595YA                    (2) OF THE HINGE LINKS HAD CRACKED OFF ON ONE END.  UPON DISASSEMBLY IT WAS DETERMINED THAT A CRACK HAD FORMED LENGTHWISE BETWEEN THE FASTENERS AND THE HINGE LINKS.  POSSIBLE CAUSE MAY HAVE BEEN FATIGUE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  3A20    1E15                 
             20080721     GL  2008       7          21         2008FA0000469    120080616G5340                MOUNT                                   CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              ALTERNATOR      CRACKED         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15710CD849        100575      0013        685689                      STANDBY ALTERNATOR MOUNTING FLANGE CRACKED IN (2) PLACES.  OIL GALLING AT MOUNT FLANGE WHERE CRACKS WERE NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTA00009CHE3SO                 
             20080721     SW  2008       7          21         2008FA0000470    120080701G5343ED12758         CLEVIS                                  GULSTM690TP 690A        0141722SW  GARRTTTPE331TPE33112UHR      WP                              RT MLG ACTUATOR BROKEN          B  BOERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19122AV                       11235                                   WHEN FLYING IN TO LAND, LANDING GEAR WAS SELECTED DOWN, RT MLG CAME DOWN ABOUT A FOOT AND STOPPED ON (2) ATTEMPTS, UPON (3RD) ATTEMPT GEAR CAME DOWN AND INDICATED LOCKED.  AC WAS BROUGHT INTO OUR SHOP AND WHEN THE RT MLG WAS INSPECTED, IT WAS FOUND THAT CLEVIS ASSY FROM UPPER STRUT HSG TO MAIN ACTUATOR HAD BROKEN IN (2) PIECES, (1) PART STILL ATTACHED TO ACTUATOR AND THE OTHER WAS STILL IN THE UPPER STRUT ASSY. AN OEM SL REQUIRING THAT THE CLEVIS BE REMOVED EA 500 HR AND INSPECTED BY A LEVEL II INSPECTOR.  THIS CLEVIS HAD 274 HR ON IT SINCE THAT INSPECTION, WHERE IT WAS FOUND AIRWORTHY.  ON THESE AC THERE IS A MAIN ACTUATOR AND AN AUXILLIARY ONE WITH ITS OWN CLEVIS MOUNTING ALSO.  LANDING GEAR CAME DOWN AND LOC1H72 3T4  T  2A4     E4WE                 
             20080721     NM  2008       7          21         2008FA0000471    120080601G7700PT25            SENSOR                                  BOEING777   7772Q8      1385238NM  GE    GE90  GE9094B     30045NE                              RT ENGINE       FAILED          W  ASMFO   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      SW23745AM10004                  32718       900475                      AC RETURNED TO DEPARTURE DUT TO RT ENGINE STALLED.  MAINT PERFORMED FIM 75-21 TASK 822 AND STALL INSPECTION IN 1ST, 5TH AND 9TH HPC STAGES.  NO DAMAGES WERE DETECTED IAW MM 71-00-00.  RT PT25 SENSOR WAS REPLACED IAW MM 73-21-63, TESTED CORRECT.  THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO AIRCRAFT LANDED WITH 211, 400 KGS AND MAXIMUM LANDING WEIGHT IS 213 KGS. (K)                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTT00001SEE00049EN             
             20080721     NE  2008       7          21         2008FA0000472    220080606G7200                ENGINE                                  BOEING777   7772Q8      1385238NM  GE    GE90  GE9094B     30045NE                              RIGHT           FAILED          W  ASMFK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW23745AM10838                  32718                                   DURING TRANSIT CHECK, THE RT ENGINE WAS DETECTED WITH DAMAGES.  MAINT PERFORMED BOROSCOPIC INSPECTION, DETECTING DAMAGES OUT OF LIMITS, SO RT ENGINE WAS REPLACED AND TESTED IAW MM 71-00-02 AND 71-00-00, ALL CORRECT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00001SEE00049EN             
             20080721     NE  2008       7          21         2008FA0000473    220080619G7200                ENGINE                                  DOUG  DC9   DC987       3022087WP  PWA   JT8   JT8D219     52053NE                              RIGHT           VIBRATION       W  ASMFO   OTHER                                                                                           EJ VIBRATION/BUFFET          WARNING INDICATION                                  NRNOT REPORTED   1                      SW23205AM                       49405                                   CAPTAIN REPORTED STRONG VIBRATION IN RT ENGINE WITH EPR`S BETWEEN 1.7 AND 1.75.  TECHS VERIFIED THE RT ENGINE CONDITION AND PERFORMED OPERATIONAL TEST IAW AMM 71-00-01 FOUND ALL CORRECT.  VIBRATION WAS WITHIN LIMITS (0.4 UNITS INDICATED). (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA6WE    E9NE                 
             20080725     NM  2008       7          25         2008FA0000474    120080709G5230                SKIN                                    BOEING737   737448      13844BUNM  CFMINTCFM56 CFM563C     13802EU                              CARGO DOOR      DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSPECTION, FOUND NUMEROUS DENT ON AFT CARGO EXT DOOR SKIN.  S/O 312001, OPS 24422.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA16WE   E21EU                
             20080728     NM  2008       7          28         2008FA0000475    120080627G5315                FLOORBEAM                               BOEING737   737448      13844BUNM  CFMINTCFM56 CFM563C     13802EU                              BS 986          CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON UNDERSIDE OF "T" CAP REPLACEMENT 986.5 AROUND ATTACH HOLES BL 29R TO BL 29L, NUMEROUS HOLES. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E21EU                
             20080725     WP  2008       7          25         2008FA0000476    120080617G324595502677        WHEEL                                   DOUG  DC9   DC983       3022083WP  PWA   JT8   JT8D*            NE                              NLG             LOOSE           W  ANCFC   ABORTED TAKEOFF                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      SO23160BS1211                   53463                                   REJECTED TAKEOFF, DURING T/O ROLL, THERE WAS AND ABNORMAL AND ABRUPT VIBRATION IN THE NOSE SECTION.  IAW AMM 32-21-04, PAGE 201/210 WAS CHECKED TORQUE LINKS ASSY BY LOOSE AND ADJUSTMENT ALSO WERE CHECK BOTH NOSE WHEELS, IAW AMM 32-40-02 PAGE 201, PRESS IN BOTH WHEELS 150 PSI IAW AMM 12-16-01 AND IAW AMM 32-22-01, PAGE 201 WERE CHECK BOTH DOORS AND LINKAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA6WE    E2EA                 
             20080725     NM  2008       7          25         2008FA0000477    120080602G21301305027         SELECTOR                                BOEING767   767284      1385184NM                                                               CABIN PRESSURE  INOPERATIVE     W  ANCFO   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      SO23988AN                       24742                                   AIR TURN BACK, CABIN ALT, CABIN ALTITUDE LIGHT EICAS MSG DISPLAYED OPERATIONAL AND MANUAL MODE RESTORED CABIN PRESS CABIN AUTO INOP 1 AND 2.  IAW AMM 21-31-01/401.  CABIN PRESSURE SELECTOR WAS REPLACED AND WAS ACCOMPLISHED CABIN PRESSURE CONTROL SYS, OPS TEST IAW TASK 21-31-00-705-001.  TEST SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA1NM                         
             20080725     NM  2008       7          25         2008FA0000478    120080618G5610                WINDOW                                  BOEING767   767259      1385136NM                                                               COCKPIT         LEAKING         W  ANCFC   ABORTED TAKEOFF                                                                                 W  INADEQUATE Q C                                                                TOTAKEOFF        1                      SO23985AN                       24618                                   REJECTED TAKEOFF, VERY STRONG NOISE AT 2R WINDOW DURING ROLL.  IT WAS APPLY SEALANT IN THE FINISH AROUND THE WINDOW EDGE IAW AMM 56-11-00 PAGE 801, DID THE WINDOW TEST IAW AMM 56-11-02, PAGE 601, TEST OK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA1NM                         
             20080725     NM  2008       7          25         2008FA0000479    120080617G2750                FLAP SYSTEM                             BOEING767   767283ER    1385149NM                                                               TE FLAPS        MALFUNCTIONED   W  ANCFO   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      SO23728CG                       24728                                   EMERGENCY LANDING, EICAS MSG TE FLAP DISAGREE DISPLAYED, TRAILING EDGE LIGHT ILLUMINATED WHEN ANY TE FLAP POSITION SELECTED.  FLAP FAIL TO MOVE SELECTED POSITION.  IAW FIM 27-51-00, FIG 105, BLOCKS 1,21,22,23,43 WAS ACCOMPLISHED AND IAW FIM 27-51-00, FIG 104 BLOCK 1 TO 4 IT IS OK, FSEU BITE WAS ACCOMPLISHED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA1NM                         
             20080725     CE  2008       7          25         2008FA0000480    120080415G32332317100016      ACTUATOR                                LEAR  60    60LEAR      5170707CE                                                               NLG             FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO14                            50038                                   THE NLG ACTUATOR HAD IMPACT MARKS FROM THE LOCKING BALLS IN THE LOCKING CHANNEL. THESE IMPACT MARKS ALSO PUSHED PISTON MATERIAL OUT OF THE CHANNEL CAUSING INTERFERENCE WITH THE LOCKING SLEEVE.  THIS INTERFERENCE CREATED METAL SHAVINGS THAT INTERFEERED WITH THE DOWN LOCK MECHANISM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA10CE                        
             20080725     EU  2008       7          25         2008FA0000481    120080702G26970292697390      CONNECTOR                               SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              FIRE DETECTION  CONTAMINATED    B  QMLRA   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      NM03902CF3746                   3630        22351                       DURING CRUISE FLIGHT, THE ENGINE FIRE LIGHT ILLUMINATED.  DURING THE DESCENT FOR A PRECAUTIONARY LANDING, THERE WAS NO SMOKE TRAILING THE AC AND THE ENGINE FIRE LIGHT EXTINGUISHED AND ILLUMINATED SEVERAL TIMES.  AFTER SECURING THE AC UPON LANDING, THE PILOT INSPECTED THE ENGINE AREA AND NO FIRE DAMAGE WAS NOTED. THE MAINTENANCE STAFF CAME OUT AND FOUND MOISTURE IN THE CONNECTOR PLUG ON THE FIRE DETECTION SYSTEM.  AFTER CLEANING AND INSPECTING THE SYSTEM, THE PILOT PERFORMED A CHECK FLIGHT AND THE AC WAS RETURNED TO SERVICE.  (K)                                                                                                                                                                                          1G71 3U3  U  H9EU    E00054EN             
             20080725     EU  2008       7          25         2008FA0000482    120080706G2150060018          BELT                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              AIR CONDITIONER BROKEN          B  QMLRA   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      NM03152AC                       3574                                    IMMEDIATELY AFTER TAKEOFF AND LEVELING FOR CRUISE, THE AIR CONDITIONER WAS TURNED ON.  WITHIN A SHORT TIME A STRONG ACRID SMELL WAS PRESENT IN THE AIRCRAFT.  THE SOURCE OF THE SMELL WAS UNKNOWN IN FLIGHT. THE AIRCRAFT WAS IMMEDIATELY LANDED NEXT TO A HARD-SURFACE ROAD JUST SOUTH OF THE HOSPITAL IN A SOY BEAN FIELD.  THE SKIDS WERE DIRECTLY BETWEEN THE ROWS AND NO DAMAGE WAS DONE TO THE FIELD BY THE AIRCRAFT.  AN AMBULANCE WAS IMMEDIATELY DISPATCHED TO THE SCENE AND THE PATIENT TRANSFERRED TO THE AMBULANCE FOR TRANSPORT.  THE DUTY MECHANIC WAS IMMEDIATELY CALLED.  THE MECHANIC INSPECTED THE AIRCRAFT, DETERMINED THE CAUSE OF THE ACRID SMELL AS THE AIR CONDITIONER BELT. THE MECHANIC THEN INSPECTED THE AIR CONDITIO1G71 3U3  U  H9EU    E19EU                
             20080725     EU  2008       7          25         2008FA0000483    120080704G2150060018          BELT                                    SNIAS 350   AS350B3     8680954EU  TMECA ARRIUSARRIUS2B1        NE                              AIR CONDITIONER BROKEN          B  QMLRA   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      NM03105LN                       3249                                    GROUND CREW NOTICED THE SMELL OF FUEL AND VAPOR COMING FROM AIRCRAFT AFTER LIFTING FROM SCENE.  PIC NOTIFIED OF THE CIRCUMSTANCES.  PIC MADE A PRECAUTIONARY LANDING WITH PATIENT ON BOARD. PIC DETERMINED THAT THE VAPOR WAS COMING FROM THE AIR CONDITIONER, AND NO FUEL LEAK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E34NE                
             20080725     CE  2008       7          25         2008FA0000484    120080516G2497                WIRE                                    CESSNA208   208B        2073701CE                                                               STARTER GEN     SHORTED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP21                            208B0989                                ON (2) RECENT OCCASIONS (2) AIRCRAFT HAVE HAD IDENTICAL DISCREPANCIES WITH THE STARTER ENERGIZED (SE) CIRCUIT. DURING A NORMAL START THE SE ANNUNCIATOR DID NOT EXTINGUISH NORMALLY/AUTOMATICALLY AS THE ENGINE NG INCREASES.  THE ANNUNCIATOR STAYS ON UNTIL THE PILOT MOVES THE STAT SWITCH TO "OFF" AT WHICH TIME THE LIGHT GOES OUT AND THE GENERATOR COMES ON-LINE.  TROUBLESHOOTING IN BOTH OF THESE CASES REVEALED HIGH RESISTANCE IN THE SPEED SENSOR CIRCUIT.  FURTHER INSPECTION REVEALED THAT THIS WAS DUE TO POOR WORKMANSHIP (CRIMPED AND POORLY SOLDERED) ON THE WIRE CONNECTIONS INSIDE THE STARTER/GEN (S/G CONNECTOR.  WIRE WAS PINCHED BETWEEN CONNECTOR AND CASE.  IN BOTH CASES THE S/G HAD BEEN RECENTLY OVERHAULED.  (K)  1H71 3T      A37CE                        
             20080725     NE  2008       7          25         2008FA0000485    220080709G7320256072          FLOW DIVIDER                            CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              NR 1 ENGINE FUELFAILED          B  B3ORA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      SW036001L                       5500169     71709                       DURING CLIMB OUT AFTER TAKEOFF, NR 1 ENGINE COULD ONLY PRODUCE 85 PERCENT N1.  WHILE RETURNING TO BASE , ENGINE SHUT ITSELF DOWN ON 2 MILE FINAL.  TROUBLESHOOTING FOUND THAT FUEL FLOW DIVIDER HAD MALFUNCTIONED.  FUEL FLOW DIVIDER WAS REMOVED FROM SERVICE, AND REPLACED WITH AN OVERHAULED UNIT.  AIRCRAFT WAS RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F4  F  A22CE   E1NE                 
             20080725         2008       7          25         2008FA0000486    420080618G2200                TRIM SWITCH                             BEECH 90    C90         1152913CE                                                               AUTO PILOT      FAILED          B  QPIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19362MC           3188E       LJ760                                   AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, 10/02/2007.  COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON 1/18/2008.  TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE.  MICRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME.  TRIM SWITCH ASSY PROVIDED WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED.  TRIM CIRCUITRY FAILED AGAIN AFTER (3) HOURS OF FLIGHT.  COMPUTER WAS REPAIRED AND REINSTALLED ON 2/17/2008.  TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT.  COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM S1L72 3T      3A20                         
             20080725         2008       7          25         2008FA0000487    320080717G6110D5258           BULKHEAD                                BEECH 33    F33A        1151425CE  CONT  O520  IO520*      17032SO                              PROP MOUNT      CRACKED         B  CNZ2K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP01500JL1279                   CE1603                                  PROPELLER SPINNER BULKHEAD CRACKING BETWEEN ATTACH BOLT HOLES IN (2) PLACES.  CRACK COULD BE INDUCED FROM VIBRATION. INSPECT VISUALLY EVERY PRE-FLIGHT.  A BETTER HEAT TREATING PROCESS MAY STRENGTHEN THE BULKHEAD AND REDUCE THE CRACKING FROM VIBRATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  3A15    E5CE                 
             20080725     EA  2008       7          25         2008FA0000488    220080423G72103028266         HOUSING                                                                    PWA   PT6   PT6A27      52043EA                              RGB             BROKEN          B  UTURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19                                        PCE41761                    ABOUT 12 INCHES OF THE RGB FRONT HOUSING SPLINES WERE FOUND BROKEN OFF DUE TO FATIGUE CRACK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      4  T          E4EA                 
             20080725     CE  2008       7          25         2008FA0000489    120080620G5410109910029165    INLET                                   BEECH 90    C90A        1152911CE                                                               LWR AFT COWLINGSCRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL055115H901                    LJ1705                                  LT AND RT WELD ASSY CRACKED ALONG A WELDED SEAM.  THE CRACKS ARE APPROXIMATELY 12 INCHES LONG.  THESE WELD ASSY ARE A PORTION OF THE ENGINE INLET.  A PORTION OF THE INLET AIR IS USED FOR THE OIL COOLER AND SOME AIR IS BYPASSED AND EXITS FROM THE LOWER PORTION OF THE COWLING.  THE CRACK IN THE WELD ASSY HAPPENED AT THE UPPER WELDED SEAMS IN THE BYPASS PORTION OF THE DUCT.  THE CRACKS POSED NO POTENTIAL PROBLEM OF BEING INGESTED INTO THE ENGINE.  WE HAVE COMMUNICATED THIS ISSUE WITH THE MFG OF THE AC. WE DO NOT KNOW OR WANT TO SPECULATE AT THIS TIME WHAT CAUSED THE PROBLEM OR ARE THERE ANY RECOMMENDATIONS TO PREVENT IT FROM HAPPENING AGAIN. OUR ONLY RECOMMENDATION IS TO INSPECT THIS AREA IN BOTH LT AND RT COWLING1L72 3T    RT3A20                         
             20080728     NE  2008       7          28         2008FA0000490    220080622G7200                ACOUSTIC LINER                          DOUG  DC9   DC987       3022087WP  PWA   JT8   JT8D219     52053NE                              LEFT            DAMAGED         W  ASMFO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW23216AM452717361              49586                                   AC RETURNED TO PLATFORM, DURING ENGINE ACCELERATION UP TO 1.4 EPR, STRONG NOISE IN THE RT ENG WAS HEARD.  MAINT PERFORMED AN INSPECTION AND DETECTED ACOUSTIC LINER DELAMINATION OF THE DIFFUSER OUTER FAN DUCT, BUT WITHIN LIMITS TO OPERATE TEN HOURS IAW MM 72-00-00.  AC, DURING OVERNIGHT CHECK, THE RT ENG WAS REPLACED AND TESTED IAW MM 71-00-02 AND MPCM 71-00-01, ALL CORRECT.  (K)                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA6WE    E9NE                 
             20080728     GL  2008       7          28         2008FA0000491    220080709G723066032           BLADE                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ441A           GL                              IP ROTOR BLADE  DEPARTED        B  FCPRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09678RF1040                   5250537     2091                        DURING ROUTINE INSP, FOUND DAMAGE TO THE 1ST STAGE STATOR ASSY, UPON FURTHER INSPECTION, FOUND 1 BLADE HAD FAILED AND DEPART THE LP ROTOR ASSY CAUSING DAMAGE TO THE REST OF THE ENGINE DOWN STREAM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4F4  FRTA1WI    E3GL                 
             20080725     GL  2008       7          25         2008FA0000492    120080630G2421                FAN                                     CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO  HARTZLHCJ3Y PHCJ3YF1    GL  ALTERNATOR      CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99PROMZ                       3041        691724      FP6763          ALTERNATOR NR 2 (BELT DRIVEN ALTERNATOR) COOLING FAN DEVELOPED CRACK AT FAN BLADE RADIUS.  CRACK ELONGATED UNTIL FAN SEPARATED FROM ALTERNATOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTA00009CHE3SO    5  CP36EA    
             20080728     GL  2008       7          28         2008FA0000493    120080623G5397                WIRE                                    CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              ALT AIR DOOR    FATIGUED        C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP05683SR                       2766        691392                      WIRES THAT CONNECT TO THE ALTERNATE AIR DOOR (WHICH ARE SOLDERED TO THE SWITCH) FOR THE TORNADO ALLEY TURBO SYSTEM ARE BECOMING FATIGUED AND SOLDER IS BREAKING AT SWITCH.  IF THE ALTERNATE AIR WAS TO OPEN AND THESE WIRES WERE BROKEN, IT WOULD NOT GIVE THE PILOT AN INDICATION THAT THE ALTERNATE AIR DOOR WAS OPEN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTA00009CHE3SO                 
             20080725     SO  2008       7          25         2008FA0000494    120080715G2170234018623       WATER SEPARATOR                         GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                                              DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP21595PE     141               1373                                    BOTH UNITS O/H AT MFG.  WHEN CHANGING SOCK, FOUND RUST STAINS ON SOCK.  REMOVED AND FOUND RETAINING CHAIN PN 834639 RUSTED.  CHAIN WAS WRONG MATERIAL (METAL) AND INCORRECT LENGTH (9.5 INCHES).  REPLACEMENT UNIT WAS SS WITH A TOTAL LENGTH OF (6 INCHES).  ALSO ON UNIT 67-272 (1) OF (8) INTERNAL RETAINING SCREWS WAS FOUND NOT SEATED AND IN CONTACT WITH PART GASKET.  ALSO FOUND INSIDE SAME UNIT WAS A PIECE OF MASKING TAPE (2 INCHES X 6 INCHES) WITH SN OF UNIT WRITTEN WITH A RED MARKER STILL AFFIXED TO INNER COATING OF AFT SECTION.  WO NR TTT91055 (SN 49-945) DATED SEPT 28, 2006. AND CLJ14812 (SN 67-272) DATED SEPT 24, 2007.  (K)                                                                                        2L72 4F4  FRTA12EA   E25NE                
             20080728     EU  2008       7          28         2008FA0000495    120080525G2800                FUEL SYS                                RHNFLUEXT300EA300L      70218DGEU  LYC   O540  AEIO540*         EA                                              MALFUNCTIONED   D      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  NRNOT REPORTED   1                      NE0522MW                        131                                     APPROX 9 GALLONS OF FUEL IN CENTER TANK BECAME INACCESSIBLE DURING FLT, PRECAUTIONARY LANDING.    AFTER DEPARTING USING CENTER TANK FUEL FOR A 120 MILE FERRY FLIGHT, SWITCHED TO  THE WING TANKS FOR THE PREPONDERANCE OF THE TRIP. NEARING THE DESTINATION  WITH THE WING TANKS ALMOST DRY, SELECTED THE FUSELAGE TANK FOR THE REMAINDER OF THE FLIGHT.  THE FUEL FLOW METER INDICATED THAT AIR, RATHER THAN FUEL , WAS BEING DRAWN INTO THE SERVO.  THE ENGINE STOPPED.  RESELECTED THE WING TANKS; THE ENGINE RESTARTED. ATTEMPTED 4 MORE TIMES TO SOURCE FUEL FROM THE FUSELAGE; EACH TIME, THE ENGINE STOPPED.  MADE A PRECAUTIONARY LANDING. MECH DECOWLED ACFT AND CONFIRMED THAT FUEL COULD BE SOURCED INTO THE SERVO FROM EITHER THE W1M71 3O3  ONCEA67U   1E4                  
             20080725         2008       7          25         2008FA0000496    420080618G220030B641          TRIM SWITCH     CENTURY                 AMTR  SUKHOISU26MX      1152913GL  PWA   PT6   PT6A21      52043EA                              CONTROL COLLUMN INOPERATIVE     B  QPIDO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19362MC           3188E       LJ760                                   AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, OCT 02, 2007.  COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON JAN 18, 2008.  MFG TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. MICRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME.  TRIM SWITCH ASSY PROVIDED BY MFG WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED ON FEB 17, 2008.  TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT.  COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM SWITCH WAS CONFIRMED TO BE CAUSING THE FAILURE AGAIN.  THE TRIM UP MICRO SWITCH1M71 3R4  TNCEXPA1M71E4EA                 
             20080728     NM  2008       7          28         2008FA0000497    120080620G2701                BOOT                                    ADAMACA500  A500        05614IQNM  CONT  O550  TSIO550E    17043SO                              CONTROL COLLUMN MISINSTALLED    D      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      WP27896MH                       0008                                    AT LOCATION WHERE CONTROL "STICK" PASSES THROUGH L/R SIDE ARM REST, THE BOOT SURROUNDING BASE OF STICK LIES OPEN TO CONTROL MECHANISMS. WHERE THE STICK ENTERS THE COCKPIT, THE LEATHER BOOT THAT IS DESIGNED TO COVER THE AREA BENEATH THE STICK, IS PARTIALLY OPEN.  THIS ALLOWS FOREIGN OBJECTS, PLACED ALONG THIS AREA, TO FALL DOWN INTO WHERE CONTROLS COULD BECOME JAMMED.  THIS HAS ALREADY OCCURRED, RESULTING IN LOSS OF VERTICAL CONTROL. MFG NEEDS TO ISSUE AN IMMEDIATE AD AND ISSUE REMEDY FOR THIS SAFETY OF FLIGHT ISSUE.  (K)                                                                                                                                                                                                  1L72 3O3  ORTA00009DEE5SO                 
             20080725     CE  2008       7          25         2008FA0000498    120080711G551004320049        BRACKET                                 CESSNA150   152         2071835CE  LYC   O235  O235*       41505EA                              HORIZONTAL STAB CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP2766970                       15281696                                WHILE CONDUCTING A 100 HOUR INSPECTION ON THE AIRCRAFT, COMPLYING WITH AD80-11-04 (NUTPLATE INSPECTION).  UPON INSPECTION, IT WAS FOUND THAT NOT ONLY WAS THERE A CRACKED NUTPLATE, BUT THERE IS ALSO A (1 INCH) CRACK IN THE WELDED BRACKET- THE PART THAT THE NUTPLATES MOUNT TO.  IT CAN BE SEEN IN MFG ILLUSTRATED PARTS CATALOG, FIGURE 18, ITEM NR 10.  UPON REMOVING THE BRACKET FROM THE AIRCRAFT, ALSO DISCOVERED THAT A LARGE PORTION OF THE STEEL BRACKET HAD BEEN RUSTED; PARTICULARLY IN THE WELDED AREAS.  BECAUSE MFG NO LONGER MAKES THIS PART, ACQUIRED A SERVICEABLE PART, INSPECTED THE WELDS, TREATED THE CORROSION, AND INSTALLED IT ON THE AIRCRAFT.  (K)                                                                 1H71 3O3  ONT3A19    E223                 
             20080725     CE  2008       7          25         2008FA0000499    120080716G275098600581        CONTROL CABLE                           CESSNA210   T210L       2073449CE  CONT  O520  TSIO520*    17040SO                              FLAPS           DEFECTIVE       D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW152423S                       21061275                                ORDERED NEW MFG FLAP FOLLOW UP CABLE; TO REPLACE ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE.  THIS CABLE IS SIMILAR TO A THROTTLE CABLE WITH AN INSIDE CABLE WHICH SLIDES IN AN OUTSIDE HOUSING. UPON INSTALLATION, OF NEW MFG  FLAP FOLLOW UP CABLE, OPERATION WAS VERY ROUGH AND INTERMITTENT.  SMOOTH OPERATION IS CRITICAL TO MEET MM SPECS AND AIRCRAFTS FLIGHT MANUAL REQUIREMENTS FOR CERTAIN SPECIFIED  FLIGHT CONFIGURATIONS.  CONTACTED MFG SERVICE CENTER AND THEN MFG TECH SUPPORT DIRECT.  MFG ASSURED, VERBALLY THE CABLE HAS BEEN MFG TO ORIGINAL SPECIFICATIONS.  FROM FIRST GLANCE, CABLE IS OBVIOUSLY CONSTRUCTED IN A DIFFERENT MANNER AND OF DIFFERENT MATERIAL OF ORIGINAL PART ON THIS AND OTHE1H71 3O3  O  3A21    E8CE                 
             20080725     CE  2008       7          25         2008FA0000500    120080713G7897                WIRE                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D5      52112NE                              THRUST REVERSER CHAFED          D      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      EA2367SF 6216                   5500243                                 ON CLIMB OUT, AFTER DEPARTURE, THE LT THRUST REVERSER DEPLOY LIGHT ILLUMINATED.  NO ABNORMAL FLIGHT CHARACTERISTICS WERE FELT IN THE AC.  AFM PROCEDURES WERE FOLLOWED AND A SAFE LANDING BACK AT DEPARTURE AIRPORT WAS MADE.  AFTER LANDING, THE PILOT CYCLED THE LT THRUST REVERSER AND THE LIGHT EXTINGUISHED.  THE TRIP WAS CANCELLED UNTIL THE AIRCRAFT COULD BE INSPECTED.  INVESTIGATION REVEALED A WIRE FOR THE DEPLOY SWITCH HAD CHAFED TO GROUND AT THE STRUCTURE OF THE LT THRUST REVERSER OB STANG.  THE DAMAGED WIRE WAS REPAIRED AND THE WIRE BUNDLE IN THAT AREA WAS REPOSITIONED TO PREVENT ANY FURTHER CHAFING.  OPS CHECK OF THE THRUST REVERSER SYSTEM AFTER REPAIR WAS NORMAL.  (K)                                         1L72 4F4  F  A22CE   E25EA                
             20080728     CE  2008       7          28         2008FA0000501    120080715G5730                SKIN                                    BEECH 300   300BEECH    1152930CE                                                               WING            DAMAGED         B  KX5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15613BA                       FL396                                   AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLE ROW OF RIVETS AT WING STA 209.016.  RIVETS WERE FOUND SMOKING AND PAINT WAS POPPED ON THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN THE DOUBLE ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AIRCRAFT HAS A TT OF 1659.1.  RECOMMEND INSPECTING THESE RIVET FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1B.  (K)                                                                                                                                                                                                                                         2L72 4T      A24CE                        
             20080728         2008       7          28         2008FA0000502    420080718G22006222263016      AMPLIFIER                               ISRAEL1124  1124A       4500103EU  GARRTTTFE731TFE731*     01518WP                              AUTOPILOT       INOPERATIVE     D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19818JH                       341                                     AFTER (1) HOUR DISENGAGES AUTOPILOT.  PRELIMINARY INSPECTION RESULTS, NO DEFECTS NOTED AFTER BENCH CHECK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2M72 4F4  F  A2SW    E6WE                 
             20080728     CE  2008       7          28         2008FA0000503    120080715G5730                SKIN                                    BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              RT WING         DAMAGED         B  KX5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15291B                        FL559                                   AIRCRAFT WAS BROUGHT IN FOR PHASE INSPECTION.  DURING INSPECTION A DOUBLER ROW OF RIVETS AT WING STATION 209.016 WERE FOUND WITH PAINT POPPING OFF OF THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN THE DOUBLE ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AIRCRAFT HAS A TT OF 201.8.  RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1B.  (K)                                                                                                                                                                                                                          2L72 4T4  T  A24CE   E4EA                 
             20080728     GL  2008       7          28         2008FA0000505    320080722G61971219310         CONNECTOR       WOODWARD                DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE  HARTZLHCC2Y HCC2YR1     GL  PROP GOVERNOR   DAMAGED         B  WOGRA   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      GL03412PJ300        00272       40495       L3186051A   CH38785B        ON JUNE 28TH, 2008, DURING CLIMB OUT, PASSING THROUGH 4000 FEET THE ENGINE SUDDENLY WENT INTO AN OVER SPEED CONDITION OF OVER 3100 RPM. THE AIRCRAFT REMAINED UNDER CONTROL AND WAS LANDED SAFELY AT AIRPORT AFTER AN EMERGENCY WAS DECLARED.  UPON DISASSEMBLY OF THE GOVERNOR, IT WAS DISCOVERED THAT THE 1219-310 PLUG HAD BECOME DISLODGED FROM THE GOVERNOR BODY.  THIS SEPARATION AND THE RESULTANT LOSS OF PROPELLER SERVO PRESSURE ALLOWED THE PROP TO RETRACT TO ITS LOW PITCH POSITION AND OVERSPEED THE ENGINE.  A PROBABLE CAUSE WAS LACK OF PROPER TORQUE DURING ASSEMBLY.  APPLICATION OF LOCK-TIGHT TO THE PLUG AND INDEPENDENT SECOND PARTY VERIFICATION OF TORQUE DURING ASSEMBLY IS SUGGESTED.  (K)                           1L71 3O3  ONTA47CE   E1CE    5  CP920     
             20080728     SO  2008       7          28         2008FA0000506    120080702G7714ACA500          TRANSMITTER                             GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              LT ENGINE       MALFUNCTIONED   G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO1961WH                        1075                                    TRANSMITTER CAUSED LT ENGINE TO SPOOL BACK TO IDLE, AC RETURNED TO AIRPORT AND LANDED WITH NO INCIDENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA12EA   E25NE                
             20080728     CE  2008       7          28         2008FA0000507    120080715G5730                SKIN                                    BEECH 300   300BEECH    1152930CE                                                               WING            DAMAGED         B  KX5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL15613BA                       FL396                                   AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLER ROW OF RIVETS AT WING STA 209.016.  RIVETS WERE FOUND SMOKING AND PAINT WAS POPPED ON THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN THE DOUBLER ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AC HAS A TT OF 1659.1.  RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43..13-1B.  (K)                                                                                                                                                                                                                                           2L72 4T      A24CE                        
             20080728     CE  2008       7          28         2008FA0000508    120080716G52105043006221      BRACKET                                 BEECH 200   B200        1152922CE                                                               PAX DOOR LATCH  MISINSTALLED    D      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      EA05786DD661        BB1171      BB1171                                  PILOT REPORTED DOOR CAME OPEN IN FLIGHT.  UPON LANDING, IT WAS FOUND THE MAIN CABIN DOOR HAD DEPARTED AIRCRAFT.  DOOR WAS RECOVERED.  DURING INSPECTION AND DISASSEMBLY OF THE DOOR, SEVERAL ISSUES WERE FOUND.  1) UPPER FORWARD LATCH HOOK WAS FOUND WITHOUT RIGGING HOLES INSTALLED AND WAS INCORRECTLY RIGGED.  2) DOOR BELLCRANK, PN 50-430031-29 WAS FOUND BENT AND TWISTED.   3) MAIN CABIN DOOR LATCH BRAZE ASSEMBLY WAS CATCHING ON HOOK.  DID NOT ALLOW FOR A SMOOTH TRANSITION TO A LOCKED POSITION.  (K)                                                                                                                                                                                                                            1L72 4T      A24CE                        
             20080805     SO  2008       8          5          2008FA0000509    120080722G32509539500         ARM                                     PIPER PA34  PA34200T    7103406SO  CONT  O360  TSIO360*    17025SO                              NLG STEERING    WORN            B  BIERO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA212190K4792                   347970096                               NLG MOUNT ASSY ATTACHMENT POINT FOR STEERING ARM ASSY HAS EXCESSIVE WEAR AT LWR MOUNT HOLE, SRM DOES NOT SPECIFY AT FIX OR ALLOWABLE LIMIT FOR PN 95551-23.  DISCREPANCY FOUND DURING INSP IAW SB 1123A & B AND ANNUAL INSPECTION IAW SRM INSPECTION GUIDE.  SB 1123B GIVES THE SERVICE LIMITS TO THE STEERING ARM CENTER PIVOT BUSHINGS AND CENTER PIVOT SLEEVE.  HOWEVER THE MORE CRITICAL COMPONENT, THE NLG MOUNT ASSY IS NOT ADDRESSED FOR THE SERVICE LIMIT OF THE STEERING ARM MOUNTING TABS.  MFG SHOULD INCORPORATE SERVICE LIMIT DATA THAT COVERS THE NLG MOUNT ASSY AND REPAIR DATA.  (K)                                                                                                                                            1L72 3O3  O  A7SO    E9CE                 
             20080811     EU  2008       8          11         2008FA0000511    120080719G2435105SG1220       STARTER GEN                             SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          FAILED          B  HDNRO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      SW03350BH                       2813        9345                        WHILE ACFT WAS CIRCLING AT A SCENE CALL, THE CREW WAS STARTING TO DETECT WHAT SEEMED TO BE BURNING PLASTIC FOLLOWED BY A GENERATOR CAUTION LIGHT.  AC LANDED BACK AT HOSPITAL PAD WITHOUT INCIDENT. MAINT WAS DISPATCHED. IT WAS FOUND THAT THE STARTER GENERATOR HAD FAILED AND THE PLASTIC FAN BLADES WERE DEFORMED RESULTING IN THE PLASTIC BURNING ODOR.  THE STARTER GENERATOR WAS REPLACED AND AN OPERATIONAL CHECK OF THE SYSTEM WAS SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
             20080811     CE  2008       8          11         2008FA0000512    120080702G276012SX1T          SWITCH                                  RAYTHN390   390         7150030CE                                                               SPOILERS        FAILED          B  E81RO   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      GL03972PF1146                   RB38                                    PILOT REPORTED SPOILER FAIL INDICATION IN CRUISE FLIGHT.  ALL SPOILER PANELS DEPLOYED UPON LANDING.  SCU FAULT CODE 44R4RV3V INDICATED.  ADJUSTED LT & RT SPOILER FINAL POSITION LVDT`S AS REQUIRED IAW MM 27-60-00-501.  REPLACED LT THROTTLE SWITCH S1, SPOILER SYS FUNCTIONAL CHECKS NORMAL, NO FAULTS INDICATED SUSPECT LT THROTTLE S1 SWITCH TO HAVE PREMATURE INTERNAL FAULT.  RECOMMEND MFG INVESTIGATE IF FLEET IS EXPERIENCING PREMATURE FAILURES OF THROTTLE SWITCHES AND REDESIGN SWITCH IF REQUIRED.  (K)                                                                                                                                                                                                                           1L72 3F    RTA00010WI                     
             20080811     NM  2008       8          11         2008FA0000513    120080730G5753                SPAR                                    BOEING737   737448      13844BUNM  CFMINTCFM56 CFM563C     13802EU                              LT TE FLAP      CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E21EU                
             20080811     NM  2008       8          11         2008FA0000514    120080730G5753                SPAR                                    BOEING737   737448      13844BUNM  CFMINTCFM56 CFM563C     13802EU                              LT WING TE FLAP CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA16WE   E21EU                
             20080811     WP  2008       8          11         2008FA0000515    120080729G5530                INLET                                   DOUG  DC9   DC982       3022082WP  PWA   JT8   JT8D*            NE                              HEAT EXCHANGER  CRACKED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39886GA                       49931                                   DURING SCHEDULED INSP, FOUND VERTICAL STABILIZER L/E AT HEAT EXCHANGER INLET IS CRACKED APPROX 6.5 INCHES LONG ON LT SIDE.  FOUND TO BE OUT OF LIMITS IAW SRM 55-05 FIG 3. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  F  A6WE    E2EA                 
             20080811     EA  2008       8          11         2008FA0000516    220080721G8550CH481101        OIL FILTER                              CESSNA150   152         2071835CE  LYC   O235  O235*       41505EA                              ENGINE          CONTAMINATED    D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE014900H1                      15284009                                FILTER INSTALLED AND OIL CHANGE RUN-UP NORMAL.  FIRST FLIGHT AFTER OIL CHANGE, PILOT NOTICED OIL PRESSURE DROPPING AND HIGH OIL TEMP, UNABLE TO CORRECT, PILOT RETURNED TO ORIGIN AND REPORTED FINDINGS.  INVESTIGATION FOUND FILTER ELEMENT DEBRIS UNDER PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE, UPON FURTHER INVESTIGATION A SECOND FILTER OF SAME DATE CODE WAS FOUND TO HAVE LOOSE DEBRIS IN THE FILTERED SIDE OF THE FILTER ELEMENT AND THE ELEMENT WAS BONDED ON ONE END ONLY.  THE ENGINE GULLIES WERE FLUSHED WITH AIR AND SEVERAL PIECES OF DEBRIS WERE FOUND, A NOW FILTER OF DIFFERENT DATE CODE WAS INSTALLED, SEVERAL GROUND RUNS WERE MADE, NO SIGNIFICANT DEBRIS WAS FOUND.  A NEW FILTER OF A DIFFERENT MFG WAS INSTALLE1H71 3O3  ONT3A19    E223                 
             20080811     EU  2008       8          11         2008FA0000517    120080801G3210DIN4718ZP       FITTING                                 DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE12501    59300EU                              MLG             LOOSE           D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA17119BJ                       42AC045                                 CIRCLIP THAT SECURES DOWNLOCK PIN IN MLG LEGS HAS BEEN TWISTING OFF RENDERING THIS DOWNLOCK PIN LOOSE ENOUGH TO FALL OUT WHEN GEAR IS RETRACTED, THIS PARTICULAR AC HAD THE AFT SECTION OF THE WHEELWELL DAMAGED DUE TO THE PIN HANGING HALF WAY OUT AND CONTACT THROUGH THE LAMINATE.  THIS PIN SHOULD BE SECURED WITH SOMETHING THAT IS PERMANENT LIKE A COTTER PIN OR SAFETY WIRE.  THIS PROBLEM WAS DISCOVERED ON A PILOTS PRE-FLIGHT.  (K)                                                                                                                                                                                                                                                                                                 1L72 3I3  BRTA57CE   E00069EN             
             20080811     SO  2008       8          11         2008FA0000518    220080717G8520654837          CAMSHAFT                                                                   CONT  O550  IO550B           SO                              ENGINE          WORN            B  Y2GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA23     2079                               296655                      CAMSHAFT LOBES WORN EXCESSIVELY FORM CORROSION PITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              3  O          E3SO                 
             20080811     EA  2008       8          11         2008FA0000519    220080717G8520LW19173         CAMSHAFT                                                                   LYC   O540  IO540*      41532EA                              ENGINE          WORN            B  Y2GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA23     1329                               L100268A                    CAMSHAFT LOBES WORN FROM CORROSION PITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          3  O          1E4                  
             20080811     EA  2008       8          11         2008FA0000520    120080624G2730C6CTM102827     JACKSCREW                               DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6*        52043EA                              LT ELEVATOR     DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP09300DZ                       644                                     FOUND SCREW-DRIVE INTERNAL THREADS STRIPPED AND SAFETY SPLIT, PIN MISSING.  PILOT HAD DIFFICULTY CONTROLLING ELEVATOR.  PART HAD 196.2 IN SERVICE, SINCE REPAIR.  RECOMMENDED TO INSPECT LT ELEVATOR TRIM TAB FOR EXCESSIVE PLAY IAW MM AS PART OF PREFLIGHT AND EVERY SCHEDULED INSP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H72 3T3  TRTA9EA    E2NE                 
             20080811     CE  2008       8          11         2008FA0000521    120080723G712010191012253     MOUNT                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6*        52043EA                              LT ENGINE       CRACKED         B  GSPRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0573WC 6814                   FL135                                   DURING A PHASE 2, 200 HR INSP, A CRACK WAS FOUND ON THE LT ENGINE MOUNT UPPER IB COWLING BRACKET.  THE CRACK EXTENDED FROM THE TOP OF THE WELD AND WAS APPROXIMATELY 1 INCH IN LENGTH.  THE ADJACENT AREAS DID NOT APPEAR DAMAGED..  TECH SUPPORT WAS CONTACTED AND THE MOUNT SENT TO A QUALIFIED WELDER FOR REPAIR.  CAUSE OF CRACK IS UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T3  T  A24CE   E2NE                 
             20080811     SO  2008       8          11         2008FA0000522    120080731G253050231L0V5280    PAN                                     GULSTMG1159 GIV         3980115SO  PWC   PW615 PW615FA     52282NE                              OVEN            MISINSTALLED    D      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      SO13416QS                       1316                                    CABIN SMOKE DUE TO DRIP PAN IN OVEN BEING IMPROPERLY INSTALLED CAUSING DRIPPINGS FROM FOOD TO CONTACT OVEN LOWER BURNER ELEMENTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA12EA   E00073EN             
             20080811     SO  2008       8          11         2008FA0000523    120080707G8120LW18302         MOUNT                                   PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              TURBOCHARGER    BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA233580X                       318052085   L628661A                    FOUND MOUNT FOR TURBOCHARGER TO BE BROKEN COMPLETELY THROUGH ON IB LOWER TUBE ON RT ENGINE.  CRACK WAS APPROXIMATELY 4 TO 5 INCHES FROM FWD LOWER ATTACH POINT.  NO REPORTED VIBRATION ISSUES OF OPERATIONAL ISSUES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA                
             20080811         2008       8          11         2008FA0000524    420080802G2300G888012         CONTROL HEAD                            AMD   FALC50FALCON50MYST2730106EU  GARRTTTPE331TPE3313     01514WP                              NR 1 NAV/COMM   FAILED          D      O   OTHER                                                                                           BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  DEDESCENT        1                      SO14980S                        249         P75665                      AS CREW REPORTED DURING DESCENT THREW 16000 FT 1.40 HR INTO FLIGHT EXPERIENCED A SUDDEN ELECTRICAL BURNING ODOR THAT WAS ACCOMPANIED BY SMALL PLUME OF SMOKE.  COMPLETED ALL MEMORY ITEMS ON THE CHECKLIST AND DECLARED EMERGENCY FOR PRIORITY LANDING.  SHORTLY THEREAFTER WHILE DESCENDING TO 6000 FT THE SMOKE AND ELECTRICAL ODOR CLEARED AND NOTED NR 1 NAV/COM CONTROL NO LONGER WORKING AND PULLED CIRCUIT BREAKER.  AT THAT TIME EMERGENCY WAS OVER AND REQUESTED NORMAL HANDLING TO THE AIRPORT.  UPON FURTHER INSPECTION BY TECH, THE NR 1 NAV/COM CONTROL HEAD HAD FAILED CAUSING THE PROBLEM.  REPLACEMENT PART INSTALLED.  REMOVED UNIT PN G8060-12, SN 273 SENT FOR EVALUATION AND REPAIR.  (K)                                   2L73 4F4  T  A46EU   E4WE                 
             20080811     EA  2008       8          11         2008FA0000525    220080722G7414AB382584        CONTACTOR       BENDIX                  BLANCA17    1731ATC     1220437GL  LYC   O540  TIO540*     41532EA                              MAGNETO         BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW13222SN                       31004                                   A BROKEN CONTACT BREAKER WAS FOUND DURING TROUBLESHOOTING AN IGNITION PROBLEM.  THE CONTACTOR RIVET WAS BROKEN ON THE MAGNETO.  THE CONTACTOR RIVET MAY BE INSUFFICIENT TO PROPERLY HOLD THE CONTACTOR IN PLACE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  A18CE   E14EA                
             20080811     SO  2008       8          11         2008FA0000526    220080619G7414K3823           DISTRIBUTOR                             CESSNA182   182Q        2072732CE  CONT  O470  O470*       17026SO                              MAGNETO         WORN            B  AKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0516MS 182                    18267267                                REMOVED NEW MAGNETOS PN 6310, SN 07061208 & 07061310..  ACCOMPLISHED SB 3-08 PREMATURE CARBON BRUSH WEAR.  BOTH CARBON BRUSHES HAD PREMATURE WEAR AS DEPICTED IN THE CENTER ILLUSTRATION FIG 1, PAGE 3 OF 5. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A13    E273                 
             20080811     SO  2008       8          11         2008FA0000527    220080619G7414M1827           CAM                                     CESSNA182   182Q        2072732CE  CONT  O470  O470*       17026SO                              MAGNETO         WORN            B  AKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0516MS 182        07061208    18267267                                REMOVED NEW MAGNETOS PN 6310, SN 07061308 & 07061310.  ACCOMPLISHED SB 2-08, MAGNETO  CONTACT POINT CAMP PREMATURE WEAR.   INSTALLED 2 NEW CONTACT POINT ASSEMBLIES PN M3081; SET "E" GAP AND TIMED TO THE ENGINE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A13    E273                 
             20080811     CE  2008       8          11         2008FA0000528    120080729G3222                STRUT                                   CESSNA172   172RG       2072438CE  LYC   O360  O360*       41514EA                              NLG             DAMAGED         B  QFBRO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      NM016448V                       172RG0709                               PILOT REPORTED A CLUNKING NOISE COMING FROM THE NLG.  UPON INSPECTION, IT WAS NOTED THAT .2500 INCH UP AND DOWN PLAY AT THE LOWER TRUNNION ASSY.  THE AC`S NLG ASSY WAS REMOVED AND DURING FATHER INSPECTION THE BARREL WAS FOUND TO BE THE CULPRIT.  THE BOLT THAT HOLDS THE HEAD AND TUBE ASSY SHOCK STRUT PN 2443005-1 AND COLLAR ASSY TO THE BARREL HAD SHIFTED AT .2500 INCH TO THE BARREL BOLT HOLE ELONGATED AND DISPLACING METAL ABOVE THE BOLT HOLE.  THE AC IS USED FOR FLIGHT TRAINING, WAS IS SUSPECT PLAYS SOME ROLE BUT BELIEVE THE PROBLEMS HAD BEEN DETECTED BEFORE AND ONLY THE BOLT WAS REPLACED.  (K)                                                                                                                        1H71 3O3  O  3A17    E286                 
             20080811     EA  2008       8          11         2008FA0000529    220080730G853074230           GUIDE                                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              CYLINDER HEAD   SEIZED          D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      WP07543ER889                    172S10522   L3342451E                   DURING FLIGHT, THE ENGINE STARTED RUNNING ROUGH AND LOST POWER.  EMERGENCY LANDING COMPLETED WITHOUT DAMAGE OR INJURY.  MAINT FOUND THE NR 3 EXHAUST VALVE SEIZED IN THE VALVE GUIDE.  FURTHER INVESTIGATION FOUND THE GUIDE BROKEN IN THE CYLINDER HEAD.  OPERATOR HAS AIRCRAFT WITH THE NEW ROLLER TAPPET ENGINES.  HAVE BEEN PERFORMING A SB388C INSPECTION ON THE REST OF THE FLEET AND HAVE FOUND THE MAJORITY OF THE EXHAUST VALVES FOR ALL CYLINDERS TO BE TIGHT IN THE GUIDES.  MFG RECOMMENDS A 1000 HOUR INTERVAL FOR THESE ENGINES FOR SB388C INSPECTION.  WILL BE INITIATING A 600 HOUR INTERVAL FOR THE SB388C FOR OUR FLEET.  HAVE REVISED LEANING PROCEDURES.  (K)                                                               1H71 3O3  ONT3A12    1E10                 
             20080811     SO  2008       8          11         2008FA0000530    120080714G2420365662R         STATOR                                  PIPER PA32  PA32R300    7103213SO  LYC   0540  IO540K1G5D  41532SO  HARTZLHCC3Y HCC3YR      GL  ALTERNATOR      SHORTED         C      A   UNSCHED LANDING                                                                                 HJ ELECT. POWER LOSS-50 PC   WARNING INDICATION                                  NRNOT REPORTED   1                      SW112125V                       32R7780431  L1664445A   DY4143A         THE AC SUFFERED LOSS OF ELECTRICAL POWER WHILE IN CONTACT WITH ATC WHEN LOST  RADIO CONTACT.  CONTACTED BKP VIA CELL PHONE AND STATED HIS PROBLEM AND REQUESTED RUNWAY LIGHT AND WHEN THEY WERE TURNED ON HE WAS WITHIN SIGHT OF THE RUNWAY AND USED EMERGENCY RELEASE OF THE LANDING GEAR AT 120 KNOTS.  AS AC TOUCHED DOWN THE NOSE GEAR COLLAPSED CAUSING THE AC TO SKID OFF RUNWAY.  DAMAGE WAS CONFINED TO THE PROP, MLG DOORS AND RT WING L/E, WING TIP.  NO FLIGHT PLAN HAD BEEN FILED AND VFR CONDITIONS PREVAILED.  NO INJURIES.  TESTED ALTERNATOR FOUND STATOR HAD SHORTED OUT, IN TURN HAD SHORTED OUT RECTIFIER.  (K)                                                                                                              1L71 3O3  O  A3SO    1E4     5  CP25EA    
             20080811     EA  2008       8          11         2008FA0000531    220080728G7314                SEAL                                    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2B  41979EA                              NR 2 ENG        LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      SO053589X           E2048       318052138   L244768A                    FUEL PUMP DRIVE SHAFT SEAL FAILED RESULTING IN LARGE FUEL LEAK AT DRAIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA                
             20080811     GL  2008       8          11         2008FA0000532    120080801G2450                BUSS BAR                                CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              CB PANEL        LOOSE           B  YEBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05839CT                       2938                                    PILOT REPORTED THE NR 2 ALTERNATOR WAS INTERMITTENT.  WHILE TROUBLESHOOTING THE NR 2 ALTERNATOR, FOUND 13 SCREWS LOOSE AND 1 SCREW MISSING ON THE COPPER CIRCUIT BREAKER BUSS BAR.  THE 1 SCREW MISSING WAS ON THE NR 2 ALTERNATOR CIRCUIT BREAKER BUSS FEED.  PROBABLE CAUSE FOR THIS WOULD BE THAT THEY WERE NOT TIGHT FROM FACTORY.  RECOMMEND CHECKING TORQUE OF ALL CIRCUIT BREAKER SCREWS AT NEXT MAINTENANCE ACTION.  (K)                                                                                                                                                                                                                                                                                                                1L71 3O3  ONTA00009CHE3SO                 
             20080811     CE  2008       8          11         2008FA0000533    120080714G716045A35042003     SKIN                                    BEECH MU300 400A        1155402CE                                                               RT ENGINE INLET CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19470LX1491                   RK478                                   REPORTED RT ENG INLET CRACKED AT 9:00 POSITION.  THE INLET WAS REMOVED AND REPAIRED AND REINSTALLED ON THE AC.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4F    RTA16SW                        
             20080808     SO  2008       8          8          2008FA0000534    120080712G28201500106151      LINE                                    PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6*        52043EA                              FUEL SYSTEM     CHAFED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      SO075339G                       4697095                                 FOUND FUEL LINE, PN 1500106-151, CHAFED AGAINST THROTTLE CABLES , PROP CONTROL CABLES  BELOW THROTTLE. THIS LINE PROVIDES FUEL PRESSURE TO THE 2 MANUAL ENGINE PRIMER PUMPS AT THE BASE OF THE QUADRANT.  HAD THIS LINE CHAFED THROUGH, FUEL UNDER PRESSURE WOULD HAVE FLOWED INTO THE AIRPLANE CABIN.  THE ONLY WAY TO SHUT OFF FUEL FLOW TO THIS LINE WOULD BE TO CLOSE THE FRONT ENGINE FUEL SELECTOR VALVE, AND SHUT DOWN THE FRONT ENGINE.  THIS IS A POTENTIAL HAZARDOUS CONDITION AND COULD CAUSE AN INFLIGHT CABIN FIRE WITH RESULTANT LOSS OF LIFE AND AIRCRAFT IF NOT FOUND AND CORRECTED.  (K)                                                                                                                                       1L71 3O3  TRTA25SO   E2NE                 
             20080811     SW  2008       8          11         2008FA0000535    120080730G32345040560006      DOWNLOCK                                MOONEYM20   M20B        5870206SW  LYC   O360  O360A1A     41514EA  MCAULY2A36C D2A36C*     GL  CONTROL LEVER   WORN            C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW19745423371                   1853        L402336     58618           LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWN LOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WAS ON THE GROUND DURING LANDING ROLLOUT.  THIS ALLOWED GEAR TO COLLAPSE.  SB M20-88B, 5/10/94.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  2A3     E286    5  CP880     
             20080811     EA  2008       8          11         2008FA0000537    120080724G5730                SKIN                                    CNDAIRCL600 CL6001A11   1900308EA                                                               WING            CORRODED        B  ZLJRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA17100QR                       1043                                    SURFACE CORROSION (PITTING) DISCOVERED ON BOTH WINGS LOWER SURFACES ADJACENT TO AND OB OF WHEEL WELLS, CORROSION DEEMED UNUSUALLY SEVERE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA21EA                        
             20080811     NM  2008       8          11         2008FA0000538    120080730G5753                SPAR                                    BOEING737   737448      13844BUNM  CFMINTCFM56 CFM563C     13802EU                              LT WING TE FLAP CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39742VA                       24773                                   DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA16WE   E21EU                
             20080811     CE  2008       8          11         2008FA0000539    120080502G324415117300        WHEEL                                   BEECH 200   B200        1152922CE                                                               MLG             CRACKED         B  E5WRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21200ND2738                   BB1612                                  CRACK INDICATIONS LOCATED IN BEED AREA OF WHEELS REAVEALED BY FLUORESCENT PENETRANT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4T      A24CE                        
             20080903     CE  2008       9          3          2008FA0000540    120080502G32464088            WHEEL                                   BEECH 200   B200        1152922CE  PWA   PT6   PT6*        52043EA                              MLG             CRACKED         B  HJ2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21200ND                       BB1612                                  CRACK INDICATIONS LOCATED IN BEAD AREA OF WHEELS, REVEALED BY FLUORESCENT PENETRANT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4T3  T  A24CE   E2NE                 
             20080903     WP  2008       9          3          2008FA0000541    220080801G725030753507        MODULE                                  RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              LPT             FAILED          B      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      GL03225PB3495                   258558      107662                      AIRCRAFT EXPERIENCED A VIBRATION IN FLIGHT.  CREW SHUTDOWN NR 1 ENGINE AND LANDED.  MAINT CREWS DETERMINED THE THIRD STAGE LOW PRESSURE TURBINE (LPT) MODULE HAD EXPERIENCED A BLADE FAILURE. ONE BLADE WAS MISSING A PIECE ABOUT ONE INCH LONG. MAINT ALSO DISCOVERED A CRACK IN THE THIRD STAGE STATOR WHICH EXTENDED BETWEEN ONE THIRD TO ONE HALF THE CIRCUMFERENCE OF THE HOUSING. NO OTHER ANOMALIES WERE NOTED DURING THE DISASSEMBLY OF THE ENGINE. PARTS WERE SENT TO MFG FOR INVESTIGATION AND REPAIR. (K)                                                                                                                                                                                                                            2L72 4F4  FRTA3EU    E6WE                 
             20080903     SW  2008       9          3          2008FA0000542    120080728G6220471201281       BEAM                                    BELL  47    47G         1181002SW                                                               MAIN ROTOR      CRACKED         B  E5WRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21                                                                    BEAM CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS (FMT). (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H1                           
             20080903     SW  2008       9          3          2008FA0000543    120080728G6220471201171       HUB                                     BELL  47    47G         1181002SW                                                               MAIN ROTOR      CRACKED         B  E5WRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL21                                                                    BEAM - CRACK INDICATION AT EAR END (FPT).  HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O      H1                           
             20080903     EU  2008       9          3          2008FA0000544    120080730G2421ALU8521         ALTERNATOR                              SOCATATB9   TB9         8680694EU  LYC   O320  O320D2A     41508EA                              ENGINE          FAILED          B  NI1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE03     1                                                              ALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK DURING GROUND RUNS ARE NORMAL MAX RPM DURING GROUND RUN 2400 RPM. ALTERNATOR APPEARS TO BE RPM SENSITIVE.  POSSIBLE CAUSE: BRUSHES NOT RIDING TRUE ON SLIP RING. OVERHAUL PROCESS MAY CONTRIBUTE TO PROBLEM. AN ADDITIONAN (2) ALU8521 ALTERNATORS FROM INVENTORY PRODUCE THE SAME SYMPTOMS, SN E113128 AND F043304. BOTH ALTERNATORS FAILED WITHIN 2 HOURS OF OPERATION.  BOTH WERE O/H UNITS.  (K)                                                                                                                                                                                                                     1L71 3O3  ONTAS1EU   E274                 
             20080903     CE  2008       9          3          2008FA0000545    120080712G361065550384        BELLOWS                                 CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                                              RUPTURED        B  QFYRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA6317PL                        5600412     PCEJC0312                   THE BELLOWS INSIDE THE BRADED CONNECTION CRACKED OUT LEAVING A HOLE ABOUT .75 IN IN DIA AT THE UP STREAM SIDE OF THE FLEXIBLE CONNECTOR.  THE PROBLEM WAS DISCOVERED ON A MAINT RUN UP AT WHICH TIME THE FIRE DETECTION SYS WAS ACTIVATED FROM AN OVERHEAT SITUATION.  RECOMMEND REMOVING THE ELBOWS AND CHECKING THE BELLOWS FOR CRACKS WITH A BORESCOPE.  (K)                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA22CE   E25EA                
             20080903     CE  2008       9          3          2008FA0000546    120080717G275098600581        CONTROL CABLE                           CESSNA210   T210L       2073449CE  CONT  O520  TSIO520*    17040SO                              TE FLAPS        DEFECTIVE       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW152423S                       21061275                                ORDERED NEW FLAP FOLLOW UP CABLE; TO REPLACED ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E8CE                 
             20080903     SW  2008       9          3          2008FA0000547    120080628G3260560006          DOWNLOCK                                MOONEYM20   M20B        5870206SW  LYC   O360  O360A1A     41514EA                              MLG             WORN            C      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW19745423371                   1853        L402336                     LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWNLOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WAS ON THE GROUND DURING LANDING ROLLOUT.  THIS ALLOWED GEAR TO COLLAPSE, SB M20-88B, 5-10-94.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A3     E286                 
             20080903     SO  2008       9          3          2008FA0000548    120080804G533069904000        SKIN                                    PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              FUSELAGE        CRACKED         B  L6QRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA05121TF1520                   3257351                                 UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST.  DAMAGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTENNA DURING FLIGHT.  TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT, RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 1L71 3O3  O  A3SO    E14EA                
             20080903     SO  2008       9          3          2008FA0000549    120080804G533099813004        DOUBLER                                 PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540*     41532EA                              FUSELAGE        CRACKED         B  L6QRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA05121TF1520                   3257351                                 UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST.  DAMAGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTENNA DURING FLIGHT.  TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT, RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 1L71 3O3  O  A3SO    E14EA                
             20080903     EA  2008       9          3          2008FA0000550    120080729G6300269D53085       DRIVE SHAFT                             SCWZER269   269D        8059501EA  ALLSN 250C  250C20      03013GL                              MAIN ROTOR      UNSERVICEABLE   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW17277DT674                    0028        CAE845057                   DURING PREFLIGHT, THE M/R DROOP STOP NUT WAS FOUND TO BE LOOSE. UPON FURTHER INSP IT WAS DETERMINED THAT M/R HUB SHOULD BE REMOVED TO LOOK FOR SIGNS OF WEAR. ONCE HUB WAS REMOVED AND INSPECTED, MODERATE WEAR (FRETTING) WAS FOUND ON DROOP STOP RETAINER PLATE (PN 269A1320), DROOP STOP RETAINER RING (PN 269D1329), DROOP STOP RETAINER (PN 269A1332) AND UPPER SCISSORS SUPPORT (PN 269A1328-901) TO THRUST BEARING TUBE SPACER ASSY (PN 269A13183). ONCE THESE PARTS WERE REMOVED, THE DRIVE SHAFT WAS REMOVED FOR INSP. ONCE DRIVE SHAFT WAS REMOVED THE DRIVE SHAFT THRUST BRG WAS REMOVED FOR INSP AND CORROSION WAS FOUND ON DRIVE SHAFT THRUST BRG JOURNAL. CORROSION WAS REMOVED AND FURTHER VISUAL EXAMINATION REVEALED A POSSIBLE1G71 3U3  U0 4H12    E4CE                 
             20080903         2008       9          3          2008FA0000551    220080806G7261                BEARING                                 DOUG  MD90  MD9030      3023690NM                                                               OIL PUMP        SEIZED          B  HZ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07                                                                    PUMP SEIZED, OIL PUMP BEARING BRACKET SHOWED SIGNS OF RUBBING WITH THE OIL PUMP GEAR.  PENDING ENGINEERING EVALUATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA6WE                         
             20080903     CE  2008       9          3          2008FA0000552    120080521G2910SA7670024001    LINE                                    RAYTHNDH125 HAWKER800XP 7150012CE                                                               HYD SYSTEM      RUPTURED        D      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      GL23484JC                       258644                                  HYDR FLEXABLE LINE TO RT MLG DOOR ACTUATOR RUPTURED DURING FLIGHT.  LOSS OF FLUID CAVITATED RT AND LT ENGINE DRIVE HYDR PUMPS. LINE RUPTURED IN  SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR.  PRESSURE IS 3000 PSI CONSTANT.  NO LANDING GEAR ACTUATION WAS IN PROCESS. SUSPECT MFG DEFECT. AC MFG NOTIFIED.  THIS IS FIRST INSTANCE OF THIS FOR THS AC.  LT MLG DOOR HYDR LINE RUPTURED 2 MONTHS BEFORE IN THE SAME EXACT WAY AND CAUSED THE SAME DAMAGE.  MFG NOTIFIED AGAIN.                                                                                                                                                                                                                                                             2L72 4F    RTA3EU                         
             20080903     CE  2008       9          3          2008FA0000553    120080808G2910SA7670024001    LINE                                    RAYTHNDH125 HAWKER800XP 7150012CE                                                               HYD SYSTEM      RUPTURED        D      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      GL23484JC2369                   258644                                  HYDR FLEXIBLE LINE TO THE LT LANDING GEAR DOOR ACTUATOR RUPTURED DURING FLIGHT.  LOSS OF FLUID CAVITATED LT AND RT ENG DRIVEN HYDR PUMPS.  LINE RUPTURED IN SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR.  PRESSURE IS 3000 PSI CONSTANT.  NO LANDING GEAR ACTUATION WAS IN PROCESS.  SUSPECT MFG DEFECT.  AC MFG NOTIFIED.  THIS IS SECOND OCCURRANCE FOR THIS AC.  SAME LINE RUPTURED 2 MONTH PREVIOUSLY ON RT SIDE ACTURATOR CAUSING SAME DAMAGE.  MFG AGAIN NOTIFIED. (K)                                                                                                                                                                                                                                                                 2L72 4F    RTA3EU                         
             20080902     CE  2008       9          2          2008FA0000554    120080813G7160125083029       INTAKE DUCT                             CESSNA206   TU206G      2073357CE                                                               INDUCTION BOX   CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW17602MB10                     U20604052                               MANUFACTURER SUPPLIED ENG INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS.  THIS PARTICULAR ACFT AND ANOTHER IDENTICAL MODEL ACFT THIS FACILITY MAINTAINS HAVE BEEN CONVERTED TO AN IO-550-F ENG.  AFTER THE STC CONVERSION, THE CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY.  CONTACTED THE STC HOLDER AND HAVE RESPONDED WITH A SCHEME TO REINFORCE THIS DUCT.  THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHICH MAY REQUIRE PER SUPPORT.  AT PRESENT, THE DUCTS ARE REQUIRING REPAIRS OR REPLACEMENT EVERY 50 HOURS.  A PMA REPLACEMENT DUCT MADE FROM COMPOSITE MATERIAL IS NO LONGER AVAILABLE.  (S)                                                                                 1H71 3O      A4CE                         
             20080825     EA  2008       8          25         2008FA0000555    120080804G3260                INDICATION SYS                          CNDAIRCL600 CL6002B16   1900305EA                                                               MLG             MALFUNCTIONED   C      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         LDLANDING        1                      SW99190MP                       5161                                    ON APPROACH TO KSSI, WHEN LANDING GEAR DEPLOYED, ONLY RECEIVED NOSE DOWN INDICATION, NO MAIN GEAR DOWN INDICATION.  CYCLED SEVERAL TIMES.  CREW DIVERTED TO KAGS AND USED EMERGENCY PROCEDURE TO LOWER GEAR.  ALL GEAR DOWN AND LOCKED FOR LANDING.  MAINTENANCE WAS UNABLE TO DUPLICATE.  CHECKED ADJUSTMENTS OF MAIN LANDING GEAR PROXIMITY SWITCHES, VISUALLY INSPECTED DOWNLOCK WIRING HARNESSES AND ACCOMPLISHED MAIN LANDING GEAR RETRACTION AND EXTENSION SEVERAL TIMES AND PERFORMED AN EMERGENCY EXTENSION.  NO DEFECTS NOTED.  REPLACED 4 NEW DOWNLOCK INDICATOR BULBS (PRECAUTIONARY).  A MAINTENANCE CHECK FLIGHT WAS ACCOMPLISHED AFTER MAINTENANCE WITH ALL OPERATIONS NORMAL.  THERE IS NO HISTORY OF THIS DISCREPANCY ON THIS AC2L72 4F    RTA21EA                        
             20080902     CE  2008       9          2          2008FA0000556    120080702G29311240583000      TRANSDUCER                              LEAR  60    60LEAR      5170707CE                                                               HYD PRESSURE    MALFUNCTIONED   C      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      SW99262FX633                    323                                     HYDRAULIC PRESSURE GAUGE READ ZERO ON LANDING CHECK.  FLAPS AND LANDING GEAR EXTENDED NORMALLY.  GAUGE WAS SEEN TO FLUCTUATE BETWEEN NORMAL TO 1000 PSI TO ZERO PSI ON APPROACH.  BRAKES AND THRUST REVERSERS OPERATED NORMALLY.  GAUGE READS ZERO DURING TAXI.  CREW DECLARED AN IFE AS A PRECAUTION.  MAINTENANCE REPLACED THE HYDRAULIC PRESSURE TRANSDUCER.  OPS CHECK AND LEAK CHECK PERFORMED SATISFACTORILY.  (S)                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA10CE                        
             20080826     NM  2008       8          26         2008FA0000557    120080801G2742900C2010375103  CONTROL ROD                             DOUG  MD900 MD900       3027375NM                                                               VERTICAL STAB   BROKEN          C      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      WP25902RN                       90000121                                EXPERIENCED EXCESSIVE LT PEDAL (2-3 INCHES) DURING CRUISE FLIGHT AT 70 TO 80 PERCENT TRANSMISSION TORQUE.  DURING POST FLIGHT FOUND THAT THE LT VERTICAL STABILIZER MOVED FREELY.  FURTHER INSPECTION REVEALED THAT THE LT VERTICAL STABILIZER CONTROL SYSTEM (VSCS) ACTUATOR CONTROL ROD WAS BROKEN AT THE THREADED PORTION.  (S)                                                                                                                                                                                                                                                                                                                                                                                                              1G72 3U    NCH19NM                        
             20080903     CE  2008       9          3          2008FA0000558    120080801G57530425118         FITTING                                 CESSNA140   140         2071602CE                                                               LT TE FLAP      CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0376671                       11111                                   THE PART WAS BEGINNING TO RUST THROUGH IN LOCATION RESPONSIBLE FOR ATTACHING THE LT FLAP TO THE FLAP CONTROL. THE DEFECT WAS FOUND DURING AN ANNUAL INSPECTION. PROBABLE CAUSE WAS RUSTING DUE TO AGE. A MORE THOROUGH INSPECTION OF THE AREA DURING PREFLIGHT SHOULD HELP DETECT THE PROBLEM SO THAT CORRECTIVE ACTION CAN BE TAKEN.                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NCA768                         
             20080903     EA  2008       9          3          2008FA0000559    220080810G7414                DRIVE SHAFT                             PIPER PA28  PA28R200    7102811SO  LYC   O360  IO360C1C    41514EA                              MAGNETO         BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE012952R           03092108    28R35344                                DISTRIBUTOR (POINT CAM SHAFT BROKE FLUSH WITH UPPER MAG GEAR INNER RACE CAUSING TOTAL MAG FAILURE.  PART WAS RETURNED TO OWNER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A13    1E10                 
             20080903     CE  2008       9          3          2008FA0000560    120080808G3222S18271          VALVE                                   CESSNA172   R172K       2072431CE                                                               NOSE STRUT      DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW099927V                       R1722354                                A NEW VALVE WAS ORDERED AND INSTALLED TO CURE A SUSPECTED LEAK IN THE VALVE CORE.  THE NEW VALVE ARRIVED WITH A BRIGHT APPEARANCE, EITHER CHROME OR NICKEL PLATED.  WITH THE NEW VALVE INSTALLED, THE STRUT LEAK WORSENED.  AN EXTERNAL INSP REVEALED THAT THE COSMETIC PLATING WAS FLAKING FROM THE HEX FLATS.  THE VALVE WAS REMOVED AND IT WAS FOUND THAT THE PLATING WAS ALSO FLAKING IN THE THREAD-AREA, AND THIS RESULTED IN A LEAK AROUND THE VALVE.  THIS VALVE EMPLOYS A NPT THREAD (1/4 INCH PIPE THREAD) AND THE THREADS FORM THE SEAL WHEN INSTALLED.  THE REMAINING PLATING WAS EASILY SCRAPED FROM THE THREADS WITH A PICK AND THE VALVE WAS REINSTALLED WITHOUT FURTHER DIFFICULTY.  SUBMITTER ADMITS THAT THE PLATING RESULTS IN1H71 3O      3A17                         
             20080903     SO  2008       9          3          2008FA0000561    120080513G2497                WIRE                                    PIPER PA44  PA44180     7104402SO  LYC   O320  O320*       41508EA                              ALTERNATOR      BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO152163F           H092370     447995167                               INTERNAL FAILURE DUE TO BROKEN WIRES INTERNALLY, HEAVY SPARKING INSIDE ENGINE COMPARTMENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A19S0   E274                 
             20080903     CE  2008       9          3          2008FA0000562    120080627G531112943003723     FRAME                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6*        52043EA                              FS 363.25       CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03534M 10817                  UE333                                   DURING STRUCTURAL INSP, FOUND LOWER FRAME WEB CRACKED AT FLANGE CORNER.  TEE ATTACHED TO FRAME CRACKED THRU LOWER RIVET HOLE.  DOUBLER ATTACHED TO LOWER AFT SIDE OF WEB WAS ALSO CRACKED.  THE AFT CLIP, ATHAT ATTACHES THE LOWER FRAME TO THE SIDEWALL SEAT TRACK STRINGER, WAS LEFT OUT AT BUILD.  THE STRESSES NOT BEING TRANSFERRED TO SUPPORTING STRUCTURE, BECAUSE OF THE MISSING CLIP, MAY HAVE ADDED TO THE FRAME FAILURE.  THE DAMAGE WAS REPAIRED IAW SRM AND DER REPORT.  (K)                                                                                                                                                                                                                                                       2L72 4T3  TRTA24CE   E2NE                 
             20080903     CE  2008       9          3          2008FA0000563    120080808G28105038903417      FUEL CELL                               BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE                              LT WING         PLUGGED         B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03350RV60                     FL585                                   PILOT REPORTED FUEL IMBALANCE OF 200 LBS AFTER TOPPING OFF TANKS.  FUEL QUANTITY INDICATING AND FUEL VENT SYSTEM WERE CHECKED AND CONFIRMED GOOD.  DURING DEFUEL, NOTED THAT LT WING TRANSFER TO LT NACELLE TANK WAS TOO SLOW TO ALLOW FULL SERVICING OF LT WING FUEL SYSTEM .  ACCESSED FUEL TRANSFER TUBE FROM INSIDE OF LT IB AFT FUEL CELL, TO NACELLE FUEL TANK, AND FOUND IT PLUGGED WITH A RAG.  REMOVED RAG, CLEANED WING FUEL STRAINER, AND SECURED FUEL SYSTEM.  LT FUEL SYSTEM CAN NOW BE SERVICED TO FULL.  (K)                                                                                                                                                                                                                     2L72 4T4  TRTA24CE   E4EA                 
             20080903     CE  2008       9          3          2008FA0000565    120080813G7160125083029       INTAKE DUCT                             CESSNA206   TU206G      2073357CE  CONT  O550  IO550*           SO                              ENGINE          CRACKED         B  RC0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW17602MB10                     U20604052                               MFG SUPPLIED ENGINE INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS.  THIS PARTICULAR AC AND ANOTHER IDENTICAL MODEL AC THIS FACILITY MAINTAINS, HAVE BEEN CONVERTED TO ANOTHER ENGINE AFTER THE STC CONVERSION.  CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY.  HAVE CONTACTED STC HOLDER, THEY HAVE RESPONDED WITH A SCHEME TO REINFORCE THIS DUCT.  THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHEICH MAY REQUIRE DER SUPPORT.  AT PRESENT, THE DUCTS ARE REQUIRING REPAIRS OF REPLACEMENT EVERY 50 HOURS.  A PMA REPLACEMENT DUCT MADE FROM COMPOSITE MATERIAL IS NO LONGER AVAILABLE. (K)                                                                                             1H71 3O3  O  A4CE    E3SO                 
             20080827     NM  2008       8          27         2008FA0000566    120080218G7830315A2502102     PANEL                                   BOEING737   737         UTILSYSNM                                                               THRUST REVERSER DELAMINATED     B  Z6WRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07     33297                                                          THE TRANSLATING SLEEVE OF THE NR2 OTBD THRUST REVERSER HALF, INNER BOND PANEL ASSY (ACOUSTIC) HAS AN AREA APPROXIMATELY 30 INCHES X 85 INCHES WHERE THE PANEL HAS DELAMINATED/SEPARATED FROM THE CORE.  THIS AREA STARTED AS 12 SMALL AREAS OF DELAMINATION AND CONTINUES TO GROW.  THE PANEL IS BEING  SCRAPPED AS A RESULT.  THE BONDING SURFACE OF THE PERFORATED PANEL APPEARS TO HAVE BEEN INADEQUATELY PREPPED PRIOR TO BONDING IN THE ORIGINAL BUILD.  THIS CONDITION WAS DISCOVERED AT SPIRIT AEROSYSTEMS REPAIR STATION Z6WR3367 WHERE IT WAS SENT FOR REPAIR FROM CONTINENTAL AIRLINES.  (S)                                                                                                                                          2L72 4F    RTA16WE                        
             20080828     NM  2008       8          28         2008FA0000567    120080822G5313                LONGERON                                DOUG  MD80  MD83        3023681NM                                                               BS 154 L23L     DAMAGED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15874GA                       49643                                   DURING SCHEDULED REPAIR, FOUND DOUBLE DRILLED ON LONGERON 23L AT FS 154.5.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RT                             
             20080828     NM  2008       8          28         2008FA0000568    120080822G5313                LONGERON                                DOUG  MD80  MD83        3023681NM                                                               BS 150 L23L     DAMAGED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15874GA                       49643                                   DURING SCHEDULED REPAIR, MISDRILLED 3 EACH HOLES AT FS 150 AND 3 INCHES BELOW LONGERON 23L.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RT                             
             20080903     EU  2008       9          3          2008FA0000570    120080729G6220704A33651158    BEARING                                 SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1     60030NE                              M/R SWASHPLATE  WORN            B  P49RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65277HC688        M1687       2052                                    COMPLIED WITH 2 YEAR / 500 HR INSP.  TASK 62.30.00.601 M/R SHAFT INSP.  WHILE PERFORMING INSP OF SWASHPLATE GUIDE UNIBALL FOUND WHILE ROTATING SWASHPLATE.  UPPER SEAL FOR BRG WAS NOT ROTATING BECAUSE IT WAS NOT FIRMLY ATTACHED TO OUTER RACE OF BRG WITH THE SEAL BEING LOOSE & UNSECURED IT WORE INTO SWASHPLATE BRG OUTER STOP RING.  REPLACED SWASHPLATE BRG, OUTER STOP RING WITH NEW.  RECOMMENDATION WOULD BE WHILE GREASING SWASHPLATE BRG DURING 100 HOUR INSP, LIFT SWASHPLATE BOOT TO INSPECT BRG SEAL FOR MOVEMENT DURING ROTATION. (L)                                                                                                                                                                                          1G71 3U3  UNCH9EU    E19EU                
             20080903     CE  2008       9          3          2008FA0000571    120080722G2730                CONTROL CABLE                           MTSBSIMU2   MU2B36A     5780413CE                                                               ELEVATOR        BROKEN          B  IZ2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15868MA9216                   708SA                                   PILOT COMPLAINED OF POOR ELEVATOR TRIM OPS.  UPON INSP, FOUND ELEVATOR TRIM CABLE 311AS-14-7245 BROKEN (RT CABLE).  311AS-14-7362 (LT CABLE), 010A-61179-81 (RT AFT) CABLES FRAYED.  IDLER PULLEY SHAFT ON PITCH TRIM SERVO SHEARED.  REPLACED CABLES & SERVO, OPS CHECKED.  RIGGED AS NEEDED.                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3T      A10SW                        
             20080903     SO  2008       9          3          2008FA0000572    120080818G323335380000000     ACTUATOR                                GULSTMG159  G159        3952202SO  GARRTTTFE731TFE7314R    01518WP                              RT MLG          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM075950C774                    213                                     RT MLG SIDE BRACE ACTUATOR LEAKING FROM SWITCH ASSY.  SIDE BRACE ACTUATOR REMOVED, REPLACED WITH REPAIRED ACTUATOR ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  F  1A17    E6WE                 
             20080903     CE  2008       9          3          2008FA0000573    120080821G28421183810025      FLOAT VALVE                             RAYTHN390   390         7150030CE                                                               FUEL TANK       SEPARATED       D      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      WP013725L1219                   RB155                                   DURING 1200 HR INSP WHICH REQUIRES OPENING ALL WING AND FUSELAGE FUEL TANK ACCESS PANELS FOR INTERNAL INSPECTION IN BOTH LT & RT CTR FUSELAGE TANKS, FWD FLOAT VENT VALVES FLOAT SECTION OF VALVE ASSY WAS FOUND SEPARATED AND LAYING LOOSE INSIDE FUEL TANK AREA.  RECOMMEND INSP OF LT & RT FWD VENT VALVE FLOAT ASSEMBLIES AT NEXT EARLIEST TIME OR INSP.  REPLACE ALL SUSPECTED OR FAULTY FLOAT VALVES.                                                                                                                                                                                                                                                                                                                                     1L72 3F    RTA00010WI                     
             20080903     SO  2008       9          3          2008FA0000574    220080815G7414                IMPULSE COUPLING                        CESSNA182   182N        2072730CE  CONT  O470  O470R       17026SO  MCAULY2A34C 2A34C203    GL  MAGNETO         FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07925511736                   18260256    275543R     891141          PILOT PERFORMED PRE-FLIGHT INSP DISCOVERED OIL ON FWD PORTION OF COWLING, SLIGHT OIL RESIDUE ON WINDSHIELD.  MECHANIC REMOVED TOP COWLING TO INVESTIGATE, DISCOVERED MAGNETO HOUSING SHATTERED AT AREA IMMEDIATELY ADJACENT TO IMPULSE COUPLING.  APPARENTLY IMPULSE COUPLING ENGAGING MECHANISM SOMEHOW CONTACTED ACTUATING PIN WHILE OPERATING (OR ENGINE BACKFIRED, WE DON`T HAVE FURTHER INFORMATION TO ASCERTAIN THIS CONDITION) SHATTERED MAGNETO BODY HSG.  MAGNETO WAS STILL FIRING, FIXED TO ENGINE (NOT LOOSE) ENGINE OPS WAS REPORTED NORMAL UPON ARRIVAL OF LAST FLIGHT, WHICH SEEMS TO INDICATE THAT MAGNETO HAD OPERATED IN THIS CONDITION FOR WHAT APPEARS TO BE AT LEAST AN HOUR OR MORE.  NO MISFIRE OR MAGNETO DROP DETECTED. 1H71 3O3  ONT3A13    E273    5  CP3EA     
             20080904     NM  2008       9          4          2008FA0000575    120080821G2421                SHAFT                                   DOUG  MD90  MD9030      3023690NM                                                               AC GENERATOR    SEIZED          C  HZ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07     17572      436                                                 GENERATOR UNIT SEIZED. THE GENERATOR FAILURE ROOT CAUSE WAS DETERMINED TO BE A ROTOR BAND SHAFT WHICH RESULTED IN AN OUT OF BALANCE CONDITION. THE OUT OF BALANCE ROOT CAUSED AN EARLY FAILURE OF THE ADE BEARING. ALL OTHER DAMAGE RESULTED FROM THE BEARING FAILURE. PENDING ENGINEERING EVALUATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA6WE                         
             20081001     EA  2008       10         1          2008FA0000577    220080612G8530AEL12688P020    VALVE SEAT                                                                 LYC   O360  IO360A1A    41514EA                              CYLINDER HEAD   DAMAGED         B  Y2GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA23                                                                    INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD.  THE LOOSE SEAT DAMAGE TO THE CYLINDER HEAD, VALVE, AND VALVE SEAT.  INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT.  THIS WAS AN OVERHAULED CYLINDER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        3  O          1E10                 
             20081001     EA  2008       10         1          2008FA0000578    220080716G8530AEL12688P020    VALVE SEAT                                                                 LYC   O360  IO360C1E6   41514EA                              CYLINDER HEAD   DAMAGED         B  Y2GRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA23                                                                    INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD.  THE LOOSE SEAT DAMAGE TO CYLINDER HEAD, VALVE, AND VALVE SEAT.  INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT.  THIS WAS AN OVERHAULED CYLINDER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            3  O          1E10                 
             20080909     SO  2008       9          9          2008FA0000579    120080610G2916                RESERVOIR                               PIPER PA31  PA31325     7103105SO  LYC   O540  LTIO540F2BD 41533EA                              HYD SYSTEM      LOW             G      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CE01727HB                       318112006   L266868A                    ON FINAL APPROACH THE LANDING GEAR HANDLE WAS PLACED IN THE DOWN POSITION.  THE GEAR WAS VIEWED IN THE MIRROR AT 45 DEGREE ANGLE.  THERE WERE NO GREEN LIGHTS INDICATING GEAR DOWN AND LOCKED. THE PILOT TRIED TO RAISE AND LOWER THE GEAR AGAIN WITH NO MOVEMENT EITHER DIRECTION.  THE PILOT THEN PROCEEDED TO MANUALLY PUMP THE GEAR DOWN.  AFTER THREE GREEN LIGHTS WERE ON, THE AIRCRAFT WAS FLOWN BACK, WITH THE GEAR DOWN.  MAINT NOTE: HYDR RESERVOIR WAS FOUND TO BE IMPROPERLY SERVICED. TRAINING WAS CONDUCTED FOR ALL MAINT ON PROPERLY SERVICING THE POWERPACK.  THIS CAN BE TRICKY AS IT IS DIFFICULT TO SEE THE FLUID LEVEL.  (K)                                                                                                1L72 3O3  O  A20SO   E14EA                
             20080909     CE  2008       9          9          2008FA0000580    120080827G2435                BEARING                                 CESSNA500   S550        2076607CE  PWA   JT15  JT15D4      52112NE                              STARTER GEN     FAILED          B  OW5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL27802Q            95264       S5500157    PCE102330                   FRONT BEARING FAILURE IN FLIGHT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4F4  FRTA22CE   E1NE                 
             20081001     SO  2008       10         1          2008FA0000581    120080812G5100SL53E19600      VERNATHERM                              PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL                  FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      AL0327663392                    317852094   L152068A    DJ10231A        THIS VERNATHERM HAD A SHAFT AND NUT ASSY THAT WAS SECURED WITH A ROLL PIN.  THE SHAFT FAILED AT ROLLPIN.  THE NUT, SHAFT PIECE AT ROLLPIN TRAVELED THRU THE OIL GALLY AND LODGED AT A FITTING.  HIGH OIL TEMP ALERTED US TO THIS FAILURE, OIL PRESSURE WAS NORMAL.(K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081006     EA  2008       10         6          2008FA0000583    220080708G8530                CYLINDER HEAD                           CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C16    GL  ENGINE          SEPARATED       G      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      WP195268U                       172RG0314   RL2898936A  04136           ON JULY 8, 2008, MADE AN EMERGENCY LANDING IN DESSERT TERRAIN AFTER THE ENGINE BEGAN TO EXHIBIT SEVERE VIBRATIONS, LOSS OF POWER AND  SMOKE.  THE NR 2 CYLINDER WAS FOUND TO HAVE SEPARATED FROM THE CASE, SEVEN OF THE EIGHT HOLD STUDS WERE FOUND TO HAVE SHEARED.  ONLY ONE HOLD DOWN STUD WAS LT INTACT.  THERE WAS NO HISTORY IN THE AC LOGS TO INDICATE IF THE HOLD DOWN STUDS HAD BEEN REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A17    E286    5  CP7EA     
             20080909     CE  2008       9          9          2008FA0000584    120080731G2510551900921       SEAT FRAME                              CESSNA500   550         2076604CE                                                               COCKPIT SEAT    CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0564TF                        5500064                                 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  CHAIR WAS REPAIRED IAW STO-1042WI STRUCTURAL SEAT REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 4F      A22CE                        
             20081006         2008       10         6          2008FA0000585    120080818G242111522185        GENERATOR                                                                                                                                               FAILED          B  HZ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07     1572                                                           FAILS SATURATION CURVE CHECK-ZERO VOLTS ANY PHASE. BROKEN LOWER CROSSOVER ON ROTOR.  PENDING ENGINEERING EVALUATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20081003     EA  2008       10         3          2008FA0000586    220080915G8520TT73806         PUSHROD                                                                    LYC   O235  O235L2C     41505EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP11                                        L1972215                    (3) PUSHRODS (TT73806) WERE INSTALLED IN THIS ENGINE AND ALL 3 HAD APPROXIMATELY A .3750 INCH VERTICAL CRACK ON BOTH ENDS. CAUSE UNKNOWN - NO RECOMMENDATIONS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E223                 
             20081006         2008       10         6          2008FA0000587    420080819G6113D57691P         DOME                                    MOONEYM20   M20E        5870212SW  LYC   O360  IO360A1A    41514EA  HARTZLHCC2Y HCC2YR1     GL  SPINNER         CRACKED         B  NT3RO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      WP259485V22                     700043                  CH42078B        THE SPINNER ASSY FAILED IN FLIGHT ON A 2.2 HR FLIGHT LEG. APPROXIMATELY 1.5 HRS INTO THE FLIGHT A SMALL SHUDDER WAS FELT AND ALL INDICATION CHECKED NORMAL. THE AC COMPLETED THE FLIGHT AND IT WAS NOTED THAT 4" X 4" SECTION OF THE SPINNER BROKE OFF. THE COWLING HAD TWO SCRAP MARKS AND NO OTHER DAMAGE WAS NOTED.  MFG SL-61-286 WAS ACCOMPLISHED 7.31 HRS PRIOR TO FAILURE. OWNER REPORTS SPINNER WAS CHECKED ON PREFLIGHT APPROXIMATELY 1.5 HRS PRIOR TO FAILURE. SPINNER TT 21.64 HRS. PROBABLE CAUSE: SPINNER DOME IS TOO LARGE FOR A SPINNER WITHOUT A FORWARD BULKHEAD FOR SUPPORT. (K)                                                                                                                                              1L71 3O3  O  2A3     1E10    5  CP920     
             20081003     SO  2008       10         3          2008FA0000588    120080826G3220502341          BOLT                                    PIPER PA44  PA44180     7104402SO                                                               NG LOCKING PAW  SHEARED         D  MOVVK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP21239AT                       4496038                                 DURING FAA CHECK RIDE, THE NOSE LANDING GEAR DID NOT PROVIDE A GREEN LIGHT AND THE GEAR UNSAFE WARNING LIGHT AND HORN OPERATED. AFTER AN UNEVENTFUL LANDING. THE ACFT WAS BROUGHT INTO MAINT FOR TROUBLESHOOTING AND REPAIRS. THE PIVOT BOLT FOR THE NOSE GEAR LOCKING PAW HAD SHEERED IN TWO. THE FAIL POINT IS LOCATED 1.25 INCHES FROM THE BOTTOM OF THE BOLT HEAD. THIS PREVENTED THE PAW FROM ACTUATING PROPERLY AND CLOSING THE DOWN LIMIT SWITCH. UPON REPLACEMENT WITH A NEW BOLT, THE PAW ACTUATED PROPERLY AND THE GEAR RETRACTION AND EMERGENCY EXTENSION WERE NORMAL WITH PROPER INDICATIONS.  (K)                                                                                                                                  1L72 3O      A19S0                        
             20081006     GL  2008       10         6          2008FA0000589    120080826G2110220045510       DRIVE SHAFT                             CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              COMPRESSOR      SHEARED         B  5CSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05433CF                       0710                                    THIS AC HAS HAD 5 FAILURES OF THE AIR CONDITIONING COMPRESSOR DRIVE SHEAR SHAFT. THE AVERAGE TIME BETWEEN FAILURES IS 35.8 HOURS. THE SAME SHAFT BUILT BY ANOTHER MFG, HAS HAD ZERO FAILURES. WE HAVE HAD SEVERAL FAILURES IN DIFFERENT AC WITH THIS PART. THE DESIGN OF THE OTHER SYSTEM SHAFT IS SLIGHTLY DIFFERENT.  MFG WILL NO LONGER COVER THIS PART UNDER WARRANTY. WE HAVE TRIED SEVERAL RECOMMENDATION FROM MFG TO SOLVE THIS PROBLEM TO NO AVAIL. (K)                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA00009CHE3SO                 
             20081006     CE  2008       10         6          2008FA0000590    120080813G3222998201005       STRUT                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              NLG             MALFUNCTIONED   C  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL031250                        FA88                                    POSITION OF THIS TORQUE LINK MOUNT RELATIVE TO THE SHIMMY DAMPNER ARMS HOLE ARE SUCH THAT THE TWO PARTS INTERFERE WITH EACH OTHER AND DONT ALLOW THE STRUT TO COMPRESS CLOSER THAN 2 INCHES FROM FULLY COLLAPSED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  T  A24CE   E4EA                 
             20081003     EA  2008       10         3          2008FA0000591    220080805G8520ST203P010       PISTON RING                             CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA                              ENGINE          MISMANUFACTURED D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE032170Q25                     177RG0570   L1256851A                   ENGINE WAS OVERHAULED USING MFG PISTON RINGS ST203P010. AFTER 25.4 HRS, RINGS STILL NOT SEATED AND EXCESSIVE BLOW-BY WAS FOULING PLUGS. REPLACED WITH ANOTHER SET OF ST203P010 AFTER HAVING CYLINDERS REWORKED. AFTER 4.2 HRS, ENGINE WAS OPERATING SO POORLY, DUE TO BLOW-BY, THAT IT WAS CONSIDERED UNSAFE AND GROUNDED.  INDEPENDENT HARDNESS TESTING BY QUALITY TESTING SVCS, INC, COMFIRMED THE RINGS WERE SOFT. COMPARATIVE TESTS WERE PERFORMED AGAINST PISTON RINGS. AFTER SWITCHING TO OTHER, THERE HAVE BEEN NO PROBLEMS.(K)                                                                                                                                                                                                          1H71 3O3  O  A20CE   1E10                 
             20081006     CE  2008       10         6          2008FA0000592    120080821G323012801111        SWIVEL FITTING                          CESSNA182   R182        2072734CE                                                               LT GEAR LEG     FAILED          H      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL034652T                       R18201725                               BRAKE SWIVEL JOINT FAILED LEADING TO FAILURE OF LT BRAKE WHEN EXITING RUNWAY. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O    RT3A13                         
             20081006     EU  2008       10         6          2008FA0000593    120080811G3520MC1014101       OXYGEN MASK                             BRAERODH125 BAE125800A  1500285EU                                                               CABIN           FAILED          D  G13RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13862CW                       258062                                  THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY THERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMENDATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY.(K)                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA3EU                         
             20081006     EU  2008       10         6          2008FA0000594    120080811G3520MC1014101       OXYGEN MASK                             BRAERODH125 BAE125800A  1500285EU                                                               CABIN           DAMAGED         D  G13RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13897CW                       258077                                  THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY THERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMENDATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY. (K)                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA3EU                         
             20081007     EA  2008       10         7          2008FA0000595    120080821G324160025663        PCB                                     CNDAIRCL600 CL600*      1900302EA                                                               MLG             UNSERVICEABLE   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01604SJ           JAN82118    1042                                    UPON LANDING, THE LT OB TIRE BLEW. UPON INSP, TIRE SHOWED SIGNS OF A SEVERE SKID. TESTED THE ANTISKID SYS & TESTED NORMAL. TESTED ALL 4 WHEEL SPEED SENSORS AND FOUND THAT WITH THE BRAKES SET & FULL HYD PRESSURE ON, BOTH OB MAIN WHEELS WOULD NOT RELEASE WHEN SPINNING STOPPED ON WHEEL SPEED SENSORS. BOTH IB WHEELS RELEASED NORMALLY WHEN TESTED. CONTACTED MFG TECH SUPPORT & INFORMED THE COMPUTER HAD 2 IDENTICAL PCB CARDS THAT COULD BE SWAPPED FOR TROUBLESHOOTING PURPOSES. ONE CARD IS FOR THE IB MAIN WHEELS AND 1 CARD IS FOR THE OB MAIN WHEELS. SWAPPED CARDS AND THE PROBLEM FOLLOWED TO THE IB MAIN WHEELS. NOW THE OB MAINS WOULD RELEASE NORMALLY DURING A SIMULATED SKID CONDITION BUT THE IB MAINS WOULD NOT RELEASE. R2L72 4F    RTA21EA                        
             20081007     CE  2008       10         7          2008FA0000596    120080821G782083004           MUFFLER                                 CESSNA150   150H        2071818CE  CONT  O200  O200A       17020SO                              ENGINE          FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW0522355339                    15068233    682287A                     END CAP SEPARATED (CLEAR BREAK) FROM MUFFLER CAR.  FAILURE OCCURED IN THE BEND RADIAS OF END CAP. NOT IN THE END CAP TO MUFFLER CAP, WELD. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  3A19    E252                 
             20081003     NE  2008       10         3          2008FA0000597    220080826G7250305086010       SUPPORT                                 AMD   FALC50FALCON2000  2730170NM  CFE         CFE73811B        NE                              NR 4 BEARING    CRACKED         B  ZN3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0748CG 3031                   041         P105194                     THE NR 4 BEARING SUPPORT, PN 305086010, CRACKED CAUSING THE ENGINE TO SEIZE. AT OPERATING TEMPERATURES, THE NR 4 BEARING SUPPORT AND INVESTMENTCAST MANIFOLD MAY HAVE BECAME LOOSE, PERMITTING RELATIVE MOVEMENT BETWEEN THE PARTS. SB CEF738-7 2-8060 REPLACES THE NR 4 BEARING SUPPORT WITH SUPPORT ASSY PN 305086012, WHICH HAS BEEN DESIGNED WITH AN INCREASED INTERFERENCE FIT TO ELIMINATE MOVEMENT. (K)                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA50NM   E44NE                
             20081007     GL  2008       10         7          2008FA0000598    120080814G5344DA4522100002    HINGE                                   DIAMONDA40  DA40        2990002GL                                                               AFT PAX DOOR    BROKEN          D  L10RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11681DS523                    40611                                   THE REAR CABIN DOOR AFT HINGE HAS BROKE AS DECRIBED IN AC 43-16A ALERT 360.  PROBABLE CAUSE IS REAR HOLD-OPEN CYLINDER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O    NTA47CE                        
             20081006     GL  2008       10         6          2008FA0000599    120080814G5210DA4522100002    HINGE                                   DIAMONDA40  DA40        2990002GL                                                               AFT CABIN DOOR  CRACKED         D  L10RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11504DS                       40204                                   THE REAR CABIN DOOR AFT HINGE HAS A CRACK IN THE SAME AREA AS DESCRIBED IN AC 43-16A ALERT 360. PROBABLE CAUSE IS REAR HOLD-OPEN CYLINDER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O    NTA47CE                        
             20081006     CE  2008       10         6          2008FA0000600    120080702G3240                BRAKE ASSY                              CESSNA525   525B        2076616CE  WILINTFJ44  FJ44        66000GL                              MLG             MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL0392MA                        525B0048                                NORMAL LANDING UNTIL BRAKE APPLICATION, AT BRAKE APPLICATION AC YAWED AGRESSIVELY TO THE LT. AC WAS CONTROLLED WITH RT BRAKE AND NOSE WHEEL STEERING. RT BRAKE APPEARED WEAK, AS SPEED DECREASED DIRECTION CONTROL WAS HARDER TO MAINTAIN. AC DECELERATED SLOWER THAN NORMAL APPROACHING END OF RUNWAY. EMERGENCY BRAKE WAS APPLIED. LT BRAKE GRABBED FORCING THE ACFT OFF THE RUNWAY INVESTIGATION IN TO SOURCE OF THE PROBLEM IS ON GOING.  PN AND PART NAME WILL FOLLOW AFTER MFG TEST COMPONENTS. (K)                                                                                                                                                                                                                                       1L72 4F4  FRTA1WI    E3GL                 
             20081003     CE  2008       10         3          2008FA0000601    120080901G8011149NL           STARTER                                 CESSNA172   172S        2072439CE                                                               ENGINE          FAILED          B  NO1YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35GMEGS55                     10723                                   STARTER MOTOR FAILURE, AFTER PRE-FLIGHT CHECK, THE STARTER MOTOR WAS UNABLE TO TURN THE ENGINE OVER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O    NT3A12                         
             20081003     CE  2008       10         3          2008FA0000602    120080814G792199103434        OIL COOLER                              CESSNA208   208         2073702CE  PWA   PT6   PT6A114     52043NE                                              CRACKED         B  MT9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW059762F                       20800181    PCE17397                    UPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3T3  TNTA37CE   E4EA                 
             20081003     CE  2008       10         3          2008FA0000603    120080723G2820                RING                                    RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              REFUELING SYS   DISLODGED       W  NUUYK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA35390EV                       RB                                      PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INSTALLED. FUEL LEAK FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AC. THE FUEL FLOWING UP THE OUTSIDE OF THE ACFT HAS BEEN DRAWN INTO THE REAR MAINT BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPRAYED OVER FLYING CONTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAIL CONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITCH TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED. (K)                                                                                                                                     1L72 3F4  FRTA00010WIE3GL                 
             20081003     GL  2008       10         3          2008FA0000604    120080814G5610                CANOPY                                  AMTR  ZODIACCH601XL     05615PWGL                                                               COCKPIT         DAMAGED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05451BB                       601051S                                 CANOPY OPENED IN FLIGHT RESULTING IN THE ACFT ENTERING INTO A NOSE DIVE ATTITUDE AND IMPACTING THE GROUND SERIOUSLY INJURING ONE PILOT AND MINOR INJURIES TO THE OTHER PILOT. THE CANOPYS LOCKING MECHANISMS AND OVERALL STRUCTURE DO NOT SEEM RELIABLE. THE LT AND RT LATCHING POINTS BOLTS DO NOT APPEAR TO BE LONG ENOUGH AND/OR PROVIDE ENOUGH MATERIAL FOR THE CANOPY LOCKS TO LATCH DOWN ON. THE CANOPY PLEXIGLASS IS VERY THIN AND COVERS A LARGE CANOPY AIRFRAME AREA WHICH MAKES THE CANOPY LOOSE AND WOBBLY. THE TWO GASEOUS RETRACT/ EXTEND SHOCKS ON EACH SIDE OF THE FWD CANOPY ALSO APPEAR TO BE TOO STRONG (40 PSI EACH) WHICH MAY CAUSE THE CANOPY TO HAVE A TENDENCY TO EXTEND IN THE OPEN POSITION IN FLIGHT. IN GENERAL, THE1L71         EXPA1L71                     
             20081003     CE  2008       10         3          2008FA0000605    120080807G3246D30260          WHEEL                                   CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              LT MLG          FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE179925V4450                   17264559                                AFTER LANDING,  WHILE TAXIING, HEARD A LOUD BANG. THEN ANOTHER BANG AND THE ACFT DROPPED LEFT. STOPPED, CONTACTED GROUND AND ASKED FOR ASSISTANCE. FOUND THE LT MAIN TIRE FLAT AND OUTER RIM FROM THE LT MAIN WHEEL WAS LYING 6 FT BEHIND ACFT, THE ATTACH BOLTS WERE SCATTERED ACROSS THE TAXIWAY. COULD ONLY FIND FOUR OF THE SIX BOLTS. ASI EXAMINATION OF THE WHEEL, THERE WAS A SPLIT IN THE INNER TUBE AND THE FOUR OUTER RIM ATTACH BOLTS THAT WERE FOUND HAD METAL FROM THE CENTER WHEEL HUB EMBEDDED IN THE BOLT THREADS WHERE THEY HAD PULLED OUT OF THE HUB.  TWO BOLTS WERE NOT LOCATED.  INSPECTED THE BOLT ATTACH AREAS OF THE HUB WITH A  MAGNIFYING GLASS, FOUND SOME CORROSION BUT NO APPARENT CRACKS NOTED.  IT APPEARS THAT E1H71 3O3  ONT3A12    E274                 
             20081006     CE  2008       10         6          2008FA0000606    120080815G322263420003        FORK                                    CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              NLG             BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25300BV1928                   5250418                                 DURING ROUTINE TAXI TO PERFORM MAINT CHECKS AFTER AC HAD BEEN PAINTED, NOSE GEAR AXLE BROKE LOOSE FROM NOSE GEAR STRUT. INVESTIGATION SHOWED BOTH WHEEL BEARING HAD HEAVY RUST AND DID NOT TURN FREELY ON THE AXLE. VERY LITTLE GREASE WAS FOUND IN EIGHER OF THE NOSE WHEEL BEARINGS. IT APPEARS THAT DURING THE TAXI, THE BEARINGS SEIZED ON THE AXLE AND THE RESULTANT STRESS AND HEAT CAUSED ONE SIDE OF THE NOSE STRUT ASSY TO BREAK WHICH IN TURN ALLOWED THE NOSE WHEEL AND AXLE TO COCK AND BEND THE OTHER SIDE OF THE NOSE STRUT. IMPROPER LUBRICATION OF THE NOSE WHEEL BEARINGS IS SUSPECTED AS A PROBABLE CAUSE.  (K)                                                                                                               1L72 4F4  FRTA1WI    E3GL                 
             20081007     NE  2008       10         7          2008FA0000607    220080906G7250BRR19985        TURBINE BLADES                          GULSTMGV    GULFSTREAMGV3980116SO  RROYCEBR700 BR700710A110     NE                              HP TURBINE      CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP01551GA3516                   606         11325                       DURING A RECENT MID LIFE INSPECTION OF THIS ENGINE BY THE MFG, 58 OF 74 FIRST STATE TURBINE BLADES WERE FOUND  CRACKED BEYOND SERVICEABLE LIMITS. THIS WAS A HIGH FAILURE RATE CONSIDERING THE LOW TOTAL ENGINE HOURS. A REPORT FROM THE MFG INTENDING TO PROVIDE AN UNDERSTANDING FOR THE HIGH RATE OF FAILURE STATED THAT SAND WAS INGESTED AND WAS BLOCKING SOME COOLING HOLES LEADING TO THERMAL STRESSES WHICH CAUSED THE CRACKS.  OF INTEREST IS THAT WHILE BOTH ENGINES ON THIS PARTICULAR AIRFRAME WERE NEVER SEPARATED SINCE NEW AND ALWAYS OPERATED IDENTICALLY BY THE SAME CREWS, AND BOTH INSPECTED AT THIS TIME, ONLY ONE ENGINE EXHIBITED THIS ALARMINGLY HIGH RATE OF FAILURE TO THE STAGE 1 BLADES. THE SISTER ENGINE EXHIBITED 2L72 4F4  FRTA12EA   E00057EN             
             20081007     GL  2008       10         7          2008FA0000608    220080904G72002544198         BEARING         HONEYWELL               BELL  206   206L1       1182107SW  ALLSN 250C  250C30      03013GL                              PT GOVERNOR     FAILED          B  HEFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP01396RL     1648  BR44409     45396       890360                      SPOOL BEARING ASSY (PN 2544198) FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT (PN 2539033) GUIDE POST AND FORK ON GOVERNOR LEVER ASSY. (PN 2523293) TO BEND. ONE FLYWEIGHT (PN 2544200) WAS DAMAGED FROM THE SPOOL BEARING CHAFING. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E1GL                 
             20081003     GL  2008       10         3          2008FA0000609    220080905G7230                BLADE                                   BELL  206   206B3       1181506SW  ALLSN 250C  250C20J     03013GL                              COMPRESSOR      FAILED          B  HEFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0143MA 6228 2904  KR66644     4156                                    THIRD STAGE COMPRESSOR BLADE, ONE OF THE BLADES WAS "THROWN" FROM THE PART.  NOTE: THIS COMPRESSOR WHEEL IS A ONE-PIECE BLADE DISK. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
             20081003     GL  2008       10         3          2008FA0000610    220080908G72002544198         BEARING                                 BELL  206   206L4       1182110SW  ALLSN 250C  250C30      03013GL                              SPOOL           FAILED          B  HEFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP01520RL2932 942               52052       CAE895008                   SPOOL BEARING ASSY FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT GUIDE POST AND FORK IN GOVERNOR LEVER ASSY TO BEND.  THE UPPER BEARING LOWER SHIELD AND RETAINER HAS COME OFF.  THE LOWER BEARING IS INTACT BUT NO LONGER ROTATES. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  UNCH2SW    E1GL                 
             20081007     SO  2008       10         7          2008FA0000611    120080814G32004049B           TUBE                                    MAULE MX7   MXT7160     5470204SO  LYC   O320  O320*       41508EA                              AT FORK OLEO    SHEARED         B  TODRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0731865572                    17003C                                  OLEO TUBE (PN 4049B) SHEARED OFF AT FORK ASSY (PN 4086E) UPON LANDING DAMAGE DONE TO PROP, ENGINE, ENGINE MOUNT, NOSE GEAR MOUNT, FIREWALL M ATTACH POINTS, LOWER COWL, AIR INTAKE PLUS ANY HIDDEN DAMAGE FOUND ON INSPECTION.  PN FOUND ON MFG DRAWING NR 4050X, DATED 6/7/1988.  OLEO TUBE ITEN NR 17, FORK ASSY, ITEM NR 5. (K)                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  3A23    E274                 
             20081003         2008       10         3          2008FA0000612    220080903G7414                BEARING                                 CESSNA182   182T        2072703CE                                                               MAGNETO         BURNED          B  L9ORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP1953610503        02111750    18281223                                REMOVED MAGNETO TO S/B3-08 AND MFG 500 HOUR INSPECTION. REMOVED HARNESS CAP FOUND A LIGHT SMOKE COLORED FILM COVERING CAP AND DISTRIBUTOR BLOCK. REMOVED MAGNETO FROM ENGINE FOUND BEARING BAR BURNED THROUGH ON LEFT SIDE WHEN VIEWED FROM DRIVE END. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O    NT3A13                         
             20081007     GL  2008       10         7          2008FA0000613    320080903G6111C13019S         CLAMP                                   BEECH 90    F90         1152909CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4T HCB4TN3     GL  BLADE           FAILED          B  ZY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP2390BD 5569                   LA134                   EAA1457         PROPELLER UNIT WAS OVERHAULED ON JULY 28, 2008, WO 79785. THE PROPELLER WAS INSTALLED ON ACFT AUG 27, 2008. UPON RUN UP OF ACFT, THE MECHANIC NOTED A GREASE LEAK FROM THE PROPELLER BLADE. A CRACK WAS FOUND. O/H FACILITY WAS NOTIFIED OF THE FINDINGS. THE PROPELLER WAS REMOVED FROM THE ACFT AND RETURNED TO THE FACILITY FOR INSPECTION .  O/H FACILITY VERIFIED THE SAME FINDINGS. BLADE CLAMP WAS REMOVED AND REPLACED WITH AN OHC CLAMP ASSY. ALL WORK WAS PERFORMED IAW SRM 118F, 202A, AND 133C. (K)                                                                                                                                                                                                                                 1L72 4T4  T  A31CE   E4EA    6  CP40EA    
             20081007     GL  2008       10         7          2008FA0000614    320080909G6110B3476A2         ROD                                     DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  PROPELLER       BROKEN          B  LU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19V2LFC           BUA26256                            BUA26256        BETA ROD CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081007     GL  2008       10         7          2008FA0000615    320080909G6110B30012          RING            HARTZL                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  PROPELLER       BROKEN          B  LU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19V2LFC29388      BUA26256                                            BETA RING CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081007         2008       10         7          2008FA0000616    420080815G2562DCELL           BATTERY                                 PIPER PA28  PA28161     7102803SO                                                               ELT             LEAKING         B  KABRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      GL1344FT 297        043551      287716219                               BATTERYS LEAK ACID ON TO SPRINGS AND CORRODED THEM. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O      2A13                         
             20081007     CE  2008       10         7          2008FA0000617    120080822G2121903840311       BLOWER                                  BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCD4N3HCD4N3A     GL  VENT            FAILED          B  BNGRA   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      GL19904RB     764               LJ1088      PCE25175    FY2838          PILOT DETECTED SMOKE IN CABIN, LANDED.  TROUBLESHOT ODOR,  CHECK IN ENGINE BAYS, NO DEFECT NOTED. FOUND CABIN VENT BLOWER NOT WORKING, CHECKED BLOWER SYSTEM WIRING, NO DEFECTS NOTED, CHECKED VENT BLOWER UNDER PILOT FLOOR AND FOUND BLOWER MOTOR LOCKED UP. REMOVED ASSY FOUND MOTOR HAD BURNED, ELEC ODOR. REMOVED AND REPLACED VENT BLOWER WITH OVERHAULED UNIT. OPERATION CHECKED NORMAL. THIS MOTOR RUNS ON LOW SPEED ANYTIME AUTO COOL OR AUTO HEAT SWITCH IS ON OR WITH BLOWER SWITCH IN LOW OR HIGH AND ENGINES ARE RUNNING. DURING INSPECTION WITH THIS LOCATION OPEN, CHECK BLOWER FOR PROPER OPERATION AND SPEED. (K)                                                                                                              1L72 3T4  TRT3A20    E4EA    5  CSTC      
             20081007     SO  2008       10         7          2008FA0000618    120080819G28103848808         TANK                                    PIPER PA32  PA32R301    7103218SO  LYC   O540  IO540*      41532EA                              FUEL            LEAKING         B  SVTRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      GL0353646607                    3246214                                 THE ACFT OPERATOR DROPPED THE ACFT OFF WITH A COMPLAINT OF A FUEL LEAK IN THE LT WING. THERE WAS EXTERNAL STAINING AT THE IB AFT EDGE OF THE TANK ASSY WHERE IT ATTACHES TO THE WING SKIN. THE TANK WAS REMOVED FROM THE AIRCRAFT TO LOOK FOR THE LEAK. IT APPEARS THAT THE SEALANT HAD DISSOLVED OR WASHED OUT OF THE TANK.  THE TANK WAS SENT FOR INSPECTION AND REPAIR.  THEY VERIFIED THAT THE SEAM WAS LEAKING AND REPAIRED IT. THERE WAS NO VISIBLE PHYSICAL DAMAGE TO THE TANK OR MOUNTING  STRUCTURE. AT THE AGE OF THIS AIRCRAFT, WOULD NOT EXPECT TO SEE A TANK LEAK LIKE THIS UNLESS THE SEALANT WAS IMPROPERLY MIXED AT THE FACTORY OR ASSY OR SOME COMPONENT IN THE FUEL WAS DISSOLVING THE SEALANT. (K)                           1L71 3O3  O  A3SO    1E4                  
             20081007     CE  2008       10         7          2008FA0000619    120080915G2400                CONTACT                                 BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              RELAY           ERODED          B  CRORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA03300TN415                    FA168                                   HAD 3 FAILURES OF THE SAME RELAY, FIRST RELAY LASTED 457 HOURS, SECOND RELAY LASTED 187 HOURS, AND THE THIRD RELAY LASTED 415 HOURS. MOST OF THE TIME THE FAILURE STARTS WITH THE 2 MICRO SWITCHES IN THE COVER GOING BAD. FOR HAVING RELATIVELY LOW TIME, THE MAIN CONTACTS WERE ERODED FAIRLY WELL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  T  A24CE   E4EA                 
             20081007         2008       10         7          2008FA0000620    420080915G2397M3902957357     SOCKET                                  SKRSKYS76   S76B        8143007NE                                                               CONNECTOR       MISINSTALLED    B  AMCRO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      GL09520AC2422                   760380                                  CREW COULD NOT TRANSMIT ON AN FM FREQUENCY THROUGH NR 1 AUDIO CONTROL BOX. MAINT FOUND CONNECTOR PIN SOCKET INSTALLED BACKWARD. THE PART FOR THE WIRE WAS INSTALLED TOWARD THE PIN SIDE, AND THE PIN SIDE HAD THE WIRE CRIMPED INTO IT. THE SOCKET IS SYMMETRICAL. UNIT HAS BEEN LIKE THIS FOR MANY YEARS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                  1G72 4U      H1NE                         
             20081003     NE  2008       10         3          2008FA0000621    220080826G7230307241613       COMPRESSOR WHEEL                        AMD   FALC90FALCON900EX 2730009EU  GARRTTTFE731TFE73160         NE                              ENGINE          SEPARATED       B  ZN3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0758CG                        47          112349                      THE CREW REPORTED VIBRATION AND ITT RISE. POWER WAS PULLED BACK TO IDLE AND THE AC LANDED WITHOUT INCIDENCE. DISASSEMBLY FINDINGS REVEALED THE LPC2 ROTOR ASSY  (PN 307241613). DISC PN 30603731, SN 990316003093, EXHIBITED MATERIAL LOSS IN THE FORM OF A DISC POST SEPARATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L73 4F4  FRTA46EU   E1NM                 
             20081003     CE  2008       10         3          2008FA0000622    120080904G7810265202231       COWLING                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE                              EXHAUST         CRACKED         B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059634B                       208B0141                                THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. IT WAS NOTICED THAT ANOTHER CARAVAN IN THE HANGER FOR INSPECTION HAD THE SAME CRACK (LENGTH AND LOCATION) THAT HAD BEEN PREVIOUSLY REPAIRED BY INSTALLING A DOUBLER PATCH. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3T3  T  A37CE   E4EA                 
             20081003     CE  2008       10         3          2008FA0000623    120080905G5730                SKIN                                    CESSNA310   310Q        2074242CE                                                               LT WING         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW13100EL                       310Q0688                                FOUND CRACK IN UPPER WING SKIN AS DESCRIBED IN SB MEB08-3.  CRACK EXTENDS 4 INCHES FORE AND AFT PARALLEL TO LT WING MAIN LANDING GEAR ASIDE BRACE WING RIB NR 502210451 OB FLANGE. CRACK IS APPROXIMATELY CENTERED IN MLG WHEEL WELL OPENING. CRACK WAS FOUND VISUALLY DURING COMPLIANCE WITH MEB76-2 MAIN LANDING GEAR RIB SIDE BRACE CRACKS, DURING INSTALLATION OF SK414-8E. (K)                                                                                                                                                                                                                                                                                                                                                             1L72 3O      3A10                         
             20081003     SO  2008       10         3          2008FA0000624    220080905G8520                BUSHING                                 CESSNA414   414A        2075907CE  CONT  O520  TSIO520NB   17040SO                              PISTON PIN      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW13414NC                       414A0484                                DURING CYLINDER NR 2 REMOVAL TO CORRECT CRACKED CYLINDER, FOUND CONNECTING ROD PISTON P/N BUSHING CRACKED WITH LARGE PIECE MISSING FROM EDGE.  FAILURE IS AS NOTED IN MFG SB071. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS CRACKED IN SAME LOCATION.  MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB B807. (K)                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A7CE    E8CE                 
             20081007     SO  2008       10         7          2008FA0000625    220080905G8520                BUSHING                                 CESSNA421   421C        2076016CE  CONT  O520  GTSIO520N   17032SO                              PISTON PIN      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW13410AJ                       421C1093    823531R                     DURING CYLINDER NR 5 REMOVAL TO CORRECT HIGH OIL CONSUMPTION , FOUND CONNECTING ROD PISTON PIN BUSHING CRACKED WITH LARGE PIECE MISSING FROM EDGE.  FAILURE IS AS NOTED IN MFG SB SB07-1. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS CRACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB SB071. (K)                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A7CE    E7CE                 
             20081003     CE  2008       10         3          2008FA0000627    120080723G5753710516000015    HINGE BRACKET                           BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              LT WING TE FLAP CORRODED        G  BEJSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO156708A7712                   ME302                                   LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A29CE   E286                 
             20081007     CE  2008       10         7          2008FA0000628    120080722G575310516000015     HINGE BRACKET                           BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              LT WING TE FLAP CORRODED        G  BEJSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO156638D9976                   ME268                                   LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORT RIBS, WHERE HINGE BRACKET PIN FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED INSIDE OF SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A29CE   E286                 
             20081003     CE  2008       10         3          2008FA0000629    120080722G575310516000015     HINGE BRACKET   BEECH                   BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              LT WING TE FLAP CORRODED        G  BEJSK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15110SU11007                  ME81                                    LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A29CE   E286                 
             20081003     CE  2008       10         3          2008FA0000630    120080723G575310516000015     HINGE BRACKET   BEECH                   BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              LT WING TE FLAP CORRODED        G  BEJSK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15278D 16533                  ME23                                    LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A29CE   E286                 
             20081006         2008       10         6          2008FA0000631    420080911G6122210044          ROD             WOODWARD                BEECH 58    58          1152740CE                                                               GOVERNOR        BROKEN          B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO196681L           1098981     TH1088                                  LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O      3A16                         
             20081007         2008       10         7          2008FA0000632    420080911G6122B20429          DRIVE SYSTEM    MCAULY                                                     CONT  O520  IO520*      17032SO                                              BROKEN          B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19CGFLM           790221                                              SPRING-DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E5CE                 
             20081007     SW  2008       10         7          2008FA0000633    120080826G6711206076031107    SERVO                                   BELL  206   206B3       1181506SW                                                               RT CYCLIC       MALFUNCTIONED   C      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      SW996NJ                         4534                                    DURING START, PILOT NOTICED CYCLIC STICK COULD NOT BE MOVED WHEN THE HYD OFF PROTAKE OFF CHECK WAS INITIATED.  WITH HYD POWER ON, FLT CONTROL OP NORM.  THE HELICOPTER RETURNED FROM FLT, THE HYDRAULIC FIELD AND SERVO WERE HOT, IT WAS A VERY HOT DAY, TEMP ABOUT 96 DEGREES.  PILOT NOTICED THE CYCLIC STICK COULD NOT BE MOVED DURING HIS HYD CHECK.  IT WAS SHUT DOWN AND BROUGHT INTO THE HANGAR MX.  A HYD MULE WAS HOOKED UP AND OPS NORMAL.  BELL HELICOPTER TECH REP WAS NOTIFIED AND ASKED TO COME TO THE FACILITY.  THE TECHS DID A GROUND RUN FOR APPROX 15 MIN W/O INCIDENT.  AFTER HOVERING FOR 5 MINUTES, THE PROBLEM RETURNED.  THE PROB APPEARED TO BE THE RT HYD SERVO (S/N 8528).  LT SERVO WAS NEAR OVERHAUL, WE REPLACED I1G71 3U      H2SW                         
             20081007     SO  2008       10         7          2008FA0000635    220080824G8500                ENGINE                                  CESSNA172   172F        2072414CE  CONT  O300  O300D       17022SO                                              POWER LOSS      B  IGBRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP018546U                       17252446    29446D4D                    AC WAS NOT OPERATING UNDER PART 135, IT WAS UNDER PART 91 FLIGHT WHEN INCIDENT OCCURRED. PILOT STATEMENT "ENROUTE, AS WE CRESTED THEMOUNTAINS, THE ENGINE STARTED SPUTTERING, AND RPMS WERE DROPPING. APPLIED CARB HEAT, TRIED SWITCHING BETWEE N FUEL TANKS, MAGNETOS, AND THE RPMS KEPT DROPPING.  WE THEN WENT THROUGH THE FORMAL CHECK LIST TO NO AVAIL. THE DECISION WAS MADE TO LAND AT RADAR FACILITY.  BY THIS TIME THE ENGINE HAD STOPPED. WE MADE THE EMERGENCY LANDING AT THE FACILITY AND CAME TO A FULL STOP. DURING THE DESCENT, TRIED STARTING THE ENGINE MULTIPLE TIME, BUT IT DIDNT START. NO ONE WAS INJURED AND THE PLANE WAS NOT DAMAGED.                                                                                  1H71 3O3  ONT3A12    E253                 
             20081007     CE  2008       10         7          2008FA0000636    120080910G323320410202        PIVOT ASSY                              CESSNA177   177RG       2073709CE                                                               MLG ACTUATOR    SHEARED         B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA077503V4800                   177RG0802                               PILOT COULDNT OBTAIN GEAR DOWN INDICATION AFTER EXTENDING GEAR. JACKED AC AND FOUND MAIN GEAR WOULDNT COMPLETELY ENTER DOWN-AND-LOCKED POSITION. FOUND MAIN GEAR RETRACT ACTUATOR REAR MOUNTING/ PIVOT PIN HAD ONE SIDE COMPLETELY SHEARED. THIS ALLOWED/CAUSED THE TUBULAR MOUNT STRUCTURE TO FLEX FROM SIDE TO SIDE AND CRACK MOST OF THE WAY THROUGH. (K)                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O      A20CE                        
             20081007     SO  2008       10         7          2008FA0000637    120080902G5510510229615       ANGLE                                   AMRGENAA5   AA5B        3960105SO                                                               HORIZONTAL STAB CRACKED         B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA07286654640                   AA5B0739                                MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. FOUND DELAMINATION, CRACKS AND WRINKLES IN HORIZONTAL STAB FWD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. WE BELIEVE THE SINGLE MOST CAUSE TO BE PILOTS AND MAINT PUSHING DOWN ON THE FWD SSPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROUND. (K)                                                                                                                                                                                                                                                                                                                                                                 1L71 3O      A16EA                        
             20081007     SO  2008       10         7          2008FA0000638    120080902G5510510229616       ANGLE                                   AMRGENAA5   AA5B        3960105SO                                                               HORIZONTAL STAB CRACKED         B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA07286654640                   AA5B0739                                MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS.  FOUND DELAMINATION, CRACKS, AND WRINKLES IN HORIZONTAL STAB FORWARD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE.  WE BELIEVE THE SINGLE-MOST CAUSE TO BE PILOTS AND MAINTENANCE PUSHING DOWN ON THE FWD SPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROUND. (K)                                                                                                                                                                                                                                                                                                                                                     1L71 3O      A16EA                        
             20080930     GL  2008       9          30         2008FA0000639    120080902G575313431003        HINGE                                   CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              TE FLAPS        CORRODED        B  ACORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39121HC724                    0277                                    FLAP HINGES IN ALL POSITIONS BOTH LT AND RT HAVE INTERGRANDULAR CORROSION NEAR THE POINT OF FAILURE. PN 13431-003,  PN 13431-004, 13432-002, QTY 2, 13433-006, 13433-005.  CONDITION WAS FOUND AT ANNUAL INSPECTION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTA00009CHE3SO                 
             20081007     SO  2008       10         7          2008FA0000640    220080801G7414M3215           BRUSHES                                 COLUMBLC41  LC41550FG4005150011NM  CONT  O550  TSIO550C         SO                              MAGENTO         WORN            B  BIERO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21623TS243                    41668       914471                      DETECTED NUMEROUS MAGNETOS WITH CARBON BLOCKS AND COILS TABS THAT ARE PREMATURELY WEARING OUT IN MAGNETO PN 6320. HAVE HAD CUSTOMERS WITH MAGNETO FAILURES AS EARLY AS 5.5 HOURS ON THEIR NEW MAGNETOS. EVEN THOUGH MFG HAS IDENTIFIED THIS ISSUE AND PUT OUT GUIDANCE TO INSPECT MAGNETOS WITHIN THE NEXT 50 HOURS OF OPERATION AS OF MAY 2, 2008, THIS ISSUE IS A MAJOR CONCERN TO ALL CUSTOMERS DUE TO THE PERFORMANCE ISSUES THEY HAVE EXPERIENCED WITH THESE MAGNETOS AND THE ADDITIONAL DOWN-TIME OF THE AC DUE TO THE FREQUENT INSP REQUIRED (EVERY 100 HRS). MFG NEEDS TO RESOLVE THEIR PRODUCT DEFICIENCY IMMEDIATELY AND THE ANSWER SHOULDNT BE THE CUSTOMERS BEAR THE COST OF REPLACEMENT OR THE ADDED COST OF FREQUENT INSPECTIONS.1L71 3O3  ONTA00003SEE5SO                 
             20081007     EU  2008       10         7          2008FA0000641    120080917G3230A223801         SWITCH                                  AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE7315BR        WP                              MLG             INOPERATIVE     B  DJSRA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL23531FL     2389              113         P95155C                     LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA7EU    E6WE                 
             20081007     EU  2008       10         7          2008FA0000642    120080919G3230123371          CONTROL SWITCH                          AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE7315BR        WP                              MLG             INOPERATIVE     B  DJSRA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL23531FL     2389              113         P95155C                     LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA7EU    E6WE                 
             20081003     NM  2008       10         3          2008FA0000643    120080918G80116420871A7       ADAPTER                                 COLUMBLC42  LC42550FG3505150012NM  CONT  O550  IO550N      17042SO                              STARTER         FAILED          B  BIERO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      EA21964SG                       42518       689029                      OWNER/OPERATOR COMPLAINS THAT HIS ENGINE USES EXCESSIVE OIL OVER SHORT AND LONG FLIGHTS, SOME TIME AS MUCH AS (2) QUARTS  IN LESS THAN A 2 HOUR FLIGHT.  REPLACED STARTER ADAPTER ASSY WITH NEW PART FROM MFG AND PROBLEM STILL OCCURS WITH OIL BEING PUMPED TO THE OIL SEPERATOR DURING THE GROUND ENGINE RUN. A COPY OF FAA FORM 8130-3 AND SHIPPING DOCUMENTS ARE ATTACHED TO THIS SDR WITH ADDITIONAL INFORMATION. (K)                                                                                                                                                                                                                                                                                                                      1L71 3O3  ONTA00003SEE3SO                 
             20081003     GL  2008       10         3          2008FA0000644    320080918G6111A66315A         CLAMP                                                                                                       HARTZLHCA2  HCA2MVK2    GL  PROPELLER BLADE BROKEN          B  ME4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19C6BH4     1873                                      H138            BLADE CLAMP FOUND TO BE CRACKED DURING MAGNETIC PARTICLE INSPECTION. CRACK IS LOCATED IN REAR HALF EXTENDING FROM THE A-321 OUTER BOLT HOLE TO THE INSIDE OF THE CLAMP. DURING TEARDOWN INSPECTION, A-321 BOLT REMOVED FROM THIS CLAMP WAS BROKEN IN HALF.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              5  CP24EA    
             20081003     GL  2008       10         3          2008FA0000645    320080918G6111A321            BOLT                                                                                                        HARTZLHCA2  HCA2MVK2    GL  BLADE CLAMP     BROKEN          B  ME4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19                                                    H138            A-321 CLAMP BOLT WAS FOUND TO BE BROKEN DURING TEARDOWN INSPECTION. BOLT IS CRACKED IN (2) PIECES APPROXIMATELY .5 THE LENGTH DOWN THE TREADED AREA. CLAMP THAT IT WAS ATTACHED TO WAS LATER FOUND TO BE CRACKED DURING MAG PARTICLE INSPECTION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         5  CP24EA    
             20081008     SW  2008       10         8          2008FA0000646    120080901G6210407015001111    BLADE                                   BELL  407   407         1182206SW                                                               MAIN ROTOR      CRACKED         B  UOHRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13407LG                       53143                                   M/R BLADE HAS 2706.0 HRS TT WHEN CLEANING BLADE FOR REINSTALLATION, MANY SHALLOW CRACKS WERE FOUND ON THE TOP SURFACE OF BLADE 24 INCH IB OF TRIM TAB. THE CRACKS RUN 45 DEGREES TO BLADE SPAN. CONTACTED MFG PRODUCT SUPPORT AND WAS INFORMED THAT THIS CONDITION IS CALLED "TRACER STRANDS" AND IS A CONDITION NEEDING REPAIR. PRODUCT SUPPORT ALSO INFORMED US THAT THIS WOULD BE REFERENCED INT THE MANUALS IN THE NEAR FUTURE AND THAT NEWER BLADES HAVE BEEN CORRECTED FOR THIS PROBLEM. (K)                                                                                                                                                                                                                                              1G71 3U    O H2SW                         
             20081008     EA  2008       10         8          2008FA0000647    120080912G5347SH670RPA0045    SEAT TRACK                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF34*       30015NE                              FS 424-513      CORRODED        B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03636BR                       7307                                    LT FLOOR SEAT TRACK AT FS 424.0-513.0 FOUND TO BE CORRODED BEYOND LIMITS.  REMOVED AND REPLACED SEAT TRACK IAW SRM 51-41-00. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA                        
             20081008     EA  2008       10         8          2008FA0000648    120080912G5347SH670RPA0045    SEAT TRACK                              CNDAIRCL600 CL6002B19   1900309EA                                                               FS 409          CORRODED        B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03636BR                       7307                                    LT FLOOR SEAT TRACK AT FS 409.00+16-409.00+128 FOUND TO BE CORRODED BEYOND LIMITS. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-41-00.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA21EA                        
             20081008     EA  2008       10         8          2008FA0000649    220080922G74147710398         MAGNETO                                 CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA                              LEFT            SEIZED          D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      SO13712TT     643               17275235    L1173239A                   DURING FLIGHT, A SHUDDER AND SLIGHT LOSS OF POWER WAS REPORTED BY THE PILOT. PRIOR TO THE NEXT FLT DURING THE MAGNETO CHECK IT WAS DISCOVERED THAT THE LT MAGNETO WAS INOPERATIVE. FURTHER INVESTIGATION FOUND THE LT MAGNETO CONDENSER WAS OUT OF THE MAGNETO CASE AND THE MOUNT FLANGE WAS BROKEN. THE MAGNETO HAD SEIZED, CAUSING THE CASE TO BREAK FREE OF THE ENGINE. THE INTERNAL PARTS MELTED AND DESTROYED.  INSP OF THE INSIDE OF THE ENGINE DRIVE GEARS AND CASE DID NOT REVEAL ANY DAMAGE. OIL WAS DRAINED AND INLET SCREEN CHECKED WITH NO METAL FOUND. THE MAGNETO WAS REPLACED. ACCORDING TO THE LOGBOOKS, THE REMOVED MAGNETO HAD BEEN OVERHAULED AND INSTALLED AT ENGINE OVERHAUL ON 6/30/08 WITH NO INDICATION OF FURTHER MAINT1H71 3O3  ONT3A12    E274                 
             20081008     CE  2008       10         8          2008FA0000650    120080905G532045A336065       BRACKET                                 BEECH MU300 400A        1155402CE                                                               FUSELAGE        CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0395GK 8304                   RK27                                    DURING SCHEDULED AIRFRAME INSPECTION FOUND PN 45A33606-5 AND PN 45A33606-6 CABIN UNDER FLOOR REINFORCING BRACKETS AT CABIN DOOR ENTRANCEWAY CRACKED. SEE SRM 53-10-50-001, FIG 1, SHEET 2 OR 3, ITEMS 29 AND 30.  SUSPECT CRACKED FROM FATIGUE, ALSO POSSIBLY FROM PREVIOUS ROUGH CABIN DOOR STEP ASSY HANDLING. AC TECHNICIANS/ INSPECTORS SHOULD INSPECT THIS AREA CAREFULLY DURING SCHEDULED INSPECTIONS ON HIGHER TIME AIRCRAFT, AND/OR AIRCRAFT WITH PREVIOUS HISTORY OPERATED BY CHARTER/AIR TAXI/ FRACTIONAL OPERATORS. (K)                                                                                                                                                                                                              2H72 4F    RTA16SW                        
             20081008     SO  2008       10         8          2008FA0000651    120080828G534367054803        TRUNNION                                PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              NLG             CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA1327GS                        28R7737160                              AIRCRAFT CAME IN FOR HARD STARTING. WHILE REMOVING LOWER COWL, TO ACCESS LOWER SPARK PLUGS, TECH NOTICED THE NOSE LANDING GEAR TRUNNION CRACKED WHERE DRAG BRACE ATTACHES TO IT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A13    1E10                 
             20081008     NE  2008       10         8          2008FA0000652    220080822G8500                ENGINE                                  AIRTRCAT300 AT301       0390103SW  PWA   R1340 R1340*      52016NE                                              STOPPED         D      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               NRNOT REPORTED   1                      SW032391Z                       3010452     12403                       ENGINE QUIT IN MID-AIR. ENGINE HAD 1195.0 HOURS SINCE MAJOR OVERHAUL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3R3  R  A9SW    5E2                  
             20081008     EA  2008       10         8          2008FA0000653    120080816G5347                SEAT TRACK                              CNDAIRCL600 CL6002B19   1900309EA                                                               BS 409-559      CORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03636BR                       7307                                    (3) SEAT TRACK SECTIONS WERE FOUND TO BE CORRODED BEYOND LIMITS DURING AN INSPECTION AT WL 79.50 - FS 409.0+12 TO FS559.0 RT SIDE, WL 72.50 - FS 409.0+12 TO 559.0 RT SIDE, WL 79.50 - FS409.0+12 TO FS559.0 LT SIDE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA21EA                        
             20081008     EA  2008       10         8          2008FA0000654    220080723G8530HIO360F1AD      CYLINDER HEAD                           ENSTRMF28   F28F        3300412GL  LYC   O360  HIO360*     41514EA                              ENGINE          DAMAGED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL138626E                       744                                     DURING CYLINDER OVERHAUL A DAMAGE SEAT POCKET CUTTER USE USED. THIS RESULTED IN A VALVE SEAT POCKET THAT MEASURED WITHIN LIMITS BUT LACKED THE PROPER SURFACE CONTACT. AFTER APPROXIMATELY 3 HOURS OF ENGINE OPERATION, THE VALVE SEAT CAME OUT CAUSING THE INTAKE VALVE TO BREAK. THIS CAUSED A LOSS OF ENGINE POWER AND THE HELICOPTER MADE A HARD LANDING.  HELICOPTER WAS DESTROYED BY FIRE. (K)                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H1CE    1E10                 
             20081006     WP  2008       10         6          2008FA0000655    120080921G7810C1691           MUFFLER                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL033203D200                    11598                                   MUFFLER WAS HEAT BLISTERED AND CRACKED AT TAIL PIPE TRANSITION. COLLECTOR WAS BURNED THRU UNDER CLAMP AT NR 1 CYLINDER, ALSO HEAT BLISTERED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081008     WP  2008       10         8          2008FA0000656    120080921G7820C1691           MUFFLER                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              EXHAUST         BULGED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03510KJ799                    10338                                   MUFFLER FOUND - BULGED - BLISTERED AND HEAT CRACKED AT TAILPIPE TRANSITION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
             20081006     CE  2008       10         6          2008FA0000657    120080919G7810265202231       COWLING                                 CESSNA208   208         2073702CE  PWA   PT6   PT6A114     52043NE                              EXHAUST         CRACKED         B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059653F                       20800114    PCE17260                    THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3T3  TNTA37CE   E4EA                 
             20081008     SO  2008       10         8          2008FA0000658    120080901G57116707002         SPAR                                    PIPER PA28  PA28R200    7102811SO                                                               LT WING         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA13                                                                    LT WING SPAR CRACKED IN THE AREA OF WHERE THE PIVOT BLOCK IS INSTALLED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O      2A13                         
             20081008     CE  2008       10         8          2008FA0000659    120080916G252071500           SEAT                                    BBAVIA8     8KCAB       2110612CE                                                               CABIN           FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL137698S                       26276                                   REAR SEAT PN 7-1500 FAILED AT THE LT HINGE POINT. THE AN3 SERIES BOLT PULLED THRU THE HINGE LUGS WHICH ARE WELDED TO THE SEAT FRAME BOTTOM. THE RT HINGE HOLES SHOW ELONGATION, BUT REMAINED INTACT. THE AC WAS DOING SPIN TRAINING AT THE TIME OF THE INCIDENT. RECOMMEND THAT THE SEAT FRAME BE MODIFIED TO CURRENT STANDARDS INSTALLED ON NEWER AC. (K)                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O      A21CE                        
             20081008     SO  2008       10         8          2008FA0000660    220080917G741410357174        CONTACT                                 BEECH 35    G35         1151516CE  CONT  E225  E2258       17015SO                              RT MAGNETO      FAILED          D      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      NM014998B34         F159517DR   D4516       33951                       RT MAGNETO FAILED COMPLETELY IN FLIGHT DUE TO THE TIP OF THE CONTACT POINTS HAVING SEPARATED FROM HE ASSY.  THIS LEFT THE CONTACTS AND THEREFORE PRIMARY ELECTRICAL CIRCUIT IN A CONTINUALLY OPEN POSITION. RENDERING THE MAGNETO INOPERATIVE.  IN A PHONE CONVERSATION WITH THE MFG REP, MFG IS AWARE OF THE POTENTIAL CONDITION AND HAD ISSUED A DISTRIBUTOR INFORMATION BULLETIN D1B2008-3. RECALLING CONTACT ASSY AT THE DISTRIBUTOR LEVEL MFG WITH DATE CODES OF 0716-0816 OR THE (16) WEEK OF 2007 TO THE (16) WEEK OF 2008.  THE CONTACTS THAT WERE INSTALLED IN THIS MAGNETO IN MAY OF2008 DURING A ROUTINE 500 HR INSP, HAD APPARENTLY MADE THEIR WAY INTO THE RETAIL INVENTORY SYS.  (K)                                              1L71 3O3  O  A777    E267                 
             20081008     GL  2008       10         8          2008FA0000661    120080917G8011                CASTING                                 DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE                              STARTER         BROKEN          B  MZERO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL15273DS           F4L08012    40954       L3417151E                   CUSTOMER ATTEMPTED TO START ENGINE. WHILE CRANKING ENGINE, CUSTOMER REPORTED A LOUD "CLUNK" AND THE PROPELLER STOPPED ROTATING. INVESTIGATED PROBLEM AND FOUND THE STARTER DRIVE CASTING BROKE FROM STARTER MOTOR. THE CASTING INCLUDED A BEARING FOR THE STARTER DRIVE SHAFT. SHAFT AND BENDIX GEAR WAS STILL ATTACHED TO THE STARTER MOTOR. (K)                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ONTA47CE   E1CE                 
             20081008     CE  2008       10         8          2008FA0000662    120080922G2810                SEAL                                    RAYTHN390   390         7150030CE  WILINTFJ44  FJ442A           GL                              FUEL CAP        DISLODGED       W      K   NONE                                                                                            K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      EA35390EU                       RB242                                   PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INSTALLED. FUEL LEAKING FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AIRCRAFT. THE FUEL FLOWING UP THE OUTSIDE OF THE AIRCRAFT HAS BEEN DRAWN INTO THE REAR MAINTENANCE BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPRAYED OVER FLYING CONTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAILCONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITCH TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED.                                                                                                                       1L72 3F4  FRTA00010WIE3GL                 
             20081006     NE  2008       10         6          2008FA0000663    220080826G731450466           PUMP                                    RKWELLNA265 NA26560     7630106CE  PWA   JT12  JT12A8      52042NE                              LT ENGINE FUEL  WORN            C  UVVRA   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CE03XCCAM6367 632               306145      P689751                     AFTER TAKEOFF THE PILOT COULD NOT ADJUST THE LT ENGINE POWER OUTPUT. ENGINE REMAINED AT TAKEOFF POWER WHILE POWER LEVER WAS RETARDED TO IDLE.  PILOT RETURNED TO AIRPORT AND SUCCESSFULLY SHUTDOWN THE LT ENGINE BY PLACING POWER LEVER TO CUT-OFF POSITION AND MADE AN UNEVENTFUL LANDING. FUEL CONTROL, PN 706633, SN 55832 WAS REMOVED FROM THE ENGINE DRIVEN FUEL PUMP AND WAS FOUND THAT THE FUEL CONTROL DRIVE SHAFT REMAINED ENGAGED IN FUEL CONTROL DRIVE SPLINE ON THE FUEL PUMP.  FURTHER INSPECTION OF FUEL CONTROL UNIT REVEALED THAT THE FUEL CONTROL DRIVE SHAFT RETAINER PLATE HAD WORN COMPLETELY THROUGH AND ALLOWED DISENGAGEMENT OF FUEL CONTROL DRIVE SHAFT FROM FUEL CONTROL UNIT. FUEL PUMP, PN 50466, SN 3ACF34 WAS INSPE2L72 4J4  JRTA2WE    1E9                  
             20081015     SO  2008       10         15         2008FA0000665    120081006G2460454668          CIRCUIT BREAKER                         PIPER PA28  PA28161     7102803SO                                                               COCKPIT         FAILED          B      K   NONE                                                                                            HG ELECT. POWER LOSS-50 PC   MULTIPLE FAILURE                                    NRNOT REPORTED   1                      CE058325T6923                   288116134                               FIVE CIRCUIT BREAKERS FAILED INTERMITTENTLY.  THE FAILED CIRCUIT BREAKERS WERE ALL RATED AT 5 AMPS, PIPER P/N 454668, DATE CODE 7903.  THE FIVE CIRCUITS AFFECTED WERE; ENGINE GAUGES, TURN COORDINATOR, INSTRUMENT PANEL LIGHTS, OVERHEAD LIGHTS AND RADIO LIGHTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O      2A13                         
             20081015     CE  2008       10         15         2008FA0000666    120080910G55425533000095      SKIN                                    CESSNA500   560CESSNA   2076750CE                                                               RUDDER          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99905LC7599                   5600334                                 THE LOWER FORWARD RUDDER SKIN IS CRACKED 2.5 INCHES, THIS WAS FOUND DURING ROUTINE PHASE INSPECTIONS.  THE RUDDER SKIN PART NUMBER IS 5533000-95.  THIS IS THE THIRD CRACK FOUND IN THE SAME LOCATION ON THE SAME MODEL AIRPLANE THIS CALENDER YEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA22CE                        
             20081015     CE  2008       10         15         2008FA0000667    120081007G56106656100000009   WINDSHIELD                              LEAR  45    45LEAR      5170805CE                                                               COCKPIT         CRACKED         E      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      GL13241LJ1778                   241                                     AIRCRAFT DEPARTED LAX PASSING THROUGH 18000 FT CREW HEARD A POP AND PILOT'S WINDSHIELD OUTER PLY CRACKED.  CREW DECLARED EMERGENCY AND RETURNED TO LAX.  LANDING WAS UNEVENTFUL.  INSPECTION OF WINDSHIELD BY STANDARD AERO - LAX FOUND OUTER PLY WINDSHIELD HAD FAILED.  STANDARD AERO - LAX CURRENTLY REPLACING WINDSHIELD WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTT00008WI                     
             20081015     NE  2008       10         15         2008FA0000668    220081003G853066713           GUIDE           LYC                     ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          UNDERSIZE       D      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      SW994126A464                    12096       L3247448E                   MOMENTARY SEVERE VIBRATION, POWER LOSS AND ENGINE RPM DROP OCCURRED IN-FLIGHT THEN RETURNED TO NORMAL.  COMPRESSION CHECK (COLD) REVEALED STUCK INTAKE VALVE ON NR 6 CYL.  INTAKE VALVE GUIDE ID MEASURED .4035" (UNDERSIZED).  LIMITS .4040 / .4050.  NO BUILDUP FOUND ON VALVE GUIDE OR STEM.  VALVE GUIDE REAMED TO PROPER SIZE PER LYC.  TABLE OF LIMITS SSP1776.  NO REOCCURRENCE REPORTED.                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081017     CE  2008       10         17         2008FA0000669    120081002G2752232507911       ATTACH BRACKET                          LEAR  35    35A         5170602CE                                                               T/E FLAP        CRACKED         B  AJCAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15308BW9341 600               438                                     DURING 600 HOUR INSPECTION FOUND TWO SHEARED ALUMINUM RIVETS, ALONG WITH A 0NE INCH CRACK IN LT FLAP ACTUATOR ATTACHMENT BRACKET, P/N 2325079-11.  INSTALLED NEW BRACKET ASSEMBLY, P/N 2325079-17.  THIS BRACKET HAS TWO STEEL RIVETS IN PLACE OF THE ORIGINAL ALUM RIVETS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A10CE                        
             20081016     CE  2008       10         16         2008FA0000671    120080924G2797CC75LA61        WIRE HARNESS                            CESSNA208   208B        2073701CE                                                               FLAP SYSTEM     CHAFED          B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059738B11206                  208B0097                                TIE WRAP WAS MISSING FROM THE CLAMP AT FS 201.50, WHICH ALLOWED THE WIRING BUNDLE CONTAINING THE WIRES FOR THE FLAP SYS PRIMARY MOTOR TO SAG AND CHAFE THROUGH WIRE NR CC75 TO THE FLAP SYSTEM AND PARTIALLY THROUGH LA61 TO THE CARGO AREA LIGHTS ON THE BULKHEAD.  THIS CAUSED THE FLAPS TO ONLY RECEIVE POWER TO THE PRIMARY MOTOR IN ONE DIRECTION.  SINCE WIRE LA61 WASN`T CHAFFED COMPLETELY THROUGH THE CARGO AREA LIGHTS WERE STILL WORKING.  (K)                                                                                                                                                                                                                                                                                       1H71 3T      A37CE                        
             20081016     CE  2008       10         16         2008FA0000672    120080926G534065651285        CHANNEL                                 CESSNA500   560CESSNA   2076750CE                                                               CABLE PULLEY    MISLOCATED      B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05809QS                       5600698                                 DURING PHASE 5 INSP, FOUND ELEVATOR TRIM CABLE CONTACTING ELEVATOR SELECTOR DRIVE CHAIN.  FOUND THE TRIM CABLE PULLEY CHANNEL BRACKET MIS-LOCATED.  ORDERED NEW CHANNEL BRACKET AND RELOCATED PULLEY TO CLEAR SECTOR DRIVE CHAIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
             20081015     CE  2008       10         15         2008FA0000673    120080924G5350671261713       FRAME                                   CESSNA750   750         2076810CE                                                               TAIL CONE       CRACKED         B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05960QS                       7500160                                 DURING ROUTINE INSP, FOUND FWD FRAME PN 6712617-13 CRACKED IN (2) LOCATIONS, ON THE TOP LT AND RT SIDES.  ALSO FOUND FRAME AFT OF THIS ONE CRACKED.  PN 6712617-14 ON THE TOP RT SIDE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4J    RTT00007WI                     
             20081015     CE  2008       10         15         2008FA0000674    120080924G5350671261713       FRAME                                   CESSNA750   750         2076810CE                                                               TAIL CONE       CRACKED         E  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05978QS                       7500187                                 DURING ROUTINE INSP FOUND FWD FRAME PN 6712617-13 CRACKED. THE CRACKED FRAME WAS LOCATED IN THE UPPER LT SIDE UNDER THE RUDDER TO STINGER FAIRING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4J    RTT00007WI                     
             20081016     CE  2008       10         16         2008FA0000675    120080908G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   BROKEN          B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05641QS                       5605295                                 DURING ROUTINE INSP, FOUND BROKEN STRANDS ON ELEVATOR TRIM CABLE ASSY PN 666000134.  DAMAGE FOUND WHERE CABLE PASSES THROUGH A SERIES OF "S" PULLEYS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA22CE                        
             20081016     CE  2008       10         16         2008FA0000676    120080908G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               TAIL            BROKEN          B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05627QS                       5605227                                 DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED.  THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIES OF "S" PULLEYS MOUNTED IN THE HORIZ STAB.  SHOULD MAKE THIS A TIME CHANGE ITEM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA22CE                        
             20081016         2008       10         16         2008FA0000677    420080930G2562AK451           ELT                                     PIPER PA34  PA34200T    7103406SO                                                               CABIN           FAILED          B  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA212190K                       347970096                               ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY CODE OR 15 DIGIT HEX ID CODE.  THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS DISTRIBUTED BY PN 453-1000 AND PN 453-0131 (MEASURE MODEL MEZ 1000 AND PSION ORGANIZER II MODEL LZ64) AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY.  INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGIT HEX ID CODE OF 26273300A5FF7FE RATHER THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E285980E4FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY.  UNIT WAS REPLACE1L72 3O      A7SO                         
             20081015         2008       10         15         2008FA0000678    420080930G2562AK451           ELT                                     PIPER PA34  PA34200T    7103406SO                                                               CABIN           NO TEST         B  BIERK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      EA212190K                       347970096                               ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY CODE OR 15 DIGIT HEX ID CODE.  THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS.  DISTRIBUTED, PN 453-1000 AND 453-0131 AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY.  INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGITS HEX ID CODE OF 26273300A5FF7FE RATHER THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E28598052FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY. UNIT WAS REPLACED BY ANOTHER ELT.  THE INCONSISTENT RESULTS WERE THE SAME.  (K1L72 3O      A7SO                         
             20081016     NM  2008       10         16         2008FA0000679    120080829G291025W711008293    LINE                                    ISRAEL1125  1125               NM                                                               HYD RESERVOIR   CHAFED          B  JGVRO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CE09111EL                       055                                     TROUBLESHOT HYDRAULIC SYS AND FOUND THE AUXILIARY HYDRAULIC SYS RETURN LINE THAT CONNECTS THE RETURN HYDRAULIC FILTER TOT THE AUXILIARY HYDRAULIC TANK CHAFED, WHICH CAUSED A SLOW LEAK IN THE HYDRA SYS.  ACCOMPLISHMENT OF SB 1125-29-254 "HYDRAULIC TUBE CLEARANCE" PROVIDES INSTRUCTIONS FOR A ONE TIME INSP OF THE CLEARANCE BETWEEN THE PRESSURE TUBE AND THE RETURN TUBE IN THE AREA OF THE HYDR AUXILIARY RESERVOIR. PROCEDURES ARE GIVEN TO ADJUST  OR REPLACE THE AFFECTED TUBE ASSEMBLIES DEPENDENT UPON THE INSPECTION FINDINGS.  ACFT WAS REPAIRED BY REPLACEMENT OF AUXILIARY HYDRA RETURN TUBE PN 25W711008-293 AND ENSURING CLEARANCES WERE MET IAW THE ACCOMPLISHMENT INSTRUCTIONS OF SB 1125-29-254.  (K)                     2L72 4F    RTA16NM                        
             20081016     GL  2008       10         16         2008FA0000680    320080929G6110A3204           SCREW                                   PIPER PA32  PA32300     7103212SO                                   HARTZLHCC2Y HCC2YK1     GL  PROP BLADE      WORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM11     200                                            CH43680B        CUSTOMER COMPLAINED OF AN EXCESSIVELY LOOSE BLADE PRELOAD ON (1) BLADE 4 MONTHS AFTER OVERHAUL. INSP REVEALED EXCESSIVE WEAR ON END OF BLADE PRELOAD SCREWS CAUSING LOOSENESS OF BLADE. OPPOSITE SCREW WAS WORN ALSO BUT NOT TO EXTENT TO BE NOTICEABLE. SECOND OCCURRENCE OF THIS TYPE NOTICED.  INSPECTION OF NEW SCREWS IN STOCK REVEALED IRREGULAR END, IE NOT FLAT BUT ANGULAR.  REPLACED BOTH SCREWS AND RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                        1L71 3O      A3SO            5  CP920     
             20081028     SO  2008       10         28         2008FA0000681    220081014G8530AEC631397       CYLINDER                                BEECH 36    A36         1151604CE  CONT  O550  IO550*           SO                              NR 1            CRACKED         D      C   ABORTED TAKEOFF                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      SW996036 355                    E1422       296794R                     AIRCRAFT OWNER REPORTED SEVERE VIBRATION. AFTER INSPECTION IT WAS FOUND THAT SPINNER BULKHEAD WAS SEVERELY CRACKED. AFTER FURTHER INSPECTION NR 1 CYLINDER WAS FOUND TO BE CRACKED ALL AROUND THE CIRCUMFERENCE OF THE CYLINDER DIAMETER.  THE CRACK WAS RIGHT AT THE 9TH AND 10TH COOLING FINS.  THIS CYLINDER HAD A TOTAL TIME OF 355 HOURS SINCE NEW.  THIS CYLINDER, DUE TO IT'S IDENTIFICATION MARKINGS DID NOT APPLY TO AD 2004-8-10, HOWEVER IT DID APPLY TO ECI'S MSB 06-2 WHICH IDENTIFIES THIS CYLINDER FOR INSPECTION FOR CRACKS.  THE AD 2004-8-10 SHOULD PROBABLY INCLUDE ALL CYLINDERS IN ECI'S MSB 06-2.  THE CONDITION WAS REPORTED IMMEDIATELY AFTER TAKEOFF AND THE PILOT RETURNED IMMEDIATELY TO THE AIRPORT AND LANDED UNEVE1L71 3O3  O  3A15    E3SO                 
             20081016     CE  2008       10         16         2008FA0000682    120080621G272005701051        CONTROL CABLE                           CESSNA170   170A        2072304CE                                                               RUDDER          BROKEN          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL219739A6459                   19200                                   CABLE BROKE AFT OF REAR PULLEY AND BULKHEAD. NO INSPECTION HOLES IN THIS AREA.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O      A799                         
             20081020     EU  2008       10         20         2008FA0000683    120080919G3210                LANDING GEAR                            AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE7315BR        WP                                              FAILED          B  DJSRA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL23531FL                       113         P95155C                     LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA7EU    E6WE                 
             20081020     EU  2008       10         20         2008FA0000684    120080917G3260A223801         POSITION SWITCH                         AMD   FALC20FALCON20C5  2730107EU                                                               MLG             INOPERATIVE     B  DJSRA   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      GL23531FL                       113                                     LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA7EU                         
             20081020     CE  2008       10         20         2008FA0000685    120080926G2697                WIRE                                    LEAR  45    45LEAR      5170805CE                                                               FIRE DETECTION  CHAFED          B  HMGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW1545NM 1158                   253                                     APU FIRE DETECT CIRCUIT BREAKER POPPED ON RT COCKPIT CIRCUIT BREAKER PANEL DURING POWER UP OF AIRCRAFT.  TROUBLESHOT SYSTEM FOUND WIRING CHAFED AT FUSELAGE STATION 614.210 AFT EQUIPMENT BAY UPPER AVIONICS SHELF SUPPORT ANGLE PN 4525708307. THE ANGLE DOES NOT HAVE ANY PROTECTION TO PREVENT CHAFING OF WIRING FROM THE FACTORY AND IT APPEARS THAT CLEARANCE IS NOT GREAT ENOUGH TO KEEP THE WIRING FROM CHAFING.  HAVE NOTIFIED MFG TECH SUPPORT. (K)                                                                                                                                                                                                                                                                                    2L72 4F    RTT00008WI                     
             20081020     CE  2008       10         20         2008FA0000686    120080929G29106317003136      LINE                                    CESSNA525   525         2076601CE                                                               HYD SYSTEM      RUPTURED        B  EWCRO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      EA3944CK 2416                   5250401                                 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LT MARKING BOTH ABOVE AND BELOW OPENING.  AFTER TAKEOFF, LOW FLUID AND PRESSURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO AIRPORT. ACFT WAS TURNED OVER TO SERVICE CENTER.  LEAK WAS LOCATED AND THE LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4F    RTA1WI                         
             20081020     EA  2008       10         20         2008FA0000688    220081001G7314154739704       PUMP                                    CESSNA182   182S        2072701CE  LYC   O540  IO540AB1A5       EA                              FUEL SYSTEM     CRACKED         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      FS6066419                       18280132    L2616748A                   PUMP HOUSING CRACKED ALONG SEAM.  POSSIBLE WEAK SPOT UPON MANUFACTURING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A13    1E4                  
             20081028     CE  2008       10         28         2008FA0000689    120081003G27316660161156660161PUSHROD                                 CESSNA560   560XL       2076702CE                                                               ELEVATOR TAB    WORN            C      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              CRCRUISE         1                      NM07669TT694                    5605684                                 ON RETURN FLIGHT TO HOME STATION, CREW COMPLAINED OF SLIGHT VIBRATION IN FLIGHT.  CREW FELT THE VIBRATION WAS ISOLATED TO THE ELEVATOR CONTROL SYSTEM.  UPON PRELIMINARY INSPECTION OF THE ELEVATOR SYSTEM, FOUND BOTH ELEVATOR TRIM TABS PLAYS BEYOND THE TOLERANCE DEFINED IN 560XL AMM TASK 27-31-00 220.  REMOVED AND REPLACED PUSH RODS (P/N 6660161-15 AND 6660161-17) ON BOTH ELEVATOR TRIM TABS IAW 560XL AMM 27-32-03 PARAGRAPH 4D(3)(A).  AIRCRAFT RETURNED TO SERVICE.  SUBSEQUENT FLIGHT REVEALED NO FURTHER ISSUE.                                                                                                                                                                                                                 2L72 4F    RTA22CE                        
             20081028     SO  2008       10         28         2008FA0000690    220081017G8530AEC631397       CYLINDER                                CESSNA414   414A        2075907CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF32C3AF32C505   GL  ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05414AN654                    414A0819    813675R                     UPON INSPECTION FOUND THAT NR 1 AND NR 5 CYLINDERS WERE CRACKED AND LEAKING FUEL ORIGINATING JUST INBOARD OF THE FUEL NOZZLE BETWEEN THE 16TH AND 18TH COOLING FINS.  CYLINDERS WERE NEW WHEN INSTALLED AT ENGINE OVERHAUL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20081023         2008       10         23         2008FA0000693    420080911G6122210044          ROD                                     BEECH 58    58          1152740CE  CONT  O520  IO520C      17032SO                              GOVERNOR        BROKEN          B  LU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO196681L                       TH1088                                  LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  3A16    E5CE                 
             20081023         2008       10         23         2008FA0000694    420080911G6122B20429          SPRING DRIVE    MCAULY                                                     CONT  O520  IO520*      17032SO                              GOVERNOR        BROKEN          B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19CGFLM           790221                                              SPRING DRIVE DISCOVERED BROKEN AT DISASSEMBLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    3  O          E5CE                 
             20081023     EA  2008       10         23         2008FA0000695    120080909G6120B3476A2         ROD             HARTZL                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  BETA SYSTEM     BROKEN          B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19V2LFC           BUA26256                                            BETA ROD CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081023     EA  2008       10         23         2008FA0000696    120080909G6120B30012          BETA RING                               DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  PROPELLER       BROKEN          B  LU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19V2LFC                                               BUA26256        BETA RING CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MALFUNCTION FOUND 3 HOURS FLIGHT TIME  AFTER LOCAL REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081023     SO  2008       10         23         2008FA0000697    220080930G7414                SPRING                                  CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO                              IMPULSE COUPLINGBROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL21622CP4          D08BA175    1932        360623                      DURING MAGNETO CHECK ON GROUND RUN-UP 30 SEPT 2008, THE PILOT REPORTED THAT WHEN THE LT MAG WAS SELECTED THE ENGINE WOULD NOT STAY RUNNING. ACFT WAS BROUGHT IN FOR MAINT AND IT WAS DISCOVERED THAT THE MAGNETO IMPULSE COUPLING SPRING WAS BROKEN IN THE LEFT MAGNETO. THE LT MAGNETO WAS REMOVED AND REPLACED, GROUND RUN CHECK WAS GOOD, AND ACFT WAS RETURNED TO SERVICE. (K)                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  ONTA00009CHE1CE                 
             20081030     NM  2008       10         30         2008FA0000698    120081019G3510                VALVE                                   BOEING767   7673CB      1385187NM                                                               OXYGEN BOTTLE   OUT OF ADJUST   B      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM01592HA                       33468                                   AIR NEW ZEALAND FAA REPAIR STATION ANZY 188C  AKL - FLT NZ707 - DURING PRE-FLIGHT, TECH CREW NOTED THAT CREW OXY PRESSURE ON EICAS DROPPED FROM 1600 PSI TO APPROX 300 PSI WHILE DEPRESSING THE TEST BUTTONS ON THE CREW OXY MODULES.  ENGINEER CALLED ON HEADSET TO INVESTIGATE.  ENGINEER CHECKED CREW BOTTLE AND FOUND THAT THE VALVE WAS APPROX ONLY 1/3 OPEN AND NOT SAFETY WIRED.  BOTTLE VALVE SUBSEQUENTLY FULLY OPENED AND COPPER WIRED IN POSITION AS REQUIRED.  CREW OXYGEN CHECKS NOW NORMAL WITH NO NOTICEABLE DROP IN PRESSURE ON EICAS.  AIR NEW ZEALAND MAINTENANCE QUALITY RISK AND SAFETY (MQRS) SAFETY INVESTIGATION GROUP HAS RAISED THE FOLLOWING AIR NEW ZEALAND INVESTIGATION (08/SI/135).                               2L72 4F    RTA1NM                         
             20081027     CE  2008       10         27         2008FA0000699    120081010G531350440012319     STRINGER                                BEECH 90    C90         1152913CE  PWA   PT6   PT6*        52043EA                              FS 298          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE01902XP5781                   LJ1136                                  REAR PRESSURE BULKHEAD, FS 298.00, ON RT SIDE. STRINGER NR 9 WAS FOUND CRACKED ON THE AFT SIDE OF THE REAR PRESSURE BULKHEAD AT THE POINT WHERE THE ZEE STIFFENER IS ATTACHED TO THE STRINGER WITH (6) RIVETS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3T3  T  3A20    E2NE                 
             20081027     NE  2008       10         27         2008FA0000700    320080718G61116607132886      BLADE                                                                                                       ROTOL R389  R3894123F25 NE  PROPELLER       CRACKED         B  MS1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA27     37586                                          DR6176385       PROP RECEIVED FOR ROUTINE O/H.  AFTER PROP WAS DISASSEMBLED IT WAS NOTED THAT BLADE NR 2, SN 1141 HAD A CRACKED ROOT END OUTER SLEEVE. BLADE IS REJECTED FROM FURTHER SERVICE. SB SF 340.60.A106 ADDRESSES THIS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         6  CP30NE    
             20081027         2008       10         27         2008FA0000701    420081006G22104006719910      SERVO                                   MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE331*     01514WP                              YAW DAMPENER    CONTAMINATED    D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07544CB     46                1536SA                                  8/11/08 INSTALLED YAW DAMPENER.  10/06/08 - CUSTOMER COMPLAINT OF INDUCED YAW WHEN ENGAGING AUTO PILOT. REMOVED YAW DAMPENER AND FOUND UNIT CONTAMINATED WITH WATER. UNIT IS MOUNTED WITH DRIVE SHAFT UP AND WITH NO DRAIN, THIS PROVIDES FOR WATER TO BE TRAPPED IN THE SERVO.  RECOMMEND SEALING THE UNIT BETTER OR PROVIDING DRAINS FOR UNIT.  (K)                                                                                                                                                                                                                                                                                                                                                                                           1H72 3T3  TRTA10SW   E2WE                 
             20081027     SO  2008       10         27         2008FA0000702    120081016G32106569100         TORQUE LINK                             PIPER J3    J3C65       7100510SO                                                               MLG             CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA23701275440                   17106                                   CRACK FOUND DURING 100 HR INSPECTION.  LAST INSPECTION FOR AD 72-08-06. DONE AT 5214.07 HR, PRESENT TIME 5440.53 (225.76 HR).  SUGGEST PART BE LIFE LIMITED.  THIS IS 2ND SET CRACK. THIS FLEET WITH OVER 5000 HR. TIME IN SERVICE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O      A691                         
             20081027     CE  2008       10         27         2008FA0000703    120081002G2730NAS428420       BOLT                                    BEECH 200   200BEECH    1152920CE                                                               ELEVATOR CONTROLOUT OF ADJUST   B  ML2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11124EK                       BB1993                                  DURING A PHASE 1-4 INSPECTION ON AC. BOLT FOR ELEVATOR CONTROL SYS. WAS FOUND TO BE ADJUSTED ALL THE WAY DOWN AND WAS NOT PROVIDING A STOP FOR THE  BALLAST. IN THIS CONDITION, THE POSSIBILITY EXISTS FOR THE INTERCONNECT LINK BETWEEN THE BALLAST WEIGHT BELLCRANK AND THE CONTROL COLUMN BRACKET TO TRAVEL PAST AN OVERCENTER CONFIGURATION AND MAY PREVENT PROPER CONTROL OF THE ELEVATOR SYSTEM IF THE ELEVATOR PRIMARY OR SECONDARY STOPS FAIL OR ARE ADJUSTED INCORRECTLY.  THE PHASE INSPECTION BEING CONDUCTED IS THE INITIAL INSPECTION ON THE AC, AND LOG RESEARCH DID NOT REVEAL ANY PRIOR MAINTENANCE ON THE ELEVATOR CONTROL SYSTEM RIGGING.  (K)                                                                                1L72 4T      A24CE                        
             20081030     NM  2008       10         30         2008FA0000704    120081024G57119252502         SPAR CAP                                LKHEEDP3A   P3A         5260103NM                                                               RT WING         FRACTURED       B      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP00921AU168421465              151385                                  DURING INSPECTION TO DETERMINE THE SOURCE OF A FUEL LEAK A FRACTURE WAS FOUND IN THE LOWER FORWARD RIGHT SPAR CAP AT WING STA 75 EMANATING FROM NUT PLATE FASTENER HOLE ON FORWARD FLANGE TO THE EDGE OF FLANGE MEMBER WITH SLIGHT ENCROACHMENT AFT FROM SAME HOLE, APPROX .125 INCH.  SECOND FRACTURE SHOWS AT WS 72.2 FROM FORWARD FLANGE NUT PLATE HOLE INTO THE VERTICAL FLANGE SEVERING THE FLANGE.  A THIRD FRACTURE WAS APPRECIATED AT WS 71R IN THE SPAR WEB.  THE CRACK APPEARS TO START AT A HI-LOK PIN HOLE AT THE LOWER CAP AND PROPAGATES APPROXIMATELY THREE INCHES VERTICAL WITH SOME INBOARD TRACK.                                                                                                                             2L74 4T    RTA32NM                        
             20081027     CE  2008       10         27         2008FA0000705    120080929G29106317003136      LINE                                    CESSNA525   525         2076601CE                                                               HYDRAULIC SYS   RUPTURED        B  EWCRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA3944CK                        5250401                                 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LEFT MARKING, BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRESSURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO DEPARTURE. ACFT WAS TURNED OVER TO REPAIR STATION.  LEAK WAS LOCATED AND LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4F    RTA1WI                         
             20081027     SO  2008       10         27         2008FA0000706    120081014G324616109302        WHEEL                                   PIPER PA32  PA32R300    7103213SO                                                               MLG             CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW151228H                       32R7780146                              WHEEL FOUND CRACKED, INNER HALF APPROX 2 INCH LONG.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O      A3SO                         
             20081031     SO  2008       10         31         2008FA0000707    120081026G57129560401         SPAR CAP                                PIPER PA34  PA34200     7103405SO                                                               RT WING         CORRODED        D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO05142584695                   347350180                               DURING ANNUAL INSPECTION, SEVERE INNER GRANULAR CORROSION WAS FOUND IN THE RIGHT WING, MAIN UPPER SPAR CAP AT THE AFT PORTION OF THE T-CAP, IN THE VICINITY OF THE WHEEL WELL IN PARTICULAR THE LOCATION OF WHEEL SPIN OFF.  DURING TIME, CAUSED DAMAGE TO THE POINT OF SPAR REPLACEMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      A7SO                         
             20081028     CE  2008       10         28         2008FA0000708    120080924G3010                LINE                                    CESSNA208   208B        2073701CE                                                               DE-ICE SYSTEM   FROZEN          D      K   NONE                                                                                            NL FALSE WARNING             NO TEST                                             ININSP/MAINT     1                      SO03                                                                    DURING MX OPERATION OF DE-ICE BOOTS MINUTES AFTER ACFT RETURNED FROM FLT, OPERATION OF THE DEICE BOOTS PRODUCED NORMAL COCKPIT INDICATION (GREEN PRESSURE LIGHT). NOTICED, THOUGH, THAT THE RT WING DEICE BOOTS DID NOT INFLATE DESPITE THE INFLATION INDICATION IN THE COCKPIT. FROZEN WATER WAS FOUND AT A BEND IN THE DEICE AIR SUPPLY DUCTING IN THE RT WING ROOT. THIS ALLOWED PRESSURE TO BUILD UP AND ACTIVATE THE PRESSURE SWITCH, PRODUCING A NORMAL INDICATION IN THE COCKPIT DESPITE THE BOOTS NOT ACTUALLY INFLATING. IF THIS WERE TO OCCUR IN THE TAIL, IT WOULD BE EVEN MORE UNDETECTABLE. RECOMMEND A CALIBRATED LEAK IN PNEUMATIC SUPPLY DUCTING IN THE FUSELAGE/ WING TO PREVENT THE ACCUMULATION OF WATER. (K)                1H71 3T      A37CE                        
             20081028     SO  2008       10         28         2008FA0000709    120081014G324616109302        WHEEL                                   PIPER PA32  PA32R300    7103213SO  LYC   O540  TIO540*     41532EA                              MLG             CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW151228H                       32R7780146                              CLEVELAND WHEEL, HOLE FOUND CRACKED, INNER HALF APPROX 2 INCHES LONG. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  A3SO    E14EA                
             20081104     CE  2008       11         4          2008FA0000710    120081027G6120                TUBE                                    BEECH 95    95B55       1152729CE                                                               NACELLE         CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03527T 4985                   TC576                                   ALUMINUM TUBING TO PROP GOVERNOR FOUND CHAFED DUE TO TIE RAP RUBBING TUBE.  FABRICATED NEW TUBE, INSTALLED AND LEAK CHECKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O    RT3A16                         
             20081104     GL  2008       11         4          2008FA0000721    220081027G7260KHU17D31        RELAY                                   CESSNA206   U206G       2073356CE  ALLSN 250C  250C20      03013GL  HARTZLHCC3Y HCC3YN      GL  ENGINE BAY      INTERMITTENT    B      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      GL19891LL4565                   U20606937   CAE290031   GC91A           THE PILOT REPORTED THAT AFTER TURNING ON TO THE RUNWAY FOR TAKEOFF AND APPLYING POWER THE ENGINE CHIP LIGHT CAME ON AND STAYED ON.  POWER WAS REDUCED, AND TOWER APPROVED A RETURN BACK TO THE RAMP.  THE AIRCRAFT NEVER APPROACED TAKEOFF SPEED.  THE AIRCRAFT WAS BROUGHT IN AND INSPECTED, UPON APPLYING ELEC POWER TO AIRCRAFT THE CHIP LIGHT WAS NO LONGER ON.  ALL THREE CHIP LIGHTS WERE INSPECTED AND FOUND NO DISCREPANCIES.  SUSPECTED WIRING PROBLEM OR RELAY PROBLEM.  REPLACED RELAY FOR THE CHIP DETECTORS.                                                                                                                                                                                                                       1H71 3O3  U  A4CE    E4CE    5  CP25EA    
             20081104     EA  2008       11         4          2008FA0000722    220081029G7322105217          CARBURETOR                              CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          DAMAGED         D      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      NM031401E247  247               17270986    L291176T    WA44044         PILOT WAS MAKING 3RD TOUCH AND GO, ON CLIMBOUT ENGINE STARTED VIBRATING EXCESSIVELY, POWER WAS REDUCED AT PATTERN ALTITUDE, MIXTURE ADJUSTED, SWITCHED MAGNETO'S FROM R TO L WITH NO CHANGE IN THE VIBRATION.  AIRCRAFT LANDED AND SUBSEQUENT OPERATION WHILE TAXIING TO PARKING NO VIBRATION WAS ENCOUNTERED.  A RUN UP WAS ACCOMPLISHED AND AT ENGINE OPERATION ABOVE 1800 RPM THE VIBRATION REOCCURRED.  MAINTENANCE DISCOVERED THE PROBLEM TO BE THE CARBURETOR ACCELERATION DISCHARGE TUBE WAS MISSING AND HAD BEEN INGESTED BY THE ENGINE. THE ENGINE AND CARBURETOR HAD 246.9 HOURS SINCE OVERHAUL BY TEXTRON LYCOMING.                                                                                                                  1H71 3O3  ONT3A12    E274    5  NP910     
             20081104     NM  2008       11         4          2008FA0000723    120081029G57119252511         SPAR CAP                                LKHEEDP3A   P3A         5260103NM                                                               RT WING         CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99921A 168421465              151385                                  DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A SECOND CRACK WAS FOUND ON THE FORWARD LOWER CAP AT BUTTLINE 56R.  THE CRACK WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY-CURRENT SURFACE SCAN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L74 4T    RTA32NM                        
             20081104     NM  2008       11         4          2008FA0000724    120081029G57119252502         SPAR CAP                                LKHEEDP3A   P3A         5260103NM                                                               RT WING         CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99921A 168421465              151385                                  DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A TERTIARY FRACTURE WAS FOUND ON THE FORWARD SPAR CAP, HORIZONTAL FLANGE, WING STA 143.5.  THE FRACTURE WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY CURRENT.  AN INTERNAL VISUAL EXAMINATION IDENTIFIED THE AFT HORIZONTAL FLANGE AND VERTICAL FLANGE HAD ALSO BEEN FRACTURED.  THE AFT FLANGE IS FRACTURED APPROXIMATELY .750 INCHES, PROPAGATING AFT TOWARD THE FLANGE END.  THE VERTICAL FLANGE FRACTURE PROPAGATED THROUGH THE FILLET RADIUS UP TO THE FIRST HORIZONTAL ROW OF HI-LOK PINS.  THE FRACTURE LENGTH IS APPROXIMATELY ONE INCH.  FRACTURES WERE CONFIRMED WITH EDDY-CURRENT SURFACE SCAN.                                                                    2L74 4T    RTA32NM                        
             20081104     SO  2008       11         4          2008FA0000725    120081029G57536232800162328000RIB                                     PIPER PA28  PA28180     7102808SO                                                               TE FLAP         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                                                                    DURING ANNUAL INSPECTION FOUND ALL FLAPS, LEADING EDGE RIBS WERE SEVERELY CORRODED.  DETECTION METHOD WAS TO TAKE THE FOREFINGER AND THUMB AND SQUEEZE LEADING EDGE AT THE RIB, GOT A CRUNCHING FEEL AND SOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O      2A13                         
             20081104     CE  2008       11         4          2008FA0000726    120081016G212066151007        TUBE                                    CESSNA560   560XL       2076702CE                                                               AC BAY          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA27     2331                   5333                                    ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO JUST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING.  CESSNA P/N 6615100-7                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA22CE                        
             20081104         2008       11         4          2008FA0000727    420081029G2210                AUTOPILOT SYS                           ECLIPSEA500 ECLIPSEEA5003350000SW                                                               COCKPIT         UNKNOWN         C      A   UNSCHED LANDING                                                                                 G  MULTIPLE FAILURE                                                              CRCRUISE         1                      SW99678P                        191                                     FLIGHT FROM SDL TO TUL, DIVERT TO ABQ.  AUTOPILOT DISENGAGED VIOLENTLY AT 410 AND YD OFF.  REFER TO QRH RESET CB.  AUTOPILOT BACK ON AT 390. 40 SECONDS LATER, AUTOPILOT AND YD DISENGAGED.  UNABLE TO RESET CB.  FL 370 AUTOPILOT BACK ON AND 30 SECONDS LATER DISENGAGED AGAIN.  REMAINED OFF THE REST OF THE FLIGHT.  YD RECOVERED AT 280.  AIRSPEED DISAGREE AT 370.  REFERRED TO QRH.  ADC SOURCE USED AND STILL GIVING AIRSPEED DISAGREE.  DISAPPEARED AT FL250 AND 265 KNOTS.  PILOT ELECTED TO DIVERT TO ABQ.  AIRCRAFT IS BEING WORKED ON AT FACTORY SERVICE CENTER.  UNKNOWN CAUSE AT THIS TIME.                                                                                                                                      1L72 4J    RTA00002AC                     
             20081031     EU  2008       10         31         2008FA0000729    120080930G2120                UNKNOWN                                 SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              CABIN           ODOR            B  QMLRA   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      NM03106LN                       3251                                    SHORTLY AFTER TAKEOFF, PERSONNEL ONBOARD REPORTED A BURNING ODOR TO THE PILOT. ABORTED FLT AND RETURNED TO HELIPAD TO INVESTIGATE.  MECH PERFORMED AN INSPECTION OF THE AIRFRAME, ENGINE, WIRING, HOSES AND THE BELTS OF ALL COMPONENTS. NO DEFECTS OR THE SOURCE OF A BURNING ODOR WAS FOUND. SUBSEQUENT CHECK FLIGHT WAS PERFORMED BY THE PILOT & MECHANIC TO INVESTIGATE FOR BURNING ODOR, NONE FOUND. THE ACFT WAS RETURNED TO SERVICE. (K)                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H9EU    E00054EN             
             20081031     NE  2008       10         31         2008FA0000730    220080903G73212523631         BELLOWS                                                                    PWA   PT6   PT6A34AG    52053NE                              FCU             DAMAGED         B  IG0RK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      NM03                B32178                  PCEPH0028                   FCU (PN 32447866-6, SN B32178) BENCH TESTED AND FOUND TO BE UNSERVICEABLE DUE TO BREACHED BELLOWS, (PN 2523631, SN 8011). (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  T          E4EA                 
             20081104     CE  2008       11         4          2008FA0000731    120081030G3210244110010       PIVOT ASSY                              CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C220   GL  LT MLG          SHEARED         B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            LDLANDING        1                      GL005319V2532                   172RG0505   L3678636E   799482          THE LEFT MAIN LANDING GEAR PIVOT ASSY SHEARED IN TWO NEAR THE ACTUATOR END.  THE SPLICED SECTION WHERE THE DRIVE GEAR IS INSTALLED SEPARATED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A17    E286    5  CP7EA     
             20081104     CE  2008       11         4          2008FA0000732    120081016G212066151007        TUBE                                    CESSNA560   560XL       2076702CE                                                               AC BAY          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA273    2242                   5341                                    ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO, JUST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING.  CESSNA P/N 6615100-7                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA22CE                        
             20081104     SW  2008       11         4          2008FA0000733    120081030G3233B10006          COUPLING        DUKES                   MOONEYM20   M20E        5870212SW                                                               LANDING GEAR    FAILED          G      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      WP09204WF3483                   210021                                  DURING APPROACH FOR LANDING, THE PILOT WAS UNABLE TO GET THE LANDING GEAR TO EXTEND, EITHER NORMALLY OR USING THE EMERGENCY GEAR EXTENSION SYSTEM.  A GEAR-UP LANDING WAS ACCOMPLISHED WITH ONLY MINOR DAMAGE AND NO INJURIES.  SUBSEQUENT INVESTIGATION DETERMINED THAT THE COUPLING (P/N B100-06) BETWEEN THE LANDING GEAR MOTOR TRANSMISSION AND THE DRIVE ACTUATOR HAD BROKEN.  THE COUPLING HAS NO REPLACEMENT REQUIREMENTS, BUT IS RECOGNIZED IN MOONEY SERVICE INSTRUCTION M20-89 AS A PART THAT COULD FAIL DUE TO AGE HARDENING AND DETERIORATION.  THE AIRCRAFT OWNER WAS NOT AWARE OF THIS CONDITION.                                                                                                                                 1L71 3O      2A3                          
             20081104     EA  2008       11         4          2008FA0000735    220080925G7414M3828           GEAR            SLICK                   CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                              MAGNETO         DAMAGED         B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07658PW           08080703    18282098    L03291348E                  WHILE PERFORMING SB03-08, FOUND THE DISTRIBUTOR GEAR DRIVE GEAR WEARING PREMATURELY AND CAUSING GEAR DUST INSIDE MAGNETO. GEAR MATERIAL WAS COMING OFF CAUSING IT TO COLLECT INSIDE DISTRIBUTOR CAP. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE MAGNETO. REPLACED MAGNETO. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A13    1E4                  
             20081104         2008       11         4          2008FA0000737    220080905G7200                ENGINE                                  AMD   FALC20FALCON200   2730150EU                                                                               FOD             B  UO2RA   UNSCHED LANDING                                                                                 CJ F.O.D.                    WARNING INDICATION                                  CLCLIMB          1                      GL1969EC                        498                                     AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL, USED THROTTLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED AND DUPLICATED PROBLEM ON ENGINE GROUND RUN. ALL VISUAL INSP REVEALED NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 CYLINDER (NO OIL LEAK NOTICED). BECAUSE OF THIS ABNORMALITY, WE REMOVED THE OIL FILTER AND SUCTION SCREEN SHOWED SUBSTANTIAL METAL SHAVING AND SMALL PIECES OF METAL AND (2) SMALL SILVER COLOR BALLS (SUSPECT BALL BEARING OF SOME SORT). THE ENGINE WAS REMOVED FOR TEAR DOWN INSP AND REPAIR. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE AND EXHAUST LIFTER2L72 4F    RTA7EU                         
             20081104         2008       11         4          2008FA0000738    220080913G8500                ENGINE                                  AMD   FALC20FALCON200   2730150EU                                                                               MAKING METAL    B  UO2RA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL1969EC                        498                                     AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL & USED THROTTLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED & DUPLICATED PROBLEM ON GROUND RUN. NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 CYLINDER (NO OIL LEAK NOTICED). BECAUSE OF THIS ABNORMALITY, REMOVED OIL FILTER & SUCTION SCREEN SHOWED SUBSTANTIAL METAL SHAVING & SMALL PIECES OF METAL AND 2 SMALL SILVER COLORED BALLS (SUSPECT BALL BEARING OF SOME SORT). ENGINE REMOVED FOR TEAR DOWN INSP & REPAIR. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE & EXHAUST LIFTER BODIES OF NR 1 CYLINDER & EXTENSIVE DAMAGE OF ENGINE. A2L72 4F    RTA7EU                         
             20081113     CE  2008       11         13         2008FA0000739    120081103G3710                ADAPTER                                 CESSNA172   172M        2072418CE                                                               VACUUM SYS      DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      SW99308305902                   17264138                                AIRCRAFT HAD A FRESHLY OVERHAULED ENGINE INSTALLED AND WAS MAKING ITS FIRST FLIGHT.  DURING CRUISE, IN VFR CONDITIONS, THE PILOT NOTED A OVERHEATING TYPE OF ODOR AND THEN NOTED A MOMENTARY SMALL REDUCTION IN POWER AFTER WHICH POWER RETURNED TO NORMAL.  THE PILOT THEN NOTICED THAT BOTH GYROS BEGAN PROCESSING AND THE VACUUM GAUGE READ ZERO.  AIRCRAFT RETURNED WITHOUT FURTHER INCIDENT.  INVESTIGATION BY MAINTENANCE FOUND THAT THE VACUUM PUMP ADAPTER WAS DISCOLORED.  REMOVAL OF VACUUM PUMP FOUND THAT THE SPLINED SHAFT HAD MELTED AWAY AND ITS PARTICLES WERE CAUGHT BETWEEN PUMP AND ADAPTER.  MAINTENANCE NOTED THAT THE OIL DISTRIBUTION HOLES BETWEEN THE ADAPTER AND THE ENGINE WERE ALIGNED PROPERLY.  NO IMMEDIATE CAUSE1H71 3O    NT3A12                         
             20081106     EA  2008       11         6          2008FA0000740    220081001G7414AB382585        CONTACT                                 ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                              MAGNETO         DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM097087J                       2873                                    CONTACT ASSY, AS A NEW ASSY OPENS BEYOND THE MAXIMUM .024 INCH. THIS IS A REOCCURRING PROBLEM WITH BOTH THE LT AND THE RT CONTACT ASSEMBLIES. CIRCUMSTANCES ARE WHEN THE POINTS ARE REPLACED. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H10WE   E286                 
             20081106     EU  2008       11         6          2008FA0000741    120081026G6322MS210436        NUT                                     HUGHES369   369FF       4470709EU  ALLSN 250C  250C30      03013GL                              BLOWER          BACKED OUT      D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP195185G                       0009F                                   OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL US. NUT IS A STAINLESS STEEL, SILVER PLATED, ALL METAL SELF LOCKING TYPE NUT.  THIS WAS THE THIRD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO CAUSES THE SHAFT BEARING TO GO BAD WHICH DESTROYS THE OIL COOLER BELT.  THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSION OIL TEMPERATURES. AFTER INVESTIGATING PNS WE FOUND THAT MFG HAS BEEN USING THIS TYPE OF NUT FOR A LONG TIME AND WE ARE UNSURE IF THE NUTS CURRENTLY BEING PRODUCED ARE SUBSTANDARD.                                                                                                                                                                                   1G71 3U3  U  H3WE    E1GL                 
             20081106     EA  2008       11         6          2008FA0000742    220080925G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          CONTAMINATED    B  Z08RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07452SM5                      172S10528   L3343151E                   DURING INSPECTION FOR SB 03-08 THE FIRST 5 HOUR INSPECTION FOUND OIL ON THE COIL TAB ON BOTH MAGNETOS AND CAM WEARING ON BOTH MAGNETOS FOR THE AMOUNT HOURS ON MAGNETOS. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE DISTRIBUTOR FOR THE AMOUNT OF HOURS ON MAGNETOS. THIS IS CAUSING THE CARBON DUST TO COLLECT AND BUILDUP INSIDE MAGNETOS. (K)                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
             20081107     SW  2008       11         7          2008FA0000743    120080929G5541442283          SPAR                                    GULSTM112   114         7630314SW                                                               RUDDER          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA654945W603                    14267                                   SPAR IS CRACKED AND BROKEN OUT AT UPPER HINGE ATTACH POINT.  THIS SPAR WAS REPLACED WITH NEW 1-1-99 FOR SAME CONDITION.  THIS CONDITION WAS FOUND BY CLOSE EXAMINATION OF AREA DURING ANNUAL INSPECTION. WE ARE IN RECEIPT OF INFORMATION OF SAME FAILED CONDITION ON SN 14408.  RECOMMEND THAT DOUBLER BE INSTALLED TO STRENGTHEN SPAR IN THIS AREA.  (K)                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O      A12SO                        
             20081110     CE  2008       11         10         2008FA0000745    120080922G2820AN8156D         CONNECTOR                               RAYTHNB300  B300RAYTHEON7150007CE                                                               RT AUX TANK     DISCONNECTED    C      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      SO15102FL                       FL263                                   UPON ENGINE RUN-UP, OBSERVED FUEL DUMPING BUT RT HEATED FUEL VENT PROBE. UPON INVESTIGATION FOUND FUEL LINE DISCONNECTED INSIDE RT AUX TANK. FUEL LINE, PN 101-920000-9 FROM MOTIVE FLOW VALVE TO JET PUMP DISCONNECTED FROM UNION PN AN815-6D. FUEL LINE PN 101-920000-19, FOUND LOOSE ON UNION PN AN815-6D.  FUEL LINES FROM JET PUMP TO NACELLE TANK PN 101-920000-57 AND 101-920000-43 FOUND LOOSE ON UNION PN AN815-8D. RECONNECTED AND TIGHTENED ALL LINES AND FITTINGS INSIDE RT FUEL AUX TANK. INSPECTION OF LT FUEL AUX TANK FOUND ALL LINES AND FITTINGS OK. (K)                                                                                                                                                                      2L72 4T    RTA24CE                        
             20081107     NE  2008       11         7          2008FA0000746    220081015G7314                PUMP                                    BOEING727   727200      138407ENM  PWA   JT8   JT8D217C    52053NE                              FUEL SYS        MALFUNCTIONED   A  I5PAA   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      WP13705AA                       22462       726206U                     CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INCLUDING RESETTING SWITCHES, NO LIGHT OFF. ACFT DIVERTED AND THE CREW PERFORMED ENG INSPECTION AND START ON NR 1 ENG HIGH IGNITION SYS, ENGINE STARTED OK IN GROUND. START IGNITION NR 1 FROM HIGH-ENERGY FAIL IN FLIGHT POSITION. DEFERRED NR 1 ENG IGNITION IAW MEL 74-1 AND 705 CONTINUED SERVICE.  MAINT REMOVED AND REPLACED NR 1 ENG FUEL PUMP IAW MM 73-11-1, PURGE FUEL SYSTEM, PS4, PT7, AND P AND D VALVE CHECK FOR MOISTURE. PERFORMED FULL POWER ENGINE RUN AND LEAK CHECK SYSTEM OPERATIONAL CHECK, OK. (K)                                                                                                  2L73 4F4  FRTA3WE    E9NE                 
             20081121     CE  2008       11         21         2008FA0000747    120081106G3520C3512000205     OXYGEN MASK                             CESSNA500   550         2076604CE                                                               CABIN           TORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW9943SA 2500                   5500086                                 THREE OF THE DROP DOWN PASSENGER OXYGEN MASKS P/N C351-2000-205 OR CESSNA P/N 17504-61 WERE FOUND WITH TEARS IN THE FACE CUSHION NEXT TO THE INNER MASK HOUSING IN THE SAME AREA DESCRIBED IN AD 99-08-21.  HOWEVER THE ELASTOMERIC CURE DATES ON THESE MASKS ARE THE 3RD QUARTER OF 1999, THE AD ONLY ADDRESSES MASKS WITH A CURE DATE FROM 3RD QUARTER 1993 TO 1ST QUARTER 1997.  THESE TEARS COULD LEAD TO LEAKAGE AND POSSIBLE INSUFFICIENT OXYGEN DELIVERY AS DESCRIBED IN THE ORIGINAL A/D.                                                                                                                                                                                                                                               1L72 4F      A22CE                        
             20081110         2008       11         10         2008FA0000748    120081101G2810CB959           FUEL TANK                                                                                                                                               DAMAGED         B  RYHRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM03                                                                    FUEL TANKS WERE FOUND TO HAVE SIGNIFICANT LEAKS IN AN AREA NOT CLOSE TO ANY SEAMS, WELDS, OR BOSSES. THERE WERE NO VISIBLE DENTS, DINGS, SCRATCHES, GOUGES OR OTHER DAMAGE IN THE AREAS OF THE LEAKS. THE LEAK HOLES WERE MUCH SMALLER THAN THE DIAMETER OF A PIN AND WERE NOT VISUALLY DETECTABLE. TANKS WERE TAGGED UNAIRWORTHY.  FUEL TANKS WERE ALSO TAGGED UNAIRWORTHY PENDING FURTHER TESTINGS AS A PRECAUTION.  (K)                                                                                                                                                                                                                                                                                                                                                                
             20081128     GL  2008       11         28         2008FA0000750    220081106G720044904           STIFFENER       WILINT                                                     WILINTFJ44  FJ443A      66006GL                              LP TURBINE      SEPARATED       B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23     1858       AU00307                 141224                      WHILE UNDERGOING A CHECK 3 MAINT INSP DURING EARLY NOVEMBER 2008, THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NOZZLE ON ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE.  NO SECONDARY DAMAGE WAS NOTED.  PROBABLE CAUSE IS A SUSPECT MANUFACTURING OPERATION.                                                                                                                                                                                                                                                                                                                                                                                                                   4  F          E3GL                 
             20081126     EA  2008       11         26         2008FA0000751    220081024G7414SS1001          BOOSTER         SLICK                   HUGHES269   269C1       8059504SW  LYC   O360  HIO360G1A   41898EA                              ZONE 100        EXPLODED        D      EH  ENGINE SHUTDOWN         DEACTIVATE SYST/CIRCUITS                                                BA SMOKE/FUMES/ODORS/SPARKS  FLAME/FIRE                                          TOTAKEOFF        1                      SW412014T701  50                0313        L3373151A                   START MAGNETO, START BOOSTER BOX PN SS1001 BLEW THE TOP PORTION APART. IT CAUGHT ON FIRE AND SMOKE WENT EVERYWHERE. INSPECTED HELICOPTER WHEN SMOKE CLEARED AND COULD NOT FIND THE PROBLEM. TURNED OFF THE FUEL AND BUMPED THE STARTER AND FOUND THE PROBLEM TO BE THE START BOX. WITHIN JUST BUMPING THE STARTER , HELICOPTER WAS COVERED IN SMOKE. I REMOVED AND REPLACED THE BOX AND INSPECTED ALL THE WIRING AND ALL IS WORKING JUST FINE NOW. BIGGEST PROBLEM I SEE IS THAT THE SLICK START BOX SETS TO CLOSE TO THE FUEL MAIN LINE, WITCH COULD OF LED TO A COMPLETE LOSS OF AIRCRAFT.                                                                                                                                                    1G71 3O3  OO 4H12    1E10                 
             20081125     CE  2008       11         25         2008FA0000752    120081103G3320CLE23602        LIGHT                                   CESSNA560   560XL       2076702CE                                                               CABIN           BURNED OUT      C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13669TT714                    5684                                    DURING POSTFLIGHT FOUND CABIN (LT) UPWASH, AND (RT) DOWNWASH LED LIGHT ELEMENTS INOP. INTIALLY TROUBLESHOOTING FOUND CIRCUIT BREAKER 140 IN THE INTERIOR DC "J" BOX OPEN. ATTEMPTED TO RESET, BREAKER WOULD OPEN IMMEDIATLY WHEN THE CABIN LIGHT SWITCH WAS ACTIVATED ON. FURTHER TROUBLESHOOTING FOUND THAT THE LT AFT CABIN UPWASH LIGHT ELEMENT SHOWED EVIDENCE OF EXCESSIVE HEAT APPROX IN THE MIDDLE OF  ELEMENT. REMOVED LIGHT ELEMENT AND INSTALLED SERVICEABLE O/H ELEMENT. OPS CHECK OF SYS PERFORMED, SYS CHECKS GOOD.  TECH SUPPORT SUGGESTS MOISTURE INGRESS AS THE CAUSE OF THE LIGHT ELEMENT FAILURE. DEFECTIVE PART WAS RETURNED TO MFG CPD.                                                                                     2L72 4F    RTA22CE                        
             20081125     SO  2008       11         25         2008FA0000753    220081107G7414                IMPULSE COUPLING                                                           CONT  O550  IO550N      17042SO                              MAGNETO         INOPERATIVE     D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15502BZ1021       D05KA054                917755                      WHILE REMOVING MAGNETO FOR EXCHANGE FOUND IMPULSE COUPLING INOPERABLE.  THIS IS THE SECOND LOW TIME MAGNETO OF THIS MODEL FOUND WITH A BAD IMPULSE COUPLING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           3  O          E3SO                 
             20081125     EA  2008       11         25         2008FA0000754    220081111G74144371            MAGNETO                                 PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA                              ENGINE          OUT OF POSITION D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL039360C90                     287890401   L2454636A                   EXCESSIVE TIMING DRIFT.  BOTH MAGS SET 25 DEGREES BTDC ON NR1 CYLINDER.  NEXT FIRING ORDER (NR 3 CYLINDER) IS OFF 6 DEGREES BETWEEN LT/RT MAG.  NEXT FIRING ORDER (NR2 CYLINDER) IS NORMAL.  LAST FIRING ORDER (NR4 CYLINDER) IS OFF 6 DEGREES BETWEEN LT/RT MAGS.  INITIAL SUSPECT IS CAM LOBE.  CARBON BRUSH INSPECTED IAW SB3-08.  BRUSH SHOWS POSSIBLE INDICATION OF (EARLY STAGE) UNDERCUT.  SLIGHT BRUSH RESIDUE EVIDENCED ON BEARING BAR.                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A13    E286                 
             20081112     EU  2008       11         12         2008FA0000755    120080930G7603                JOINT                                   PIAGIOP180  P180        6960204EU                                                               CONTROL CABLE   DAMAGED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW9923RF                        1080                                    RT ENGINE POWER CONTROL CABLES FREEZING AT ALTITUDE. INSPECTED CABLE AND FOUND THE STAINLESS STEEL SLEEVE DISCONNECTED AT JOINT TO FLEX SLEEVE. IT APPEARS TO BE A SILVER SOLDERED JOINT, AND SOLDER FAILED ALLOWING MOISTURE TO ENTER THE INTERNAL OF CABLE AND FREEZE WHICH COULD CAUSE LOSS OF MOTION OF THE CONTROL CABLES AND CAUSE FUEL CONTROL CABLES NOT TO ACHIEVE FULL TRAVEL, RESTRICTING ENGINE POWER.                                                                                                                                                                                                                                                                                                                              1H72 3O    RTA59EU                        
             20081125     CE  2008       11         25         2008FA0000756    120081112G7120051313211       MOUNT                                   CESSNA175   175         2072502CE                                                               ZONE 100        CRACKED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23175UK                       55829                                   DURING INSP, MECHANIC FOUND THE LT UPPER ENGINE MOUNT BRACKET, PN 0513132-11, CRACKED ALL THE WAY THROUGH. CRACK WAS AT THE OUTER RADIUS OF THE WASHER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O    NT3A17                         
             20081112     SW  2008       11         12         2008FA0000757    120080718G5610                WINDOW                                  ECLIPSEA500 ECLIPSEEA5003350000SW                                                               COCKPIT         FAILED          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA61136EA                       000136                                  THERE WAS A POPPING NOISE COMING FRAOM THE VICINITY OF THE PILOTS WINDOW, WINDOW WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4J    RTA00002AC                     
             20081112     SW  2008       11         12         2008FA0000758    120080818G2621FX002002        EXTINGUISHER                            ECLIPSEA500 ECLIPSEEA5003350000SW                                                               RT NACELLE      LEAKING         C      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      EA61575CC                       000075                                  RT ENGINE FIRE EXTINGUISHER CARTRIDGE LEAKED THROUGH DISCHARGE NOZZLE AND EXPOSED THE ENGINE AND COMPONENTS TO HIGHLY CORROSIVE CHEMICAL. ENGINE REMOVED FOR CLEAN UP AND REPAIR BY MANUFACTURER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4J    RTA00002AC                     
             20081112     SW  2008       11         12         2008FA0000759    120080911G5340                RETAINER                                ECLIPSEA500 ECLIPSEEA5003350000SW                                                               COCKPIT WINDOW  UNKNOWN         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA61568EA                       000168                                  A POPPING NOISE COMING FROM THE VICINITY OF THE CO PILOTS WINDOW. SIDE WINDOW RETAINERS WERE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4J    RTA00002AC                     
             20081125     SO  2008       11         25         2008FA0000760    220081112G8530AEC631397       CYLINDER                                CESSNA188   188B        2073007CE  CONT  O550  IO550D      17042SO  MCAULYD3A34 D3A34C401   GL  ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0778417                       18801952T   1580856D    001465          FOUND ALL 6 CYLINDERS WERE CRACKED.  CYLINDER NR1 S/N 50422-12, CRACKED BETWEEN COOLING FIN 16 AND 17 (COUNTED DOWN FROM TOP) FROM THE INTAKE PORT ALL THE WAY AROUND THE CYLINDER, OVER THE TOP SPARK PLUG HOLE, TO THE EXHAUST PORT.  2 CRACKS ON THE INSIDE FROM THE TOP SPARK PLUG HOLE TO THE INTAKE SEAT AND THE INTAKE SEAT TO THE EXHAUST SEAT.  AN APPROX .1250 X .2500 HOLE BY THE EXHAUST SEAT ALL THE WAY THROUGH THE HEAD.  THE OTHER 5 CYLINDERS (S/N 50741-13, 50974-19, 50960-01, 50422-06, AND 50991-25) ARE CRACKED UNDER FIN 16 OR 17 ANYWHERE FROM 1INCH TO 6 INCH LONG ON THE OUTSIDE OF THE INTAKE PORT, APPROX MIDDLE SECTION OF THE HEAD (CRACKS RUN PARALLEL WITH COOLING FINS).                                       1L71 3O3  O  A9CE    E3SO    5  CP47GL    
             20081126     SO  2008       11         26         2008FA0000761    120081113G53477745405         SEAT TRACK                              PIPER PA38  PA38112     7103812SO                                                               ZONE 100        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM092472D                       3879A0327                               PASSENGER SEAT WAS REMOVED FOR ANNUAL INSPECTION.  UPON VISUAL INSPECTION OF SEAT RAILS, A CRACK WAS DISCOVERED GOING THROUGH THE ENTIRE RAIL.  THE SEAT RAIL MUST BE REPLACED IN ORDER TO FACILITATE SAFE FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O      A18SO                        
             20081118     CE  2008       11         18         2008FA0000762    120081020G2721S22952593       CHAIN           CESSNA                  CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA                              RUDDER TRIM     BROKEN          B  BGSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21169EC288                    172RG0515   L2843836A                   DURING A NON RELATED MAINTENANCE ACTION, THE MECHANIC NOTICED THE RUDDER TRIM WHEEL WAS MOVING WITH NO RESISTANCE. THE MECHANIC INSPECTED FURTHER AND FOUND THE CHAIN HAD SEPARATED AT ONE OF THE LINKS.  AFTER CLOSER EXAMINATION IT HAS BEEN FOUND THAT SEVERAL OF THE LINK PINS ARE EITHER TOO SHORT OR WAS NOT PRESSED ENOUGH TO HOLD THE LINKS TOGETHER.  THE PART WAS ORDERED FROM MFG.  (K)                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  3A17    E286                 
             20081118     CE  2008       11         18         2008FA0000763    120081008G2720717             SOLENOID VALVE                          BEECH 90    C90         1152913CE                                                               RUDDER          STUCK           B  E81RO   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      GL03261GB5351                   LJ1119                                  INVESTIGATED PILOT REPORT OF RUDDER BOOST CONSTANTLY KICKING TO LEFT.  FOUND PN 717 LT SOLENOID VALVE STUCK IN OPEN POSITION.  ALSO FOUND (3) PN AN9181D RUDDER BOOST CONTROL SYSTEM CROSS FITTING CRACKED AND WATER IN SYSTEM.  PURGED WATER FROM SYSTEM AND REPLACED LT SOLENOID VALVE, CRACKED FITTINGS AND SYSTEM FILTER; OPERATIONS NORMAL.  SUSPTECT CONDENSATION OR OTHER SOURCE OF WATER INGESTION INTO SYSTEM THAT CAUSED FREEZING DAMAGE TO COMPONENTS.  (K)                                                                                                                                                                                                                                                                          1L72 3T      3A20                         
             20081118     CE  2008       11         18         2008FA0000764    120081021G276021EN96          SWITCH                                  BEECH MU300 400A        1155402CE                                                               SPEED BRAKE SYS CORRODED        B  E81RO   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      GL0348SE                        RK48                                    INVESTIGATED PILOT REPORT OF UNCOMMANDED "SPEEDBRAKE EXTENDED" ANNUNCIATOR LIGHT ILLUMINATION IN FLIGHT.  FOUND HIGH RESISTANCE IN SPOILER MIXER ASSY.  SPEEDBRAKE RETRACT SWITCH ASSY, REPLACED S156 SWITCH WITH SUPERSEDING PN 21EN42-6 SWITCH ASSY.  SPEEDBRAKE SYSTEM OPERATIONS NORMAL, NO FAULTS INDICATED.  SUSPECT S156 SWITCH CONTACTS CORRODED OR PITTED FRO WEAR AND/OR LONGTERM WATER/DIRT CONTAMINATION.  RECOMMEND SIMILAR SWITCHES ON BE 400 SERIES AIRCRAFT BE REPLACED WITH IMPROVED SWITCHES WITH BETTER SEALING CAPABILITIES BY RECOMMENDED SERVICE BULLETIN OR SIMILAR.  (K)                                                                                                                                                2H72 4F    RTA16SW                        
             20081118         2008       11         18         2008FA0000765    420081020G345713824120211     GPS                                     SNIAS 350   AS350BA     8680817EU                                                               COCKPIT         OVERHEATED      B  H0CRAH  UNSCHED LANDING         DEACTIVATE SYST/CIRCUITS                                                B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      WP0129FX                        2085                                    DURING FLIGHT, THE TRIMBLE GPS OVERHEATED AND EMITTED SMOKE.  THE PILOT MADE A PRECAUTIONARY LANDING AND SECURED POWER TO THE GPS BY REMOVING THE FUSE.  THE UNIT HAD BEEN INSTALLED SINCE 1996.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U    NCH9EU                         
             20081124     GL  2008       11         24         2008FA0000766    120080808G2752EM41165         ACTUATOR                                AMTR  LANCARLANCAIR320  056300AGL                                                               TE FLAP         FAILED          C  TOWRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL09320LA                       269                                     MULTIPLE FLAP ACTUATION FAILURES. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O    RTEXPA1L71                     
             20081124     CE  2008       11         24         2008FA0000769    120081010G27101260505315      CONTROL CABLE                           CESSNA210   210N        2073453CE  CONT  O520  IO520*      17032SO                              TR AILERON      WORN            B  TF2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE056523N3369                   21063081                                DURING ANNUAL INSP, THE RT AILERON RETURN CABLE WAS FOUND WORN BEYOND LIMITS BY THE WHITE PLASTIC PULLEY NEAR THE LEADING EDGE AT THE WING ROOT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A21    E5CE                 
             20081120     CE  2008       11         20         2008FA0000770    120081026G2720441921933       RUDDER PEDAL                            CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              COCKPIT         JAMMED          B  CNQRK   NONE                                                                                            O  OTHER                                                                         DEDESCENT        1                      CE01370QS                       6800099                                 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF.  AN EMERGENCY WAS DECLARED AND THE ACFT LANDED UNEVENTFULLY.  DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER MAINT WITH NO REPORTED ISSUES.  THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY.  A SCR (SERVICE CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYPE INSTALLATION.  (K)                                                                                                    2L72 4F4  FRCT00012WIE35NE                
             20081120     CE  2008       11         20         2008FA0000771    120081026G2720                RUDDER PEDAL                            CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              COCKPIT         JAMMED          B  CNQRO   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CE07370QS                       6800099                                 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF.  AN EMERGENCY WAS DECLARED AND THE ACFT LANDED UNEVENTFULLY.  DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER MAINT WITH NO REPORTED ISSUES.  THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY.  A SCR (SERVICE CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYPE INSTALLATION.  (K)                                                                                                    2L72 4F4  FRCT00012WIE35NE                
             20081120     CE  2008       11         20         2008FA0000772    120081002G275067183281        CONTROLLER                              CESSNA750   750         2076810CE  ALLSN AE3007AE3007C     03047GL                              TE FLAP         FAILED          B  CNQRO   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CE0778SL                        7500238                                 FLAPS HARD FAILED DURING FLIGHT.  FOUND THAT THE FLAP CONTROLLER HARD FAILED DURING COLD SOAKING.  REPLACED FLAP CONTROLLER AND ACCOMPLISHED SATISFACTORY FLAP FUNCTIONAL CHECK WITH NO DEFECTS NOTED.  RETURNED ACFT TO SERVICE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4J4  FRTT00007WITE6CH                
             20081120     SO  2008       11         20         2008FA0000773    220080929G853065315           CYLINDER                                CESSNA150   150L        2071826CE  CONT  O200  O200A       17020SO                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO155307Q1081                   15073207    21411272A                   NR 4 CYLINDER FOUND CRACK AT BARREL BETWEEN COOLING FINS.  CRACK WAS APPROX 300 DEGREES AROUND CYLINDER CIRCUMFERENCE.  SYMPTOMS INCLUDED ROUGH RUNNING, LARGE OIL LEAK AND SMOKE.  CATASTROPHIC FAILURE WAS EMANATE AND WOULD HAVE CAUSED COMPLETE LOSS OF ENGINE POWER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  3A19    E252                 
             20081120     EU  2008       11         20         2008FA0000774    120081031G5210709010401101    TRIM TAB                                AGUSTAA109  A119        0261102EU  PWA   PT6   PT6B37A     52179NE                              MAIN ROTOR BLADEDELAMINATED     D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17315PD                       14035       PU0041                      UPON POST FLIGHT IT WAS NOTICED THE MAIN ROTOR BLADE TRIM TAB WAS SERIOUSLY DELAMINATED AND SEPARATED IN FLIGHT. THIS PROBLEM HAS OCCURRED NUMEROUS TIMES IN THE PAST.  SOME OCCASIONS REQUIRED THE BLADE TO BE REMOVED AND SENT BACK TO THE MFG FOR REPAIR.  AS IN THIS CASE, OTHER TIMES THE BLADE WAS ABLE TO BE REPAIRED AT OUR FACILITY IAW MM.  MFG IS AWARE OF THIS PROBLEM AND STILL HAS NOT CORRECTED IT.  PROBABLE CAUSE IS THE BONDING MATERIAL AND/OR THE BONDING PROCEDURE.  (K)                                                                                                                                                                                                                                                   1G71 3U4  U  H7EU    E4EA                 
             20081120     EA  2008       11         20         2008FA0000775    220081027G7322383493          SERVO                                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          DEFECTIVE       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO115339M2362                   172S9359    L3084051A                   PN 383943 PLUG FOUND HANGING BY SAFETY WIRE WHEN TROUBLESHOOTING LACK OF POWER FROM ENGINE.  THREADS IN COVER MISSING.  THIS SERVO WAS NOT INCLUDED IN AD2008-08-14 DUE TO MFG DATE OF UNIT.  THE SERVO WAS ORIGINAL EQUIPMENT ON A 2003, 172S, WITH A TT OF 2462.0 HOURS AND HAD NOT BEEN REPAIRED OR O/H.  PLUG GASKET WAS MISSING. (K)                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    1E10                 
             20081125     EA  2008       11         25         2008FA0000776    220081024G8530AEL75838        GUIDE                                   BELL  47    47G4A       1181031SW  LYC   O540  VO540B1B3   41532EA                              NR 1 CYLINDER   WORN            G  PFIGK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1324HM                        7688        L245043                     DURING INVESTIGATION OF AN ACCIDENT IN WHICH ACFT LOST POWER AND WAS FORCED TO LAND THE FOLLOWING WAS DISCOVERED: COMPRESSION CHECK REVEALED THE NR 1 CYL WAS LEAKING PAST THE EXHAUST VALVE. (COMPRESSION 45/80).  EXAMINATION OF THE CYLINDER REVEALED THE EXHAUST GUIDE WAS EXTREMELY WORN AND CRACKED IN 4 PLACES.  VALVE OD .496 INCH GUIDE ID .540 INCH, .044 INCH CLEARANCE.  IT WAS FURTHER DISCOVERED THAT THE VALVE WAS PN SL-16740 NIMONIC VALVE GUIDE. THIS VALVE REQUIRES THE USE OF A HIGH CHROME CONTENT NI-RESIST VALVE GUIDE.  ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED.  THIS IS A NI-RESIST VALVE GUIDE.  ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED.  THIS IS A NI-RESIST GUIDE.  HOWEVER IT DOES NOT HAVE THE CHROM1G71 3O3  O  2H3     E304                 
             20081120     CE  2008       11         20         2008FA0000777    120081024G2820                FUEL LINE                               CESSNA340   340A        2076405CE  CONT  O520  TSIO520*    17040SO                              FUEL SYSTEM     CORRODED        D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      GL07340SU3808                   340A0979                                THE FUEL CROSSFEED LINE LT TANK TO RT ENGINE, HAD CORRODED TO THE POINT OF LEAKAGE.  THE CORRODED AREA WAS UNDER THE CABIN FLOOR BEHIND THE CO-PILOT SEAT.  THE DUCTWORK FOR THE CABIN VENTILATION SYSTEM LAYS ON THE LINE THIS LOCATION.  THE CORROSION WAS LIMITED TO THE AREA OF CONTACT.  PIN HOLES HAD DEVELOPED ALLOWING A SMALL QUANTITY OF FUEL TO LEAK, NOT ENOUGH TO DRIP, BUT ENOUGH TO SATURATE THE DUCT WORK AND PRODUCE A STRONG ODOR IN THE CABIN.  THE VENTILATION DUCT MUST BE MOVED FOR VISUAL INSPECTION.  IN ADDITION, WHEN THE LINE WAS REMOVED, THERE IS EVIDENCE OF ABRASION FROM CONTROL CABLES AT THE OTBD PORTION OF THE LINE.  THIS NEEDS TO BE INSPECTED AT THE NEXT OPPORTUNITY.  (K)                              1L72 3O3  O  3A25    E8CE                 
             20081120     CE  2008       11         20         2008FA0000778    120081029G551165320104        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000779    120081029G551165320125        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000780    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000781    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000782    120081029G551165320144        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000783    120081029G551165320104        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000784    120081029G551165320114        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000785    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000786    120081029G551165320135        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000787    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000788    120081029G551165320145        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000789    120081029G551165320144        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000790    120081029G551165320154        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09371QS                       5600471                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY   INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                             2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000791    120081029G551165320104        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000792    120081029G551165320114        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                               2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000793    120081029G551165320125        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000794    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000795    120081029G551165320135        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000796    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000797    120081029G551165320145        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY  INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000798    120081029G551165320154        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000799    120081029G551165320104        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000800    120081029G551165320114        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000801    120081029G551165320125        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000802    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000803    120081029G551165320123        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000804    120081029G551165320135        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000805    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000806    120081029G551165320133        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000807    120081029G551165320145        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000808    120081029G551165320144        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000809    120081029G551165320143        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000810    120081029G551165320163        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000811    120081029G551165320174        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09330QS                       5600329                                 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                              2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000812    120081029G551165320104        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000813    120081029G551165320125        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000814    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000815    120081029G551165320135        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000816    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000817    120081029G551165320145        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000818    120081029G551165320144        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000819    120081029G551165320154        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000820    120081029G551165320164        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000821    120081029G551165320193        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000822    120081029G551165320144        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000823    120081029G551165320114        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000824    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000825    120081029G551165320124        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000826    120081029G551165320135        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000827    120081029G551165320134        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000828    120081029G551165320145        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000829    120081029G5511                RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000830    120081029G551165320154        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000831    120081029G551165320164        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081120     CE  2008       11         20         2008FA0000832    120081029G551165320174        RIB                                     CESSNA500   560CESSNA   2076750CE                                                               HORIZ STAB      CRACKED         B  JQ0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09363QS                       5600536                                 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AFTER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED.  (K)                                                                                                        2L72 4F    RTA22CE                        
             20081124     EA  2008       11         24         2008FA0000833    220081101G7414M3008           DISTRIBUTOR GEARSLICK                   CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA                              MAGNETO         DESTROYED       D  DF2SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW154260Q1186       04070369    17260160                                CONTACT PIN ON THE DISTRIBUTOR GEAR COMES LOOSE AND IS UNUSEABLE.  PLASTIC HOLDING IT ON IS CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274                 
             20081126     GL  2008       11         26         2008FA0000834    220081106G725072165           TURBINE NOZZLE                                                             WILINTFJ44  FJ44        66000GL                              ENGINE          SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09     1858                               141224                      WHILE UNDER GOING A CHECK 3 MAINTENANCE INSPECTION,  THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NOZZLE ON THIS ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE.  NO PROBABLE CAUSE IS A SUSPECT MFG OPERATION.  HELD FOR INVESTIGATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                     4  F          E3GL                 
             20081125     GL  2008       11         25         2008FA0000835    220080930G731323031938        DIAPHRAGM                                                                  ALLSN 250C  250C20B     03013GL                              NOZZLE          CRACKED         C  HEFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP01     1568                               CAT34079                    FLOURESCENT PENTRANT INSPECTION PRODUCED INDICATIONS AT 2 LOCATIONS ALONG BRAZING WHERE DIAPHRAGM AND OUTER RING ARE JOINED.  INDICATIONS ARE APPROXIMATELY 1.60 AND 2.50 INCHES LONG, APPROX 180 DEGREES APART.  VOIDS IN BRAZING ARE ALSO PRESENT AT 2 LOCATIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               3  U          E4CE                 
             20081125     CE  2008       11         25         2008FA0000836    120081120G2750                FLAP SYSTEM                             CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160CTM    GL  ZONE 600        FAILED          C      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      SW99                            17259899    L3814327A                   ON FINAL APPROACH THE PILOT DECIDED TO EXECUTE A GO AROUND AND AS HE BROUGHT UP THE FLAPS TO THE 20 DEGREE SETTING THE RT FLAP INBD ROLLER SUPPORT JAMMED IN THE FLAP TRACK ASSY AND THE FLAP RETRACTED CROOKED AND JAMMED AGAINST THE RT AILERON LEAVING THE RT AILERON STUCK IN THE UP POSITION AND CAUSING AN ASYMMETRICAL FLAP CONDITION WHICH CAUSED THE AIRPLANE TO PULL TO THE RT.  WITH FULL LT PRESSURE ON THE YOKE AND WITH RUDDER THE PILOT WAS ABLE TO CONTROL THE AIRPLANE. THE PILOT WAS ABLE TO TURN LT AND WITHOUT FURTHER INCIDENT FLY THE PATTERN AND LAND THE AIRPLANE SAFELY.                                                                                                                                               1H71 3O3  ONT3A12    E274    5  NP910     
             20081201     NM  2008       12         1          2008FA0000838    120081121G36107732873         PRECOOLER                               BOEING767   767222      1385122NM                                                               ZONE 400        FRACTURED       B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39767VA7738777387             21870                                   NR1 PYLON PRECOOLER CRACKED IN SEVERAL PLACES.  REMOVED AND REPLACED NR1 ENG PRECOOLER IAW MM 36-11-15. WORK PERFORMED ON NR 35501 S/O 599197.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA1NM                         
             20081201     EU  2008       12         1          2008FA0000839    120081122G7700NE00000133101   SENSOR                                  DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE1250299       EU                              CRANKSHAFT      DIRTY           D      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      SW99490TS244                    42AC090     020201763                   FADEC CONTROLLED POWERPLANT/ HAD UNCOMMANDED POWER REDUCTION TO 75 PERCENT (3 SEPARATE WRITE-UPS) ACCOMPANIED BY MINOR ENGINE SURGING AT VARIOUS TIMES DURING NORMAL CRUISE FLIGHT. MFG FIX WAS RE-DESIGNED FADEC SOFTWARE, THAT DID NOT ALLEVIATE THE PROBLEM. WHILE PERFORMING A CLUTCH PLATE INSPECTION THE AREA WAS CLEANED AS WELL AS THE CRANKSHAFT POSITION SENSORS, WHICH IS ONE OF THE FADECS SENSORY INPUTS. THIS ACTION SEEMED TO RESOLVE THE AFOREMENTIONED PROBLEMS. TO DATE THERE IS APPROX 23 HOURS OF ENGINE OPERATION TIME WITH NO REPEAT OF THE ISSUE. OTHER OPERATORS HAVE DESCRIBED HAVING THE SAME TYPE OF PROBLEM.                                                                                                       1L72 3I3  BRTA57CE   E00069EN             
             20081202     SW  2008       12         2          2008FA0000840    120081124G2400MS902982        GROUND STUD                             MOONEYM20   M20K        5870220SW  CONT  O360  TSIO360*    17025SO                              AIRFRAME        MISINSTALLED    D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO13305P 2847                   250524                                  AIRFRAME GROUND PLUG IN HAS NEVER BEEN CONNECTED TO AIRFRAME GROUND. BASE OF RECEPTACLE WAS INSULATED FROM AIRFRAME GROUND BY PRIMER ON METAL ANGLE. WE FOUND COMPLETE ISOLATION FROM GROUND POINT TO FUEL FILLER OPENING, NO GROUND ON OUR FUELING OPERATIONS FOR PAST 3 YEARS. MFG SHOULD CHECK CONTINUITY ON AIRFRAME GROUND PORT AT MFG SINCE NO OTHER TIME IN LIFE OF ACFT IS IT REQUIRED TO CHECK.                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  2A3     E9CE                 
             20081202     GL  2008       12         2          2008FA0000841    120081124G5210                LATCH                                   DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE  HARTZLHCC2Y HCC2YR1     GL  PAX DOOR        DISENGAGED      P      BA  EMER. DESCENT           UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      SW99661DS1050                   40600       L3241251A   CH39369B        AT 10500 FT IN CRUISE FLIGHT, GOT AN AUDIBLE "DING" ON THE G1000 WARNING AND THEN A LIGHT SAYING THAT A DOOR WAS OPEN. BACK DOOR HAD COME OPEN IN FLIGHT.  THE DOOR HAD BEEN SHUT AND THERE HAD BEEN NO WARNING DURING PRE-FLIGHT CHECK AND RUN-UP.  WAS IN THE RT SEAT AND COULD NOT REACH THE DOOR UNTIL I UNDONE MY SEATBELT.  TRIED TO SHUT THE DOOR, BUT DUE THE DESIGN OF THE HANDLE, THERE IS NO WAY TO SHUT THE DOOR.  THE SAFETY LATCH WAS ABOUT TO LET GO AND I HELD ONTO THE HANDLE AS LONG AS I COULD.  IT FINALLY GOT INTO THE AIR SCREAM AND WAS JERKED OUT OF MY HAND AND THEN THE DOOR DEPARTED THE AIRCRAFT.  DECLARED AN EMERGENCY AND LANDED.                                                                                1L71 3O3  ONTA47CE   E1CE    5  CP920     
             20081202     SW  2008       12         2          2008FA0000842    120081124G2897                GROUND WIRE                             BELL  206   206B3       1181506SW                                                               BOOST PUMP      MISSING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP28304PD6486                   4525                                    MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681-101.  OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.                                                                                                                                                                                                                                                                                                            1G71 3U      H2SW                         
             20081202     SO  2008       12         2          2008FA0000843    120081110G5414                COWLING                                 PIPER PA32  PA32300     7103212SO  LYC   O540  IO540*      41532EA                              ZONE 400        BROKEN          G      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      SO192772P6938 6905              3240456                                 AFTER LIFTOFF, AT APPROX 250 TO 300 FEET AGL THE RT SIDE OF THE UPPER ENGINE COWLING CAME LOOSE AND BROKE OFF AT APPROX THE MIDDLE LT PORTION OF THE COWLING, FALLING TO THE GROUND.  THE ACFT HAD UNDERGONE A 100 HOUR INSP ON  THE ENGINE AT 6905.8 HRS. OWNER STATED NO ADDITIONAL MAINT SINCE THAT TIME.                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  A3SO    1E4                  
             20081202     SW  2008       12         2          2008FA0000844    120081124G2897                GROUND WIRE                             BELL  206   206B3       1181506SW                                                               BOOST PUMP      MISSING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07305PD2853                   4586                                    MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681-101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.                                                                                                                                                                                                                                                                                                       1G71 3U      H2SW                         
             20081202     SW  2008       12         2          2008FA0000845    120081124G2897                GROUND WIRE                             BELL  206   206B3       1181506SW                                                               BOOST PUMP      MISSING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07306PD                       4588                                    MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681-101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.                                                                                                                                                                                                                                                                                                       1G71 3U      H2SW                         
             20081201     SW  2008       12         1          2008FA0000846    120081124G2897                GROUND WIRE                             BELL  206   206B3       1181506SW  ALLSN 250C  250C20J     03013GL                              BOOST PUMP      MISSING         D      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      WP07306PD1990                   4588                                    MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681-101. OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H2SW    E4CE                 
             20081202     CE  2008       12         2          2008FA0000847    120081125G8011S539800M015     SPRING                                  BEECH 95    95B55       1152729CE  CONT  O470  IO470L      17026SO                              STARTER ADAPTER BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW135716V14   14    CAS2234     TC990       272745R                     STARTER ADAPTER P/N 635050-A4, STARTER SPRING FAILED.  STARTER ADAPTER OVERHAULED, RETURNED TO SERVICE AFTER OVERHAUL. PART SOLD, STARTER ADAPTER INSPECTED AND RETAGGED AND SOLD TO MFG. MAINT INSTALLED STARTER ADAPTER AND SPRING FAILED 14 HOURS LATER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  ORT3A16    3E1                  
             20081202     EA  2008       12         2          2008FA0000848    220081119G7310STD2048ORLW18733HOSE                                    CESSNA182   182         2072702CE  LYC   O540  TIO540AK1A       EA                              FUEL SYSTEM     DETERIORATED    D      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      NM0972758554                    T18208004   L1088361A                   ENGINE LOST RPM AND PARTIAL POWER ON GO-AROUND FROM REJECTED LANDING.  ACFT THEN FLEW NORMAL PATTERN AND LANDED WITHOUT INCIDENT.  GROUND RUN-UP SHOWED NO ABNORMALITIES.  MAINT REMOVED INJECTOR NOZZLES.  NR 2 CYL NOZZLE WAS PLUGGED AND CONTAMINANTS FOUND IN SEVERAL OTHER INJECTORS.  THE CONTAMINANTS APPEARED TO BE FLAKES FROM THE INSIDE OF AIR BLEED HOSES TO THE INJECTOR NOZZLES.  THE HOSES ARE HARDENED BY HEAT AND SHOW CRACKING; THEY ARE CHIPPED WHERE THEY SLIDE ONTO THE NOZZLE TUBES.  WE INSTALLED NEW HOSES.  PERHAPS HOSE P/N LW-18737 SHOULD BE REPLACED AT 500 HOUR INTERVALS.                                                                                                                                        1H71 3O3  ONT3A13                         
             20081201     SW  2008       12         1          2008FA0000849    120081101G243530B4521A        STARTER GEN                             NAMER T28C  T28C        6402509SW                                                               ENGINE          FAILED          B  XB2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0139FS                        624480                                  STARTER GEN PREVIOUSLY HAD A FIELD FAILURE-COMPLETE MELT DOWN AFTER APPROX 12 FLIGHTS AFTER OVERHAUL.  IT WAS REPAIRED UNDER WARRANTY AND REINSTALLED.  AFTER APPROX 4 FLIGHTS IT WOULD NOT CONSISTENTLY CARRY THE LOAD.  ACFT REGULATION/CHARGING SYST CHECKED AND FOUND CORRECT.  THE INSP COVER ON THE GENERATOR WAS REMOVED AND DAMAGE TO THE COMMUTATOR WAS FOUND PROBABLY DUE TO THE PREVIOUS FAILURE.  INSP OF 1 SET OF BRUSHES REVEALED GROOVED FACES AND THE LACK OF PROPER BRUSH RUN AT OVERHAUL.  AS STATED THIS IS 2ND FAILURE OF THIS ITEM IN A VERY SHORT TIME, THESE FAILURES ARE OBVIOUSLY DUE TO THE LACK OF PROPER PROCEDURES/ WORKMANSHIP BEING FOLLOWED.  (K)                                                               1L71 4R    RTEXPA1L71                     
             20081201         2008       12         1          2008FA0000850    420081024G2565                PIN                                     BOEING767   767238      1385114NM  PWA   JT9   JT9D7R4D    52054NE                              EVAC SLIDE      INSTALLED       B  M4QRK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      SW19673BF43                     23402                                   A SLIDE DEPLOYMENT OF THE RT AFT ENTRY DOOR OF THE ACFT WAS ATTEMPTED IN CONJUNCTION WITH A DITCHING DEMONSTRATION IN SUPPORT OF OUR FAR PART 125 CONFORMITY ASSESSMENT BY FSDO - 25.  THE SLIDE DID NOT EXTRACT FROM THE DOOR BUSTLE AS THE DOOR WAS OPENED.  UPON INVESTIGATION OF THE CAUSE OF THE FAILURE, IT WAS FOUND THAT THE GIRT BAR WAS NOT PROPERLY INSERTED INTO THE GIRT BAR CARRIER OF THE SLIDE AS CALLED OUT IN AMM 25-66-01, PAGE 405, STEP (15). THIS CONDITION WAS CORRECTED AND THE DOOR WAS CLOSED TO ATTEMPT SLIDE DEPLOYMENT AGAIN.  ON THE SECOND ATTEMPT, THE SLIDE PACK DID RELEASE FROM THE DOOR AND DROPPED PROPERLY, HOWEVER IT DID NOT INFLATE.  THE IN-CABIN FA OPERATING THE DOOR ATTEMPTED TO MANUALLY INFLATE 2L72 4F4  FRTA1NM    E3NE                 
             20081210     CE  2008       12         10         2008FA0000851    120081023G326012707332        WARNING SYSTEM                          CESSNA210   210N        2073453CE                                                               LANDING GEAR    MALFUNCTIONED   B      H   DEACTIVATE SYST/CIRCUITS                                                                        N  FALSE WARNING                                                                 CRCRUISE         1                      SW996621A78                     21063559    821099R                     WHILE FLYING THROUGH RAIN IN IFR CONDITIONS, THE LANDING GEAR NOT DOWN/LOCKED WARNING HORN SOUNDED FALSELY EVEN THOUGH THROTTLE WAS NOT RETARDED TO DESCENT CONFIGURATION.  AIRCREW PULLED WARNING HORN CIRCUIT BREAKER TO TEMPORARILY CANCEL THE HORN WHICH ALSO DEACTIVATES THE NORMAL FUNCTION OF THE STALL/GEAR WARNING SYSTEM.  THE HORN IS VERY LOUD INTERFERING WITH ATC COMMUNICATIONS DURING A CRITICAL PHASE OF FLIGHT.  TROUBLESHOOTING REVEALED THE THROTTLE SWITCH INPUT ON THE DUAL WARNING UNIT IS HYPERSENSITIVE TO A HIGH RESISTANCE GROUND, I.E.  MOISTURE ACCUMULATION AT THE THROTTLE SWITCH TERMINAL.                                                                                                                      1H71 3O      3A21                         
             20081210     SO  2008       12         10         2008FA0000852    220081129G8550ES48109         OIL FILTER                              CESSNA172   172A        2072404CE  CONT  O300  O300D       17022SO                              ENGINE          RUPTURED        P      E   ENGINE SHUTDOWN                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      SW997830T2    2                 47430                                   ON 11/26/2008, APPROXIMATELY 1 MINUTE AFTER START-UP THE OIL FILTER RUPTURED RESULTING IN MASSIVE LOSS OF ENGINE OIL.  THE OIL FILTER WAS THE LAST OF FOUR THAT WERE PURCHASED ON 10/05/2006.  THE ENGINE WAS SHUT DOWN UPON NOTICE OF LOW OIL PRESSURE AND HAS BEEN DETERMINED TO BE UNHARMED BY THE LOCAL AP MECHANIC.                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A12    E253                 
             20081210     CE  2008       12         10         2008FA0000853    120081130G2421ASG120001       ALTERNATOR                              CESSNA303   T303        2073820CE                                                               ENGINE          SHORTED         D      HD  DEACTIVATE SYST/CIRCUITSRETURN TO BLOCK                                                         BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  TXTAXI/GRND HDL  1                      SW99303ET149                    T30300036   246242      840184          HAVE HAD MULTIPLE FAILURES, BOTH IN FLIGHT AND DURING MAINTENANCE GROUND OPERATIONS.  HOURS ON FAILED ALTERNATORS RANGE FROM AS LOW AS 30 TO A MAXIMUM OF 220 HOURS TIME IN SERVICE.  THE ONE COMMON FACTOR IN ALL FAILURES HAS BEEN THE DISCOVERY OF LOOSE HEX HEAD CASE BOLTS INSTALLED AND SAFETY WIRED BY MANUFACTURER.  THIS PROBLEM IS NOT RESTRICTED TO ONE SIDE ONLY, BOTH ENGINES DRIVE THE SAME ALTERNATOR WITH SAME PART NUMBER.                                                                                                                                                                                                                                                                                                     1L72 3O      A34CE                        
             20081219     GL  2008       12         19         2008FA0000854    220081201G720023038229        SPUR GEAR                               BELL  206   OH58A       1181579SW  ALLSN 250C  250C20C     03013GL                              ENGINE          BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99306HP                       7120794     AE405466                    GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229.  SHEARED IN HALF, PRODUCING METAL IN OIL.  WHEN TECHNICIAN DISASSEMBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H2SW    E4CE                 
             20081219         2008       12         19         2008FA0000855    220081201G721023038229        SPUR GEAR                               BELL  206   OH58A       1181579SW                                                               GEARBOX         SHEARED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99306HP1954 162               7120794                                 GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL.  WHEN TECHNICIAN DISASSEMBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U      H2SW                         
             20081202     CE  2008       12         2          2008FA0000856    120081124G3230SM50D7          RELAY                                   BEECH 33    F33A        1151425CE                                                               LANDING GEAR    INTERMITTENT    B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP078252T184                    CE1545                                  PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION.  THE GEAR FAILED TO RETRACT, 3-4 MINUTES LATER THE PILOT REPORTED THE GEAR CAME UP ON ITS OWN.  PILOT THEN PUT THE GEAR IN THE DOWN POSITION AND RETURNED TO BASE.  PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O      3A15                         
             20081203     EA  2008       12         3          2008FA0000857    220080314G7414                SHAFT                                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              MAGNETO         BROKEN          B  ZF7RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP079126M110        07071657    2816104     RL1306439A                  ROTATING MAGNET SHAFT BROKE IN HALF.  BROKE DIRECTLY BELOW WHERE THE ROTOR CAM GOES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A13    E274                 
             20081202     GL  2008       12         2          2008FA0000858    220081118G7412106149504       EXCITER                                 BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              POWERPLANT      INTERMITTENT    B  BJFRO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      EA23739NM                       51124                                   ENGINE HAD AN INTERMITTENT DELAYED LIGHTOFF CAUSING HOT STARTS.  REPLACING THE IGNITION EXCITER CORRECTED THE PROBLEM. THE DEFECTIVE EXCITER WAS FOUND TO HAVE A LOOSE STUD WHERE THE INPUT VOLTAGE IS APPLIED.  SUSPECT THIS WAS CAUSING A LOW OUTPUT VOLTAGE.  IT APPEARS THE NUT ON THE STUD WAS OVERTORQUED DURING INSTALLATION, CAUSING THE STUD TO LOOSEN.  (K)                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E1GL                 
             20081202     CE  2008       12         2          2008FA0000859    120081113G3211                SUPPORT                                 CESSNA414   414A        2075907CE                                                               TRUNNION        CRACKED         B  E5WRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21901BA6946                   414A0232                                ON THE FWD TRUNNION SUPPORT, A CRACK WAS LOCATED ON THE LT AND RT SIDES. EDDY CURRENT INSP USED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O      A7CE                         
             20081203     SO  2008       12         3          2008FA0000860    120081118G324016405700        BRAKE DISC                              PIPER PA23  PA23250     7102308SO                                                               RT MLG          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0963954238                    277854085                               THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .5 INCH FROM THE OUTER CIRCUMFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISK. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O      1A10                         
             20081203     GL  2008       12         3          2008FA0000861    120081117G801114924LS         STARTER                                 DIAMONDA40  DA40        2990002GL  LYC   O360  IO360M1A         NE                              ENGINE          BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW03203US                       40903       L3393551E                   STARTER HOUSING BROKE AT FRONT CASTING BREAKING OFF FRONT MOTOR SHAFT SUPPORT BEARING WHICH ALLOWED STARTER SHAFT TO DROP DOWN PREVENTING POSITIVE ENGAGEMENT OF STARTER TO FLY WHEEL.  CONVERSATION WITH AIRCRAFT MFG NOTED THIS IS NOT AN ISOLATED INCIDENT AND THERE ARE DEFECTS IN THE FRONT CASTINGS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA47CE   1E10                 
             20081202     CE  2008       12         2          2008FA0000862    120081114G574310112002584     BRACKET                                 BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6*        52043EA                              RT MLG SUPPORT  CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA2740R                         BC07                                    A 1.4 INCH LONG CRACK WAS FOUND IN THE RT MLG DRAG BRACE SUPPORT BRACKET DURING INSPECTION.  DURING THE REMOVAL OF THE PART (2) ADDITIONAL CRACKS 1.4 INCH LONG WERE FOUND AROUND 4 FASTENERS WHERE THE BRACKET ATTACHES TO THE MAIN SPAR WEB.  WHEN INSTALLED, THE AREA AROUND THESE 4 FASTENERS IS OBSCURED BY THE MLG DRAG BRACE FWD ATTACH FITTING (PN 50-120201-5).  THE PART WAS REPLACED WITH A NEW BRACKET.  NO CRACKS WERE FOUND N THE SPAR WEB.  SUSPECT CRACKS CAUSED BY FATIGUE AND OR HARD LANDINGS.  (K)                                                                                                                                                                                                                          1L72 4T3  T  A24CE   E2NE                 
             20081203     EA  2008       12         3          2008FA0000863    120081110G6320269A510351      PINION GEAR                             SCWZER269   269D        8059501EA  ALLSN 250C  250C20W          NE                              TRANSMISSION    WORN            D  BS2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW17297BJ           S0005       0029        CAE845042                   DURING SHUT-DOWN, PILOTS REPORTED CLUNKING NOISE.  UPON FURTHER INSPECTION, NOISE WAS LOCATED AT UPPER PULLEY SPRAG CLUTCH AREA.  REMOVED UPPER PULLEY AND FOUND M/R TRANSMISSION INPUT PINION (PN:269A5103-51) WORN EXCESSIVELY DUE TO LOOSE AFT PINION NUT.  PROBABLE CAUSE OF AFT PINION NUT LOOSENING IS SB DB-019 (CORROSION PROTECTION OF INPUT PINION SPLINES).  POSSIBLE EXCESSIVE APPLICATION OF ZINC-CHROMATE PRIMER TO INPUT PINION CAUSED IMPROPER CLAMP-UP DURING TORQUING PROCEDURE.  (K)                                                                                                                                                                                                                                         1G71 3U3  U0 4H12    E4CE                 
             20081203     CE  2008       12         3          2008FA0000864    120081108G323315232003        ACTUATOR                                CESSNA500   560CESSNA   2076750CE                                                               NLG             LEAKING         B  FZPRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM1145KB                        5600191                                 ON NOV 6, THE ACFT EXPERIENCED FOR THE THIRD TIME, LANDING GEAR RETRACTION PROBLEMS.  IT WAS FLOWN TO REPAIR STATION FOR LANDING GEAR MAINTENANCE.  THE ACFT WAS JACKED, AND A GEAR RETRACT CHECK WAS ABLE TO DUPLICATE THE INFLIGHT PROBLEM.  TROUBLESHOOTING REVEALED THAT THE NOSE GEAR ACTUATOR WAS LEAKING INTERNALLY, FILLING THE NITROGEN EMERGENCY EXTENSION SYSTEM WITH HYD FLUID.  THIS RESULTED IN A HYDRAULIC LOCK DURING THE NORMAL LANDING GEAR RETRACTION CYCLE, THUS PREVENTING ONE OR MORE MAIN LANDING GEAR FROM ACHIEVING AN UP AND LOCKED POSITION.  APPROX 1.5 PINTS OF HYD FLUID WERE DRAINED FROM THE EMERGENCY EXTENSION LINES AND COMPONENTS. ADDITIONALLY, THE EMERGENCY EXTENSION BREATHER CHECK VALVE PN P48-389 HAD2L72 4F    RTA22CE                        
             20081203     CE  2008       12         3          2008FA0000865    120080920G6220368200119       ROD                                     BEECH 33    F33A        1151425CE                                                               NOSE GEAR       BENT            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA056431X2333                   CE1005                                  ON LANDING, PILOT OBSERVED THREE GREEN LIGHTS.  ON TOUCHDOWN AND ROLL OUT NOSE GEAR COLLAPSED INTO NOSE GEAR WHEEL WELL.  UPON INVESTIGATION GEAR TRANSMISSION WAS DOWN AND LOCKED.  NOSE GEAR ROD END BENT FWD SIDE OF AFT RETRACT ROD.  NOSE GEAR ROD END CAN BE ACCESSED IN WHEEL WELL AFT RT SIDE ATTACHED TO KEEL UNDER SHIELD.  THIS IS A GOOD PLACE TO LOOK AT HARD LANDINGS AND DURING ANNUAL INSPECTIONS.  PILOT INTERVIEWED AND SAID HE DID NOT HAVE HARD LANDING OR PORPOISE ACFT.  PN OF ROD IS 36-820011-9, PN FOR ROD END IS ANDE5-323.  (K)                                                                                                                                                                                      1L71 3O      3A15                         
             20081203     CE  2008       12         3          2008FA0000866    120081117G712026510088        MOUNT                                   CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE                              ENGINE          CRACKED         B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059750B12988                  208B0100    PCE17240                    THE CENTER ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA                 
             20081202     CE  2008       12         2          2008FA0000867    120081117G712026510127        MOUNT                                   CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE                              LT ENGINE       CRACKED         B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW059750B                       208B0100                                THE LT ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3T3  T  A37CE   E4EA                 
             20081202     SO  2008       12         2          2008FA0000868    120081121G534067271800        BRACKET                                 PIPER PA28  PA28R201    7102816SO                                                               NLG ACTUATOR    CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW994142N16129                  2837012                                 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED.  PROBABLE CAUSE IS TIME IN SERVICE.  CHANGE AT A REASONABLE TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O      2A13                         
             20081202     SO  2008       12         2          2008FA0000869    120081029G534067271800        BRACKET                                 PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              NLG ACTUATOR    CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW994155G                       2837017                                 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED.  PROBABLE CAUSE IS TIME IN SERVICE.  CHANGE AT A REASONABLE TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O  2A13    1E10                 
             20081203         2008       12         3          2008FA0000870    120081028G8011774960A4        STARTER                                                                                                                                 ENGINE          MISMANUFACTURED D  SI3RO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      EA63     425                                                            FOUND BAFFLES INSTALLED INCORRECTLY, INCORRECT HOUSING INSTALLED AND VARIOUS INTERNAL PARTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
             20081203     CE  2008       12         3          2008FA0000871    120081101G5100                SPAR                                    BEECH 18    H18         1151012CE  PWA   R985  R985*       52008NE                              UNKNOWN         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW076GJ                         BA633                                   HAVE JUST HAD THE SPAR X-RAY ACCOMPLISHED IAW AD75-27-09 R2.  UPON REVIEW OF THE X-RAYS IT WAS DETERMINED THAT THERE WAS A CRACK.  IT SEEMS THIS CRACK OF A VERY SIMILAR ONE WAS PREVIOUSLY REPAIRED AND THAT REPAIR IS IN QUESTION AS WELL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3R3  R  A765    5E1                  
             20081202     EA  2008       12         2          2008FA0000874    220081118G7414M3820           DISTRIBUTOR                             PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA                              MAGNETO         DAMAGED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW9963954881                    277854085                               SUBJECT PART APPEARS TO HAVE NOT RETAINED ITS LOWER BEARING THAT SUPPORTS THE DISTRIBUTOR GEAR.  THE PART WAS FOUND TO BE BURNED AND THE BEARING HOLE MISSING THE BEARING AND ROUNDED OUT WHICH CAUSED THE MAGNETO TO FAIL AND PREVENTED ENGINE STARTUP.  JUST PRIOR TO THIS, ENGINE STARTUP HAD BEEN DIFFICULT, HOWEVER, MAG DROP AND PERFORMANCE WERE NORMAL.  (K)                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  1A10    1E4                  
             20081203     SO  2008       12         3          2008FA0000875    120081118G324016405700        BRAKE DISC                              PIPER PA23  PA23250     7102308SO                                                               MLG             CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW9963954277                    277854085                               THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .75 INCH FROM THE OUTER CIRCUMFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISC.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      1A10                         
             20081202     CE  2008       12         2          2008FA0000876    120081117G32406364106         BRAKE CABLE                             CESSNA525   525B        2076616CE                                                               LT BRAKE        FAILED          B  JVGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0992MA                        525B0048                                LET ACFT SIT OVER NIGHT WITH PARKING BRAKE APPLIED AND FOUND BRAKE SYS TO STILL HAVE 700 PSI IN BRAKE SYS.  RELEASED PARKING BRAKE AND FOUND THAT THE LT BRAKE STILL HAD 160 PSI RESIDUAL PRESSURE AND RT SIDE HAD ZERO RESIDUAL PRESSURE.  VERIFIED RT WHEEL ASSY WOULD ROTATE, CHECK LT SIDE AND LT WHEEL ASSY WOULD NOT ROTATE.  INSPECTED INSIDE PORTION OF BRAKE METERING VALVE IN CABIN AND NOTICED THAT THE LT ACTUATION CABLE CLEVIS END COULD GET HOOKED ON EDGE OF CABLE BALL END.  WHEN THAT HAPPENS 160 PSI REMAINS ON LT BRAKE.  WHEN CABLE IS POSITIONED PROPERLY LT BRAKE HAS NO RESIDUAL PRESSURE ON GAUGE AND LT WHEEL ROTATES.  OBTAINED NEW AFT BRAKE CABLES FROM MFG AND MODIFIED IAW ENGINEERING CO NR 525-1495.  REMOVED O1L72 4F    RTA1WI                         
             20081203         2008       12         3          2008FA0000877    420081120G2360                GROUND STUD                             CESSNA510   510         2076617CE  PWC   PW615 PW615FA     52282NE                              RT WING         LOOSE           B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09551WH                       5100055                                 ADJACENT TO RT WING ACCESS PANEL 623DB THERE IS A GROUNDING POINT TO GROUND THE ACFT DURING FUELING OR WHILE PERFORMING MAINTENANCE.  IN AN ATTEMPT TO GROUND TO ACFT IN ORDER TO PERFORM MAINT, WE FOUND THE GROUNDING JACK MISSING.  PANEL 632DB WAS REMOVED AND UPON FURTHER INSP THE PARTS WERE FOUND FLOATING AROUND INSIDE THIS AY WHICH ALSO HOUSES THE AILERON CONTROL SECTOR.  SOME TYPE OF SAFETY SHOULD BE INCLUDED ON GROUNDING JACK TO PREVENT IT FROM COMING APART AND POTENTIALLY JAMMING THE AILERON.  (K)                                                                                                                                                                                                                      1L72 4F4  FRTA00014WIE00073EN             
             20081217     SW  2008       12         17         2008FA0000878    120081127G3220                TUBE                                    MOONEYM20   M20F        5870214SW                                                               NLG             BROKEN          G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      SO116829V3000                   220012                                  PILOT STATED THAT HE HEARD A LOUD SOUND  DURING THE TAKE OFF ROLL OFF OF A GRASS STRIP AND THE ACFT BEGAN TO "HANDLE DIFFERENTLY".  HE CONTINUED TO ACCELERATE BRIEFLY AND THEN DECIDED TO ABORT THE TAKE-OFF.  INCIDENT INVESTIGATION FOUND ACFT ON ITS NOSE WITH THE NOSE LANDING GEAR FOLDED BACK UNDERNEATH THE ACFT.  INSPECTION REVEALED THAT THE TUBING OF THE NLG LEG ASSEMBLY WAS BROKEN.  THERE WERE POSSIBLE STRESS FRACTURES AT THE WELS POINTS ON BOTH SIDES OF THE STRUCTURE.                                                                                                                                                                                                                                                     1L71 3O      2A3                          
             20090107     SW  2009       1          7          2008FA0000879    120081127G3220540004501       LEG ASSY                                MOONEYM20   M20F        5870214SW                                                               NLG             BROKEN          D      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      SO11V68293000                   220012                                  PILOT STATED THAT HE HEARD A LOUD NOISE DURING TAKE-OFF AND THAT THE AIRCRAFT BEGAN TO "HANDLE DIFFERENTLY." HE CONTINUED TO ACCELERATE BRIEFLY, LIFTED OFF AND THEN DECIDED TO ABORT THE TAKEOFF.  THE ACFT CAME TO REST ON ITS NOSE WITH THE NOSE L/G FOLDED BACK BENEATH THE ACFT. INSP OF THE NOSE GEAR REVEALED THAT THE NLG LEG TUBING HAD BROKEN AT THE WELD POINTS ON THE UPPER ENDS OF THE TUBING. CLOSER INVESTIGATION SHOWED POSSIBLE FATIGUE CRACKS AT THE FWD PORTION OF THE WELDED JOINTS.                                                                                                                                                                                                                                        1L71 3O      2A3                          
             20090106     GL  2009       1          6          2008FA0000880    120081122G793112635002        SENSOR                                  CIRRUSSR    SR20        05628AJGL  CONT  IO360 IO360*      17025CE                              OIL SYSTEM      DEFECTIVE       G      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      SO19212LV678  678               1547        360009                      SENSOR PRODUCED A FALSE HIGH OIL PRESSURE INDICATION DURING ACFT APPROACH TO AIRPORT. PROBABLE CAUSE WAS INTERNAL FAILURE, RECOMMENDATIONS TO PREVENT RECURRENCE ARE UNAVAILABLE, AS THE FREQUENCY OF THIS TYPE OF OCCURRENCE HAS BEEN VERY LOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ONTA00009CHE1CE                 
             20090106     SO  2009       1          6          2008FA0000881    220081209G74144310            MAGNETO                                 DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              LEFT            FAILED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP23293DC22   22                C0193       824561R                     MAGNETO, PN 4310, SN 08063188. DELIVERED NEW WITH APPLICABLE SB, SB3-08A. AFTER 21.6 HOURS COMPLIANCE WITH SB3-08A FOUND PART FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  ONTTA4CH   E7SO                 
             20090107     SW  2009       1          7          2008FA0000882    120081209G2710473501          BELLCRANK                               GULSTM112   112A        7630302SW                                                               ZONE 500        MISREPAIRED     D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP191420J1560 1560              420                                     EXCESSIVE AILERONS T/E FREE PLAY. SUSPECTED AIL SYS CUMULATIVE WEAR. UPON FURTHER CLOSE VISUAL INSP, FOUND AILERONS BELLCRANK ASSY, PIVOT BRG HSG SECURED TO BELLCRANK PLATE WITH (3 EACH) BLIND FASTENERS. PROTRUDING HEAD FASTENERS WERE FOUND LOOSE AND EXHIBITING BLACK POWDERY RESIDUE AT FASTENER'S PROTRUDING HEAD PERIMETER, SUGGESTING BRINELLING IS OCCURRING ABOUT UPSET FASTENER HOLLOW SHANK OD AND BELLCRANK PLATE FASTENER HOLE SURFACE. ALL SUBJECT FASTENER'S DRIVE STEEL PINS WERE FOUND NOT TO HAVE LIBERATED FROM FASTENER HOLLOW SHANK ID.  REPLACED PIVOT BEARING HOUSING ASSY P/N MS20218-1 DUE WORN AND REINSTALLED/SECURED SAME WITH SOLID AD RIVETS. COMMANDER IPC PAGE 2-195 ITEMS 25, 27 BELLCRANK ASSY PIVOT BEARIN1L71 3O      A12SO                        
             20090107     EA  2009       1          7          2008FA0000884    220081210G7322229164          DISCHARGE TUBE                          CESSNA172   172P        2072436CE  LYC   O320  O320*       41508EA                              FUEL PUMP       LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW9964204669  669               75534                                   DURING 100 HR INSP, FOUND THE PUMP DISCHARGE TUBE ON A MA-4SPA LOOSE. THIS IS THE THIRD SUCH FIND. OTHER ACFT HAVE HAD THE PUMP DISCHARGE TUBE MISSING AND FOUND AT THE BOTTOM OF THE CARB AIRBOX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E274                 
             20090107     CE  2009       1          7          2008FA0000885    120081211G325066426438        JAM-NUT                                 CESSNA560   560XL       2076702CE                                                               STEERING BUNGEE LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      SO13669TT740                    560XL5684                               DURING ALL FLIGHT REGIMES (CLIMB/CRUISE/DESCENT) CREW FELT RESISTANCE WHEN LT RUDDER PEDAL WAS DEPRESSED. NO CHANGE IN FEEL WITH LANDING GEAR POSITION (UP OR DOWN). ON GROUND RESISTANCE COULD NOT BE FELT, HOWEVER ACFT WOULD PULL LT WHILE TAXIING. INITIAL FINDINGS REVEALED THE JAM NUT ON THE NOSE STEERING BUNGEE ASSY HAD BACKED OFF AND THE CLEVIS END OF THE BUNGEE HAD TURNED INTERNALLY CAUSING THE OVERALL LENGTH TO INCREASE. NOT KNOWING WHAT IF ANY INTERNAL DAMAGE WAS DONE TO THE SPRING, THE DECISION WAS MADE TO REPLACE THE NOSE STEERING BUNGEE WITH A NEW UNIT. THE BUNGEE WAS INSTALLED AND THE AND THE STEERING SYS WAS RIGGED IAW AMM. ACFT WAS RELEASED FOR TEST FLIGHT, NO RESISTANCE WAS FELT IN THE RUDDER, AND DU2L72 4F    RTA22CE                        
             20090106     NE  2009       1          6          2008FA0000886    220081111G8530                CYLINDER                                PIPER PA31  PA31310     7103103SO  LYC   O540  TIO540J2B        NE  HARTZLHCC2Y HCC2Y*      GL  ENGINE          SEPARATED       D      K   NONE                                                                                            RE PARTIAL RPM/PWR LOSS      VIBRATION/BUFFET                                    CRCRUISE         1                      EA09801JK     787               318012014   L528061A    FH998           PILOT NOTED REDUCTION OF PWR, THEN VIBRATION IN CRUISE FLIGHT. VISUAL INSP REVEALED NR1 CYL INTAKE TUBE SEPARATED FROM SUMP INLET AND WEDGED APPROX 1 INCH AFT OF INLET.  FUEL INJECTOR LINE BROKE AT INJECTOR. BOTTOM (2) CYL HOLD DOWN STUDS BROKE AND (1) BOTTOM, (1) TOP HOLD DOWN NUTS BACKED OFF. SUSPECT CYL HEAD SEPARATION.                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ORTA20SO   E14EA   5  CP920     
             20081217         2008       12         17         2008FA0000887    420081028G2211GFC700          AUTOPILOT SYS                           CESSNA510   510         2076617CE                                                                               MALFUNCTIONED   P      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         APAPPROACH       1                      SW99510AZ20                     510124                                  WHEN A DISCREPENCY BETWEEN THE NAVDATA DATABASE & ACTUAL IMPLEMENTATION OF A LOCALIZER NAVAID, GFC700 WILL NOT INTERCEPT & TRACK LOCALIZER SIGNAL CORRECTLY.  IT EITHER FLIES THROUGH COURSE OR WILL ACTIVATE LOC MODE & IMMEDIATELY TURN OFF COURSE.  AFCS APPEARS TO REFERENCE LOCALIZER COURSE FROM DATABASE RATHER THAN SELECTED COURSE ON HSI.  FIRST DISCOVERED ON ASE LOC DME A APPROACH LAST APRIL.  NAVDATA HAD INCORRECT COURSE OF 120 FOR I-PKN LOCALIZER.  I-PKN TUNED, HSI WOULD AUTO-SET COURSE TO 120.  THE PILOT CAN TURN THE NEEDLE TO THE CORRECT COURSE OF 300, AND THE HSI WILL PROVIDE CORRECT SENSING.  AUTOPILOT WILL NOT CAPTURE THAT COURSE & WILL FLY RIGHT THROUGH LOCALIZER TOWARD TERRAIN.  MANUFACTURERS AND FAA/N1L72 4F    RTA00014WI                     
             20081219     CE  2008       12         19         2008FA0000888    120081215G2751DT2RA7          SWITCH                                  BEECH 90    C90         1152913CE                                                               TE FLAPS        BENT            B      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW99964G 7692                   LJ1007                                  THE UP TRAVEL SWITCH ON THE RT FLAP FAILED TO TRIP UPON FLAP RETRACTION.  THIS CAUSED THE FLAP MOTOR TO CONTINUE TO RUN ALTHOUGH THE FLAP WAS ALREADY FULLY RETRACTED.  THE MOTOR OVERHEATED AND STARTED GENERATING SMOKE.  THE ACFT WAS ON THE GROUND, TAXIING FOR TAKEOFF WHEN THIS WAS DISCOVERED.  THE ACFT RETURNED TO THE RAMP.  UPON INSPECTION BY MX STAFF IT WAS DISCOVERED THAT THE ARM ON THE FLAP UP TRAVEL SWITCH WAS BENT (CAUSE UNKNOWN.)  THIS PREVENTED THE SWITCH FROM CLOSING.  A CAREFUL EXAMINATION OF THE AREA COULD NOT REVEAL WHAT CAUSED THE ARM TO BEND.  SPECULATION IS THAT PERHAPS IT WAS RELATED TO ICE OR FOD DEBRIS.                                                                                            1L72 3T      3A20                         
             20081230     EU  2008       12         30         2008FA0000889    120081119G65204639306038      PINION GEAR                             BOLKMS105   BO105LSA3   5626020EU                                                               TAIL ROTOR DRIVEDEFORMED        W  ZF6YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33315LS                       2033                                    THE MAIN TRANSMISSION WAS DELIVERED FOR OVERHAUL.  THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING.  CHIP DETECTOR AND OIL FILTER WERE CLEAN.  AT THE BEGINNING OF THE DISASSEMBLY, MECHANIC NOTED THAT THE TAILROTOR DRIVE DIDNT MOVE WHEN THE INPUT FLANGE WAS TURNED.  AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND THE ASSOCIATED ROLLER BEARINGS WAS DETECTED.  THE BEARING WAS CRACKED AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED. THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX.  (K)                                                                                                                                                                                          1G72 3U      H3AU                         
             20081222     EU  2008       12         22         2008FA0000890    120081119G65004639306006      BEARING                                 BOLKMS105   BO105LSA3   5626020EU                                                               TAIL ROTOR DRIVECRACKED         W  ZF6YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33315LS603                    2033                                    MAIN TRANSMISSION WAS DELIVERED FOR O/H. THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING.  CHIP DETECTOR AND OIL FILTER WERE CLEAN.  AT THE BEGINNING OF THE DISASSEMBLY, THE MECHANIC NOTED THAT THE TAILROTOR DRIVE DID NOT MOVE WHEN THE INPUT FLANGE WAS TURNED.  AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND THE ASSOCIATED ROLLER BEARINGS WERE DETECTED.  THE BEARING WAS CRACKED, AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED.  THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX. (K)                                                                                                                                                                                             1G72 3U      H3AU                         
             20081229     EU  2008       12         29         2008FA0000891    120081111G6310                COUPLING                                AEROSPAS355 AS355N      8680818EU  TMECA ARRIUSARRIUS1A         NE                              MAINTRANSMISSIONMISINSTALLED    D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NE05766AM                       5601        21252126                    ENGINE TO MAIN TRANS COUPLINGS FOUND TO BE INCORRECTLY ASSEMBLED.  THS WAS FOUND DURING A PRE-FLIGHT INSP.  THE COUPLINGS HAVE NOW BEEN ASSEMBLED CORRECTLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G72 3U3  URTH11GU   E34NE                
             20081230     CE  2008       12         30         2008FA0000892    120081001G2510                CLEVIS PIN                              CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              PILOT SEAT      MISSING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW9975743                       17267920                                CLEVIS PIN THAT SUPPORTS BACK OF PILOTS SEAT WORN OVER .2500 THRU.  THIS PIN SLIDES IN A CURVED PORTION OF THE LOWER FRAME OF THE SEAT.  PROBLEM PARTS ARE CLEVIS PINS THAT SUPPORT THE SEAT BACK ON NR (2), (BELLCRANK).  THE BELLCRANK IS WELL WORN IN THE CURVED SECTION AND FILING INTO THE CLEVIS PIN.  IF THIS PIN FAILS, THE BACK-REST OF THE SEAT WILL PARTIALLY DROP OFF OR POSSIBLY COMPLETELY DROP OFF WITH OBVIOUS RESULTS.  MY SOLUTION WILL BE TO ROUND-OFF THE CURVE IN THE BACK OF THE BELLCRANK, SMOOTH IT WELL AND MAKE A STEEL ROLLER TO FIT INTO THE AREA OF THE CLEVIS PIN WHERE THE BELLCRANK WEARS ON IT.   JUST PERIODICALLY REPLACING THE CLEVIS PIN SHOULD SUFFICE UNLESS THE COARSE WEARING IN THE BELLCRANK IS OBSER1H71 3O3  ONT3A12    E274                 
             20090107     NE  2009       1          7          2008FA0000893    220081217G73142PR600CWT       PUMP                                    DOUG  DC3   C47         3021461WP  PWA   R1830 R183092     52020NE                              LT ENGINE FUEL  LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CE19982Z 163  163               12947       438796                      LT ENG FUEL PUMP DEVELOPED LEAK THROUGH THE BLEED HOLE IN A PLUG INSTALLED ON THE PRESSURE ADJUSTMENT PORTION OF THE PUMP.  SYS WAS PRESSURIZED BY THE ELECTRIC FUEL PRESSURE BOOST PUMP AND A LEAK WAS DETERMINED TO BE APPROX (1) DROP PER SECOND AT A PRESSURE OF 18 PSI.                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4R4  R  A669    5E4                  
             20090106     SO  2009       1          6          2008FA0000894    220081215G73146467683A1       PUMP                                    CESSNA210   T210N       2073456CE  CONT  O520  TSIO520*    17040SO                              ENGINE          SHEARED         E  WNHAC   ABORTED TAKEOFF                                                                                 Y  ENGINE STOPPAGE                                                               TOTAKEOFF        1                      WP255340Y2    2                 21064173    289648                      ON SECOND TEST FLIGHT AFTER FACTORY REBUILT ENG INSTALLATION, ENG QUIT DURING TAKEOFF, JUST AFTER LIFTOFF, ALTITUDE LESS THAN 5 FT AGL. PILOT LANDED ACFT AND ROLLED OUT WITHOUT FURTHER INCIDENT. DURING THIS EVENT, PILOT REPORTED THAT AT TAKEOFF INITIATION, POWER SETTINGS WERE " NORMAL, SMOOTH, AND HEALTHY." AT ACFT ROTATION (65-70 KNOTS), PILOT REPORTED MANIFOLD PRESSURE AND FUEL FLOW DECREASED STEADILY AS ENGINE FALTERED, THEN QUIT COMPLETELY.  TOWED ACFT TO MAINT AREA. ENG PROMPTLY RESTARTED BUT QUICKLY FALTERED. WITH PROMPT USE OF AUXILIARY FUEL PUMP ENGINE WAS ABLE TO KEEP RUNNING. INSPECTED ENG AND FOUND ENG DRIVEN FUEL PUMP DRIVE SHAFT SHEARED. CURRENTLY IN CONTACT WITH MFG ABOUT THE INCIDENT.            1H71 3O3  O  3A21    E8CE                 
             20090107     NM  2009       1          7          2008FA0000895    120081212G6310A1902           BELT            ROBSIN                  ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                              CLUTCH ASSY     DEFECTIVE       E      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      WP23558LA1968                   3153        L3771936A                   THE PILOT REPORTED A CLUTCH LIGHT COMING ON FOR MORE THAN 5 SECONDS, FOLLOWED THE PROCEDURES IN THE POH AND MADE A PRECAUTIONARY LANDING. UPON VISUAL INSP IT WAS DEFECTED THAT ONE OF THE DRIVE BELTS IN THE CLUTCH SYS HAD FAILED AND CAUSED THE CLUTCH ACTUATOR TO ENGAGE CAUSING THE CLUTCH LIGHT TO ILLUMINATE.  THERE WERE NO DAMAGES TO THE ROTORCRAFT OR ANY INJURIES TO THE PILOTS. DRIVE BELTS WHERE REPLACED AND THE ROTORCRAFT WAS RETURNED TO SERVICED.                                                                                                                                                                                                                                                                            1G71 3O3  O  H10WE   E286                 
             20090106     CE  2009       1          6          2008FA0000896    120081201G3010671440211       TUBE                                    CESSNA750   750         2076810CE                                                               ANTI-ICE SYSTEM MISMANUFACTURED C  NOZRO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      WP239NG  4141                   7500213                                 LT WING INBD HEATED LEADING EDGE AIR DISTRIBUTION TUBE PN 6714402-11 HAS AN INCOMPLETE WELD ON THE PERIPHERY OF THE FITTING.  HAD ANIT-ICE TUBE PN 671440211 WELDED IAW DWG 6714402 DWG 001.  REINSTALLED L/E AND SEALED SEAMS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4J    RTT00007WI                     
             20090107     SW  2009       1          7          2008FA0000897    120081214G6210206011135005    BOLT            BELL                    BELL  206   206L3       1182108SW                                                               MAIN ROTOR      DEBONDED        D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      EA23739NM12938      A298        51124                                   MAIN ROTOR BLADE BOLT LWR PLUG, PN 206-011-137-001, FELL OUT ON ENG SHUTDOWN WHEN ROTOR RPM DROPPED BELOW 40 PERCENT. THIS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HAVE HAD ADEQUATE ADHESIVE APPLIED.                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U      H2SW                         
             20090105     CE  2009       1          5          2008FA0000898    120081222G5311                FRAME                                   LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              FUSELAGE        CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19244LJ4361                   35A244                                  WHILE INSPECTING THE LT AFT FUEL TANK STRUCTURE, DUE TO LIGHTENING DAMAGE EVENT,  FOUND THE FOAM INSULATION WATER SOAKED, AND CAUSING SERIOUS  CORROSION IN OUTER FLANGE OF AFT PRESSURE BULKHEAD AND SURROUNDING STRUCTURE. THE  HOLE IN THE LT OUTER PRESSURE BULKHEAD FLANGE, WHERE HOT AIR PIPE PENETRATES FLANGE HAD SEVERE INTERGRANULAR CORROSION OCCURRING ,  AND AREA WAS VERY WET.                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  F  A10CE   E6WE                 
             20090106     EA  2009       1          6          2008FA0000899    220081016G852013B21431        CRANKSHAFT                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                              ENGINE          BROKEN          B  YYBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL036478P                       15285025                                THE ENGINE WAS REMOVED DUE TO ABNORMAL NOISE AND ROUGHNESS, UPON TEARDOWN INSP, FOUND THE CRANKSHAFT BROKEN IN TWO AT THE CENTER MAIN BEARING AREA.  THE CTR MAIN BRG SHOWED DISTRESS, BUT DID NOT INDICATE ANY LACK OF LUBRICATION.  THE CRANKCASE HAD SLIGHT DAMAGE IN THE BEARING RETAINING AREA.  THIS ENGINE HAD BEEN FACTORY OVERHAULED ON 7/14/06, AND PRESENTLY HAS 961.3 HOURS SINCE OVERHAUL.  THE LOG BOOK DID NOT INDICATE ANY PROP STRIKE OR PROPELLER CHANGE.  (K)                                                                                                                                                                                                                                                                1H71 3O3  ONT3A19    E223                 
             20090105     CE  2009       1          5          2008FA0000900    120081009G323399121204        ACTUATOR                                CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                              NOSE GEAR       BYPASSING       B  BGSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA213FA                         5600023                                 HYD LOW LEVEL LIGHT CAME ON AFTER TAKEOFF AND REMAINED ON UNTIL FLAPS AND GEAR WERE SELECTED UP AND LOCKED.  REPLACED NOSE GEAR ACTUATOR DUE TO INTERNALLY BYPASSING INTO THE EMERGENCY SIDE FOR GEAR EXTENSION.  SENT NOSE GEAR ACTUATOR OUT FOR OVERHAUL AND INSTALLED AN OVERHAULED ACTUATOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA22CE   E25EA                
             20090106     CE  2009       1          6          2008FA0000901    120081202G3230390814101007    DAMPER                                  RAYTHN390   390         7150030CE                                                               BUMPER MISSING  WRONG PART      B  E81RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL03100WE                       RB45                                    INVESTIGATED PILOT REPORT OF MLG DOORS NOT CLOSING INDICATION FOLLOWING GEAR RETRACTION.  FOUND RUBBER BUMPER MISSING FROM LT MAIN GEAR UPLOCK DAMPER ASSY,  LT MAIN GEAR UPLOCK DAMPER ASSY CAUSING LT MN GEAR UPLOCK HOOK NOT TO RESET AND ENGAGE ROLLER FOLLOWING GEAR RETRACTION DUE TO EXCESSIVE UP-TRAVEL OF LT MAIN GEAR.  REPLACED LT MAIN GEAR UPLOCK DAMPER WITH SERVICEABLE, SUPERSEDING PN 3908141010013 DAMPER ASSY.  LANDING GEAR RETRACTION/ EXTENSION OPERATIONS NORMAL.                                                                                                                                                                                                                                                        1L72 3F    RTA00010WI                     
             20090102     WP  2009       1          2          2008FA0000902    120081208G7500369H8407        TUBE                                    HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              BLEED AIR       UNSERVICEABLE   B  BS2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW178617F272                    570128D     CAE830481                   THIS DEFECT WAS DETECTED DURING TROUBLESHOOTING FOR AN ENGINE PWR PROBLEM.  THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUCTION WITH AN STC FROM ENG PWR PROBLEM.  THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUNCTION WITH AN STC, PC SAFETY VALVE KIT SE5511NM.  AFTER THE DEFECT WAS DETECTED, THE KIT FOR SAFETY VALVES WAS REMOVED AND THE ORIGINAL HARD LINE WAS RE-INSTALLED.  THE STC KIT WILL NOT FIT IN THE ENGINE COMPARTMENT WITHOUT THE USE OF THE FLEX BLEED AIR TUBE.  THESE TUBE ASSY ARE VERY SENSITIVE TO BREAKAGE AFTER THEY HAVE TAKEN A SET.  (K)                                                                                                                                                                       1G71 3U3  U  H3WE    E4CE                 
             20090105     CE  2009       1          5          2008FA0000903    120081208G3244850108PR        TUBE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  TIRE            LEAKING         C  MT9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW051120N                       208B0386    PCE19211    980220          THE PILOT REPORTED A FLAT TIRE.  MAINT FOUND AN INNER-TUBE LEAKING WITH NO APPARENT DAMAGE TO THE TIRE.  THE TUBE WAS REPLACED WITH A NEW TUBE.  SIX DAYS LATER THE SAME PILOT IN CHARGE OF THE SAME ACFT REPORTED THE SAME TIRE FLAT.  MX AGAIN FOUND THE INNER TUBE FLAT WITH NO APPARENT SIGNS OF DAMAGE TO THE TIRE.  A THROUGH INSP OF THE INNER-TUBE SHOWED PIECES OF WHAT APPEAR TO BE PAPER TOWEL EMBEDDED INTO THE RUBBER.  THE FIRST TUBE WAS THEN INSPECTED WHICH SHOWED THE SAME MATERIAL EMBEDDED INTO IT.  AN INSPECTION OF NEW STOCK SPARE INNER TUBES OF THIS TYPE THAT HAD NEVER BEEN ISSUED OUT, FOUND THE SAME MATERIAL EMBEDDED IN THEM ALONG WITH, IN SOME CASES, PIECES OF HARD MATERIAL.  (K)                            1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20090106     NE  2009       1          6          2008FA0000904    220081209G725030606266        TURBINE BLADES                          AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73140    29001NE                              NR 2 ENGINE     DAMAGED         B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09373RS                       0259                                    THE THIRD STAGE LP TURBINE DISK ON NR 2 ENG HAD A BLADE (PN 30606901) BREAK IN FLIGHT DAMAGING THE EXHAUST NOZZLE AND THE AFTER BODY OF THE ENG.  THE BLADES OF THE TURBINE DISK HAD A 2500 HOUR MPI REQUIRED EDDY CURRENT INSP COMPLETED AT 2458.6 TSN AND 1979 CSN.  THE NEXT INSP APPEARS TO BE DUE IN 216.5 HRS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                       2L73 4F4  F  A46EU   E1NM                 
             20090106     SO  2009       1          6          2008FA0000905    220081201G8530ECC712CN        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              ENGINE          SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA25333ZX                       TH1739                                  NR 1 CYL FAILED, HEAD SEPARATED FROM BARREL.  ALL CYL, WERE OVERHAULED,  5/12/2004,  817.5 HRS AGO.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  3A16    E3SO                 
             20090106     EU  2009       1          6          2008FA0000906    120081122G8120                SEAL            GARRTT                  SOCATATB20  TB21        8680697EU  LYC   O540  TIO540AB1A  41533EA                              TURBOCHARGER    FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE092802W           SCR0175     1137        L921061A                    PILOT REPORTED THAT ENGINE LOST OIL PRESSURE AT AN ALTITUDE OF 8000 FT ABOUT 14 MILES WEST OF MUNICIPAL AIRPORT.  HE WAS ABLE TO MAKE AIRPORT AND SHUTDOWN THE ENGINE AFTER COMING TO A STOP ON THE RUNWAY.  REPORTED THAT WHEN THE ACFT LEFT, THE OIL WAS CHECKED AND WAS INDICATING 10 QTS. ON THE DIPSTICK.  THE ENGINE WAS EXAMINED WITH A REP FROM FAA PRESENT.  IT WAS DETERMINED AFTER EXAMINING THE TURBOCHARGER AREA THAT THE INTERNAL SEALS TO TURBO MUST HAVE FAILED, CAUSING OIL TO ENTER BOTH INTAKE SYS AND HOT SIDE OF TURBO.  SCAVENGE PORT OF TURBO WAS INSPECTED AND FOUND TO BE UNOBSTRUCTED.  OIL WAS DRAINED FROM SUMP, YIELD WAS 1.5 QTS.  (K)                                                                            1L71 3O3  ORTA51EU   E14EA                
             20090106     SO  2009       1          6          2008FA0000907    220081208G8530539491          CYLINDER                                BEECH 33    35C33       1151408CE  CONT  O470  IO470K      17026SO  MCAULY2A36C 2A36C23     GL  ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP07653P 295                    CD991       818526R     652989          ANNUAL INSP REVEALED A LARGE QUANITY OF VERY BLACK OIL RUNNING DOWN THE ENGINE MOUNT LEG AND AIRFRAME STRUCTURE.  FURTHER INVESTIGATION FOUND THE LEAK TO ORIGINATE AT THE HEAD TO BARREL CONNECTIONS OF CYLINDERS NR 1, AND NR 3.  COMPRESSION CHECK USING AN INPUT PRESSURE OF 80 PSI AND LEAK DETECTING SOLUTION SHOWED AIR TO BE LEAKING FROM THE CYLINDER HEAD TO BARREL CONNECTION.  CYLINDERS WERE REMOVED AND INSPECTED BUT IT COULD NOT BE CONFIRMED IF CRACK EXISTED OR IF LEAK WAS THROUGH THE THREADS.  THE LOW TIME ON NEW MFG CYLINDERS INDICATES THAT THE PROBLEM COULD BE IN THE MFG PROCESS.  NOTE: ENGINE WAS REBUILT / ZERO TIMED USING NEW CYLINCERS ON 5/20/2001.  (K)                                                     1L71 3O3  O  3A15    3E1     5  CP880     
             20090107     SO  2009       1          7          2008FA0000908    220080810G8520510384          CONNECTING ROD                          PIPER J3    J3C65       7100510SO  CONT  C90   C908F       17009SO                              ENGINE          FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1542080                       14307       4077788                     NR 1 CONNECTING ROD FAILED IN FLT, OFF-AIRPORT LANDING AND SUBSTANTIAL DAMAGE.   CONNECTING ROD FAILED SLIGHTLY ABOVE CRANKSHAFT; ROD CAP STILL BOLTED & SAFETIED TO DAMAGED & SEPARATED LOWER PORTION OF CONNECTING ROD.  DAMAGE TO CRANKCASE, CRANKSHAFT, & ADDITIONAL INTERNAL ENGINE COMPONENTS SUGGEST A FAILED/ SPUN NR 1 ROD BEARING, RESULTING IN A LOSS OF LUBRICATION TO NR 1 CONNECTING ROD. EXCESSIVE HEAT BUILDUP, AND SUBSEQUENT SEIZURE TO THE CRANKSHAFT JOURNAL AND ROD FAILURE.   THE OIL SCREEN MINIMAL CONTAMINATION, INDICATING A SHORT OPERATING TIME BETWEEN PART FAILURE AND ENGINE SHUTDOWN.  ENG EXHAUST WAS CLEAN AND THERE WAS NO EVIDENCE OF EXTERNAL OIL LEAKAGE ON THE ENG; REGARDLESS, OIL QUANTITY IN THE ACFT 1H71 3O3  O  A691    E252                 
             20090106     GL  2009       1          6          2008FA0000909    220080825G726123038229        SEPARATOR                                                                  ALLSN 250C  T63A720     03002GL                              AIR/OIL         BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                                        AE405466                    CUSTOMER HAD CHIP LIGHT INDICATING METAL GENERATION IN ENG.  INVESTIGATION/ DISASSEMBLY REVEALED THE AIR OIL SEPARATOR GEAR WAS BROKEN AT  GEARFACE TO SHAFT LOCATION (WHERE THE 16 DRILLED HOLES CONVERGE AT GEAR CTR). THIS IS THE 4TH OR 5TH AIR OIL SEPARATOR GEAR I`VE SEEN BROKEN LIKE THIS IN 7-8 YEARS.  WHEN THE GEAR BREAKS, IT GENERATES METAL BUT DOESN`T FAIL IN OPERATION, BUT THEN THE GEARBOX IS OPENED THE GEAR COMES OUT IN TWO PIECES. (THE GEAR IS SUPPORTED BY A BEARING ON EITHER END AND IN OPERATION THE BROKEN GEAR IS HELD TOGETHER BY THE SANDWICH FIT CREATED BY THE GEARBOX IT OPERATES IN).  THE PROBABLE CAUSE FOR THE REPEATED FAILURES IS POSSIBLY THE DESIGN.  THE GEAR HAS 16 HOLES DRILLED INTO IT AND THEY        3  U          E4CE                 
             20090107     CE  2009       1          7          2008FA0000910    120081226G7120AN721           BOLT                                    CESSNA500   550         2076604CE                                                               ENGINE MOUNT    INCORRECT       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05649WM500                    42030                                   DURING UNSCHEDULED MAINT THE ENG WAS REMOVED FROM THE MOUNTS, (1) ENG MOUNT HAD THE HELICOIL PULL OUT OF THE CASTING NECESSITATING REPLACEMENT OF THE MOUNT. IT WAS ALSO DISCOVERED THAT ALL OF THE ENGINE MOUNT BOLTS WERE OF THE INCORRECT PN.  ALL OF THE BOLTS INSTALLED (AN7-21) WERE DRILLED FOR COTTER PINS RATHER THAN THE BOLTS (AN7-21A) NOT DRILLED FOR A COTTER PIN THAT ARE CALLED OUT IN THE PARTS BOOK. THERE WERE NO LOG ENTRIES FOUND INDICATING THAT THE ENG HAD BEEN REMOVED SINCE INSTALLATION AT THE FACTORY.                                                                                                                                                                                                              1L72 4F      A22CE                        
             20090106     CE  2009       1          6          2008FA0000911    120081201G3230HMX5FG          ROD END                                 CESSNA310   310R        2074245CE  CONT  O520  IO520M      17032SO                              LT MLG          CRACKED         C      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      GL1777RG 12579                  310R0636                                PILOT REPORTED NO LT GEAR DOWN LIGHT AND ALSO HEARD A LOUD BANG WHEN GEAR WAS RETRACTED.  PILOT DID SEVERAL FLYBYS FOR MECHANICS ON GROUND, GEAR APPEARED TO BE DOWN.  PILOT LANDED WITHOUT INCIDENT AND STOPPED ON RUNWAY. GEAR WAS NOT COMPLETELY LOCKED.  GEAR WAS SECURED AND ACFT WAS TAXIED TO MAINT.  WHEN PLACED ON JACKS, THE ROD END (HEIM END) ON THE IB LT MAIN GEAR PUSH PULL TUBE WAS FOUND TO HAVE THE BALL PULLED OUT OF THE ROD END.  ROD END APPEARED TO HAVE A SMALL CRACKED WHERE IT FAILED.  NOTE: ACFT HAD BEEN LANDED GEAR UP JAN O2.  (K)                                                                                                                                                                               1L72 3O3  O  3A10    E5CE                 
             20090106     CE  2009       1          6          2008FA0000912    120081201G7400                IGNITION SYS                            CESSNA182   182C        2072708CE  CONT  O470  O470L       17026SO                              EGNINE          DEFECTIVE       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL158595T                       52495       6944670LR                   ENG RUNS ROUGH. ENG MISFIRES. HISTORY: 2/25/2004; TACH 487.1 - REPLACED LT AND RT MAGNETOS.  ACFT RUN UP CHECKED OUT OK.  4/26/2004 TACH 508 - CHECKED TIMING.  05/11/2005 (NO TACH) - TROUBLESHOOTING ROUGH ENGINE.  REMOVED INTAKE MANIFOLD AND FLAT SAND FLANGES AND REMOVE DENTS.  REPLACE ALL INTAKE FLANGE GASKETS AND HOSES.  PRESSURE TEST INTAKE MANIFOLD.  REMOVE AND REPAIR MA4-5 CARB.  RUNUP OK.  8/16/2007 TACH 542.7 - CHECK MAG TO ENG TIMING.  RUN-UP AND LEAK CHECK OK.  SOLUTION; TACH 573.8 USED DAIL INDICATOR AND FOUND THAT UTILIZING TIMING MARKS RESULTS IN 20+ DEGREE RETARDED IGNITION.  USED DIAL INDICATOR TO SET PROPER TIMING AND ENGINES PERFORMS AS IT SHOULD.  (K)                                            1H71 3O3  ONT3A13    E273                 
             20090102     EU  2009       1          2          2008FA0000917    120081217G2435                BEARING                                 UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              STARTER GEN     UNSERVICEABLE   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07451F            1781        1124                                    PILOT COMPLAINED OF A SEVERE ENGINE VIBRATION AND HOWLING NOISE EMANATING FROM THE ENGINE AREA, DURING ALL PHASES OF ENGINE OPERATION.  THE STARTER WAS REPLACED AND THE VIBRATION CEASED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 3U3  UNCR0001RD E34NE                
             20090106     NE  2009       1          6          2008FA0000918    220081215G7414103827991       MAGNETO                                 MOONEYM20   M20J        5870219SW  LYC   O360  IO360A3B6D  41828NE                              ENGINE          MALFUNCTIONED   B  C41RO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO13201TC                       240173      L1710951AC                  STARTED THE ACFT NORMALLY, TAXIED FROM HANGAR TO THE SELF-SERVE FUEL PUMP AND SHUTDOWN.  FUELED ACFT.  ATTEMPTED TO START THE ACFT AFTER FUELING.  THE ENG TURNED OVER NORMALLY, BUT DID NOT FIRE.  TROUBLESHOOTING REVEALED NO SPARK OUTPUT FROM THE MAGNETO.  SENT MAGNETO OUT FOR REPAIR MAGNETO SHOP DETERMINED THE MAGNET HAD SLIPPED ON THE SHAFT.  A NEW MAGNETO WAS INSTALLED IN THE ACFT.  ENGINE TT: 5345.1; TSO 132.6.  THIS MAGNETO WAS INSTALLED AT THE ENGINE OVERHAUL AS AN OVERHAULED EXCHANGE UNIT.  PROBABLE CAUSE/ RECOMMENDATIONS TO PREVENT RECURRENCE; NO ADDITIONAL INSP REQUIREMENTS ARE RECOMMENDED. A FAILURE SO SOON AFTER OVERHAUL SUGGESTS A DEFECT IN THE PARTS OR A FAILURE IN THE OVERHAUL PROCESS.  THE LARGEST1L71 3O3  O  2A3     1E10                 
             20090107     CE  2009       1          7          2008FA0000919    120081210G571152221003        SPAR                                    CESSNA402   402B        207590PCE  CONT  O520  TSIO520EB   17040SO  MCAULY3AF32C3AF32C87    GL  LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13141MC10940                  402B0547                                DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRACKS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH WITH THE 2 LOWER HOLES  CONTINUING INTO THE ACCESS HOLE.  CRACKS WERE ALSO AT THE 7 AND 5 O, CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RIGN AND NUT PLATES ON THE OPPOSITE SIDE.  THESE CRACKS WENT THROUGH THE SCREW HOLES AND EXTENDED UP T 2+ INCHES.  THE CRACKS WERE OBSERVED 2671 HOURS AFTER THE MAIN SPAR CAP MODIFICATION.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT.  ALL HAVE THE MOD.  IT IS NOT KNOWN IF TH1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20090106     CE  2009       1          6          2008FA0000920    120081216G323312810016        ACTUATOR                                CESSNA172   172RG       2072438CE                                                               RT MLG          CRACKED         D  JU8SO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL259423D1940                   172RG0285                               ON 7/08/2008, RT MLG NOT FULLY RETRACTED REPORTED BY ATC.  THE PILOTS NOTICED THE RT MLG WAS NOT FULLY RETRACTED.  THE LANDING GEAR WAS THEN EXTENDED, A DOWN AND LOCKED IND FOR GEAR WAS REPORTED.  THE RT MLG ACTUATOR BODY (DATE STAMP OF AUG 21, 2001.) WAS FOUND CRACKED AT THE FWD BOLT HOLE ATTACH POINT.  THE CRACK ALLOWED THE ACTUATOR SECTOR GEAR AND PISTON TO BECOME MISALIGNED.  ACTUATOR SECTOR GEAR PN 988200202 AND PISTON ASSY PN 98820041 WERE FOUND TO BE DAMAGED.  THIS ACTUATOR BODY WAS REPLACED WITH A NEW PART IAW SEB 01-2 R1 ON 10-11-2001 AT AN TT OF 5180.2.  IT WOULD BE POSSIBLE FOR THIS DAMAGE TO PREVENT THE GEAR FROM TRAVELING TO THE FULL DOWN AND LOCKED POSITION RESULTING IN LOSS OF ACFT CONTROL DURING1H71 3O      3A17                         
             20090106     CE  2009       1          6          2008FA0000921    120081210G5711522210003       SPAR                                    CESSNA402   402B        207590PCE  CONT  O520  TSIO520EB   17040SO  MCAULY3AF32C3AF32C87    GL  LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13402CA12660                  402B0842                                DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRACKS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH.  CRACKS WERE ALSO AT THE 7 AND 5 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RING AND NUT PLATES OF THE OPPOSITE SIDE.  THESE CRACKS WENT THROUGH THE SCREW HOLES AND EXTENDED UP TO 1.5 INCH.  THE CRACKS WERE OBSERVED 1600 HOURS AFTER THE MAIN SPAR CAP MODIFICATIONS.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT.  ALL HAVE THE MOD.  IT IS NOT KNOWN IF THERE IS ANY CORROLATION.  (K)                            1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20090106     CE  2009       1          6          2008FA0000922    120081210G571152221003        SPAR                                    CESSNA402   402B        207590PCE  CONT  O520  TSIO520NB   17040SO                              LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13106GP16296                  402B1235                                DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRACKS WERE AT THE 11,2,5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH.  CRACKS WERE ALSO AT THE 7 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RING AND NUT PLATES ON THE OPPOSITE SIDE.  THIS CRACK WENT THROUGH THE SCREW HOLE AND EXTENDED 1 INCH. THE CRACKS WERE OBSERVED 930 HOURS AFTER THE MAIN SPAR CAP MODIFICATION.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT.  ALL HAVE THE MOD.  IT IS NOT KNOW IF THERE IS ANY CORROLATION.  (K)                                                   1L72 3O3  O  A7CE    E8CE                 
             20090106     EU  2009       1          6          2008FA0000923    120081212G322225UN561         AXLE                                    BRAERODH125 HS125700A   4230170EU                                                               NLG             WORN            B  X42RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03483FG521                    257094                                  CONTINUOUS NOSE GEAR VIBRATIONS UPON LANDING.  TEARDOWN AND INSPECTION OF NOSE GEAR AXLE BARREL ASSY REVEALED THE NOSE AXLE TO BE WORN BEYOND LIMITATIONS.  (2) .005" GROOVES WORN INTO AXLE.  (1) ON EACH SIDE WHERE THE AXLE BARREL COVER PLATE SEALS ARE LOCATED.  NO WEAR IS PERMITTED AS PER THE OVERHAUL MANUAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A3EU                         
             20090102     CE  2009       1          2          2008FA0000924    120081201G2710500000066       CONTROL CABLE                           CESSNA421   421B        2076014CE                                                               LT AILERON CABLEFRAYED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13                            68494                                   TT ON CABLES UNKNOWN SUSPECT ORIGINAL.  FOUND LT AFT AILERON CABLE FRAYED AT WING STATION 58.94 THE PULLEY WAS FROZEN.  INSPECTED REST OF SYSTEM NO DEFECTS FOUND.  ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29.  THE PULLEYS AT THIS STATION WERE TURNING FREELY.  WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSO AT WING STATION 87.29, ALSO REQUIRING CABLE REPLACEMENT.  SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WING STATION 106.79 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA TO INSPECT, AND THE AILEREONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKE1L72 3O      A7CE                         
             20090107     CE  2009       1          7          2008FA0000925    120081215G28206017001079      VENT LINE                               BEECH 58    58          1152740CE                                                               RT WING         LEAKING         B  EHHRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA17584RF1933                   TH2012                                  FOUND RT WING FUEL VENT CONSTANTLY LEAKING FUEL.  OPENED RT WING TIP FILLER CAP AND BLEW AIR THROUGH THE VENT SYSTEM AND BUBBLES WERE SEEN IN THE LOWER END OF THE FUEL TANK WHERE THE VENT TUBE PASSES THROUGH THE FUEL TANK BULKHEAD.  USED ACFT MM TO FABRICATE A HOLE IN FUEL CELL TO GAIN ACCESS TO THE LEAKING TUBE AND APPLIED PRO SEAL TO SEAL THE TUBE TO THE BUSHING WHERE THE LEAK WAS OBSERVED.  (K)                                                                                                                                                                                                                                                                                                                                1L72 3O      3A16                         
             20090102     CE  2009       1          2          2008FA0000926    120081201G2710500000067       CONTROL CABLE                           CESSNA421   421B        2076014CE                                                               LT AILERON      FRAYED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13                            68494                                   TT ON CABLES UNKNOWN SUSPECT ORIGINAL. FOUND LT AFT AILERON CABLE FRAYED AT WING STA 59 THE PULLEY WAS FROZEN.  INSPECTED REST OF SYSTEM NO DEFECTS FOUND. ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29. THE PULLEYS AT THIS STATION WERE TURNING FREELY.  WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSOAT WING STATION 87.29, ALSO REQUIRING CABLE REPLACEMENT.  SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WING STA 106.79 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA TO INSPECT, AND THE AILERONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKEN IN SMALL LOCAL1L72 3O      A7CE                         
             20090120     SO  2009       1          20         2008FA0000927    220081201G8500S1053E16T       HOSE                                    CESSNA150   A150K       2071824CE  CONT  O200  O200*       17020SO                              AIR INTAKE      CONTAMINATED    D      A   UNSCHED LANDING                                                                                 RY PARTIAL RPM/PWR LOSS      ENGINE STOPPAGE                                     CLCLIMB          1                      AL058450M                       A15000150                               BEGAN NORMAL LANDING CHECK LIST INCLUDING CHECKING CARB HEAT.  AFTER PULLING CARB HEAT ON, ENGINE DIED.  TURNED OFF CARB HEAT & ENGINE RESTARTED ON ITS OWN WITHOUT PILOT INPUTS.  CONTINUED PATTERN & GRADUALLY REAPPLIED CARB HEAT ON BASE AND FINAL.  ON SHORT FINAL ENGINE DIED & PILOT GLIDED TO A SAFE TOUCHDOWN.  ABLE TO RESTART ENGINE & TAXI BACK TO PARKING WITHOUT INCIDENT.  FOUND THE SCAT HOSE COMING FROM FRONT BAFFLE DOWN TO FRONT OF EXHAUST SHROUD HAD FILLED WITH WATER.                                                                                                                                                                                                                                                   1H71 3O3  O  3A19    E252                 
             20090106     EA  2009       1          6          2008FA0000928    220081230G741466LC35SDNP      MAGNETO                                 CESSNA206   206H        2073301CE  LYC   O540  TIO540AJ1A       EA                              RIGHT           DAMAGED         B      O   OTHER                                                                                           O  OTHER                                                                         UKUNKNOWN        1                      NM075880K594                    T20608581   L12173                      RT MAGNETO INTERMITTENT, MAGNETO STAYED HOT AND SOME TIMES IT WILL NOT HAVE ANY CURRENT GOING THROUGH.  IF PROPELLER WAS MOVE IT WILL FIRE RT UP, AFTER REMOVED RT MAGNETO AND OPENED FOUND THAT THAT COIL HAS MELTED MOST OF THE GEARS AND CASING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ORTA4CE    E14EA                
             20090106     CE  2009       1          6          2009F00002       120081221G561010138402522     WINDSHIELD                              BEECH 90    C90         1152913CE                                                               COCKPIT         CRACKED         G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CE01736EA                       LJ1478                                  ACFT LEVELED OFF AT 20,000 FT AFTER APPROX 45 MIN OF FLIGHT, THERE WAS A SUDDEN BANG, AND CO-PILOTS WINDSHIELD INNER PANE SPIDER WEB CRACKED.  FLT CREW DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3T      3A20                         
             20090107     CE  2009       1          7          2009FA0000000    120081208G325066429438        BUNGEE CYLINDER                         CESSNA560   560XL       2076702CE                                                               MLG             MALFUNCTIONED   C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13669TT740                    5684                                    DURING TAXI, ACFT PULLS TO LT UNCOMMANDED. ALSO INFLIGHT CREW HEARD A RUBBING NOISE FROM THE LT RUDDER PEDAL. CREW ALSO MENTIONED IN FLIGHT THE RUDDER PEDALS FEEL LIKE THERE IS SOMETHING RUBBING.  FOUND JAM NUT ON STEERING BUNGEE HAD LOOSENED, ALLOWING THE ROD END TO EXTEND ON THE PUSH ROD. REPLACED STEERING BUNGEE WITH NEW UNIT AND RE-RIGGED THE NOSE STEERING. IN THE MAINT PROCEDURE 32-50-00 THERE IS NO MENTION OF SECURING THIS ADJUSTMENT (ROD END BEARING, JAM NUT, PUSH ROD) SUCH AS LOCK TITE 732, OR POSSIBLY EVEN BETTER A WAY TO SAFETY THE JAM NUT. REPLACEMENT OF BUNGEE AND RIGGING THE NOSE STEERING FIXED THE PROBLEM.  WORK WAS ACCOMPLISHED AT THE MFG SERVICE CENTER.                                           2L72 4F    RTA22CE                        
             20090108     SW  2009       1          8          2009FA0000002    120081218G3233EM411514        ACTUATOR                                ECLIPSEA500 ECLIPSEEA5003350000SW                                                               RT MLG          FAULTY          C      K   NONE                                                                                            J  WARNING INDICATION                                                            CLCLIMB          1                      SO19929KD134                    000240                                  DURING CLIMB THE RT MLG FAILED TO FULLY RETRACT.  GEAR INTRANSIT INDICATED.  ON SELECTION OF LANDING GEAR DOWN, RT MLG FAILED TO EXTEND.  ALTERNATE GEAR EXTENSION USED AND GEAR EXTENDED FULLY AND "DOWN AND LOCKED" INDICATED.  NORMAL LANDING ACCOMPLISHED.  ON JACKS THE RT MLG WOULD ONLY RETRACT ABOUT 45 DEGREES AND WOULD NOT EXTEND FULLY WHEN SELECTED.  RT MLG ACTUATOR REPLACED AND SYSTEM FUNCTION TESTED NORMAL.                                                                                                                                                                                                                                                                                                                  1L72 4J    RTA00002AC                     
             20090120     SO  2009       1          20         2009FA0000004    220081210G8520                BOLT                                    CESSNA210   T210L       2073449CE  CONT  O520  TSIO520H    17040SO                              ENGINE          FAILED          G      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      GL159426K                       21060572    506240                      DURING CLIMB TO CRUISE ENGINE MADE A LOUD NOISE AND QUIT RUNNING, ENGINE REMAINED WINDMILLING TO LANDING.  VISUAL INSP REVEALED NR 3 CYLINDER ROD BOLT MISSING, ROD CAP EXITED ENG THRU UPPER CASE, NO EVIDENCE OF OIL STARVATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  3A21    E8CE                 
             20090120     CE  2009       1          20         2009FA0000005    120081223G2910S217840095A     HOSE                                    CESSNA210   T210M       2073451CE  CONT  O520  TSIO520*    17040SO                              HYD SYSTEM      BURST           B      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  LDLANDING        1                      SO05732UR3658                   21061789                                RT NLG DOOR ACTUATOR HOSE FAILED CAUSING COMPLETE HYD FLUID LOSS . RESULTING IN LT MAIN GEAR NOT ABLE TO BE FULLY EXTENDED TO DOWN AND LOCKED POSITION.  ACFT MADE EMERGENCY LANDING WITH LT MAIN GEAR PARTIALLY EXTENDED.  MINOR DAMAGE.  FAILED HOSE APPEARS TO BE ORIGINAL INSTALLED NEW IN 1977.                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E8CE                 
             20090130     CE  2009       1          30         2009FA0000007    120081215G323335810080602     ACTUATOR                                BEECH 35    A35         1151504CE                                                               MLG             FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      GL15473AB     368               D1578                                   INTERNAL FAILURE WITHIN LANDING GEAR ACTUATOR GEARBOX. GEAR WOULD NOT CYCLE DOWN BY NORMAL OR EMERGENCY EXTENSION. EMERGENCY HANDLE WOULD NOT ENGAGE. COMPONENT WAS OVERHAULED IN 1983.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O      A777                         
             20090120     NE  2009       1          20         2009FA0000012    220081230G73212123M55P04      ECU                                     AIRBUS320   A320214     3930316EU  CFMINTCFM56 CFM565B4P        NE                              NR 2 ENGINE     FAULTY          C  VQIAA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      WP15632VA                       3155        577893                      FLIGHT 515 LAX TO JFK.  DURING CRUISE 3 ECAM WARNINGS, THRUST LEVER FAULT, CTL VALVE FAULT, AND ENG2 FADEC A FAULT.  AN ASSOCIATED LAND ASAP AMBER ECAM ADVISORY MSG ALSO APPEARED.  CREW ADVISED DISPATCH THAT THEY WERE DIVERTING TO LAS.  MX FOLLOWED THE TSM FOR THE FAULTS AND FOUND ENGINE 2 CHANNEL A NOT REPORTING DURING ECU TEST.  THE ECU WAS REPLACED AND OPS CHECKED OK PER AMM 73-21-60.  IAW THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS.  THE ACFT WAS RELOCATED BACK TO SFO.  N632VA DEPARTED LAS AT 0741Z AND ARRIVED SFO AT 0842Z.  NO FAULTS NOTED.                              2L72 4F4  FRTA28NM   E38NE                
             20090120     EU  2009       1          20         2009FA0000013    120081217G6120                CONTROL CABLE                           STBROSSD3   SD360       8100606EU                                                               RT PROPELLER    BROKEN          C  TXHAO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP13808KR                       SH3734                                  THE ACFT RT PROP CABLE BROKE.  ACFT RETURNED TO HONOLULU STATION FOR INSPECTION AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T      A41EU                        
             20090129     CE  2009       1          29         2009FA0000014    120081210G3260                ARM                                     CESSNA414   414         2075908CE                                                               DOWNLOCK        BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      GL1952CS                        4140615                                 ON LANDING, THE PILOT SELECTED THE GEAR DOWN AND NEVER GOT A GREEN DOWN AND LOCK LIGHT IN THE CABIN FOR THE RT MAIN GEAR.  THE GEAR DOWNLOCK MICRO-SWITCH ACTUATOR ARM WAS BROKEN AND WOULD NOT ACTUATE THE MICRO-SWITCH.  THESE ACTUATOR ARMS SEEM TO GET WEAK OVER TIME.  THERE WAS NO OTHER REASON FOR THE ARM TO FAIL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O    RTA7CE                         
             20090130     CE  2009       1          30         2009FA0000015    120081230G3240632750012       TUBE                                    CESSNA525   525         2076601CE                                                               BRAKE SYS       BROKEN          B  AWORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15793CJ4959                   5250021                                 DURING AN INSP, DOC 10, LANDING GEAR PNEUMATIC BRAKE SYS FUNCTIONAL CHECK ONE OF THE LINES IN THE RT LANDING GEAR WELL BLEW.  FURTHER INVESTIGATION FOUND THAT THE 6327500-12 TUBE ASSY BROKE OFF AT THE FLARE ON THE INBD END OF THE TUBE ASSY.  INSP OF THE SAME LINE ON THE LT SIDE FOUND NO DEFECTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F    RTA1WI                         
             20090129     SO  2009       1          29         2009FA0000016    220081217G8550652969          PAN                                     CESSNA414   414A        2075907CE  CONT  O550  TSIO550A    41516SO                              ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      GL15414PS                       414A0056    800653                      OIL LEAK CAME FROM CRACK IN OIL PAN.  CAUSE UNKNOWN.  ENG TSMOH 95 HRS.   CRACK/ FITTING WITH HOSE ATTACHED FOR REMOTE OIL DRAIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A7CE    E5SO                 
             20090130     WP  2009       1          30         2009FA0000017    120081223G7820C16932          MUFFLER                                 ROBSINR44   R44RAVENII  7640122WP                                                               EXHAUST SYSTEM  FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE051425K676                    10153                                   MUFFLER CAN BLOW OUT AT TAIL PIPE CONNECTION AND COLLECTOR FAILURES, BULGES AND BLOW OUTS.  WEAK MATERIAL, USE THICKER AND BETTER MATERIAL.  PEOPLE ARE GETTING SICK AND/OR BAD HEADACHES.  CO DETECTORS ARE SOUNDING OFF IF YOU HAVE ONE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O      H11NM                        
             20090128     WP  2009       1          28         2009FA0000018    120081223G7810C1695           COLLECTOR                               ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              IB AREA 3 TO 1  DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE05417PK497                    11480                                   EXHAUST COLLECTORS 3 TO 1 TYPE.  BULGES AND BLOW OUTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  H11NM   1E4                  
             20090128     CE  2009       1          28         2009FA0000020    120081224G326045A3951141      UPLOCK HOOK                             BEECH MU300 400A        1155402CE                                                               NLG             DISENGAGED      B  E81RA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL03175QS15                                                             AFTER DEPARTING, FLIGHT CREW OBSERVED RED LANDING GEAR UNSAFE LIGHT IN LANDING GEAR CONTROL HANDLE ILLUMINATED AFTER LANDING GEAR RETRACTION.  RETURNED TO DEPARTURE.  FOUND NLG UPLOCK HOOK NOT ENGAGING NOSE GEAR STRUT ASSY AS REQUIRED IAW MM 32-30-00.  LANDING GEAR RETRACT/ EXTENSION SYS FUNCTION CHECKS IAW MM 32-00-00 OK.  SUSPECT ADJUSTMENT CHANGED SLIGHTLY FROM AS-BUILT RIGGING DUE TO COMPONENTS WEARING IN, HAVE NOTED SIMILAR CONDITION PREVIOUSLY ON OTHER LOW-TIME ACFT.  (K)                                                                                                                                                                                                                                              2H72 4F    RTA16SW                        
             20090129     SO  2009       1          29         2009FA0000021    120081022G3230SE0521903XXX    BEARING                                 GULSTMG1159 GIV         3980115SO                                                               NLG             LOOSE           D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      WP19972MS                       1285                                    WHILE TAXIING ACFT, CREW REPORTED POPPING SOUND COMING FROM NOSE WHEEL WELL AND DURING RT TURNS.  FOUND NLG DRAG BRACE UPPER ATTACH VERTICAL BEARING AT FS 119, FINGER TIGHT.  INSPECTED OTHER ACFT AND FOUND SAME OCCURRENCE.  SB 157 HAS BEEN COMPLIED WITH ON 3/09/2004.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA12EA                        
             20090130     EU  2009       1          30         2009FA0000022    120081027G7921MS210435        NUT                                     HUGHES369   369FF       4470709EU  ALLSN 250C  250C30      03013GL                              COOLER BLOWER   BACKED OUT      B  GI3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP015185G                       0009F                                   OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL USE.  NUT IS A STAINLESS STEEL, SILVER PLATED, ALL METAL SELF LOCKING TYPE NUT.  THIS WAS THE 3RD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO AWARE OF ONE OTHER INCIDENT TO ANOTHER COMPANY.  WHEN THE NUT BACKS OFF IT CAUSES THE SHAFT BEARING TO GO BAD WHICH DESTROYS THE OIL COOLER BELT.  THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSION OIL TEMPERATURES.  AFTER INVESTIGATING PN, WE FOUND THAT MFG HAS BEEN USING THIS TYPE NUT FOR A LONG TIMEAND WERE UNSURE IF THE NUT CURRENTLY BEING PRODUCED ARE SUBSTANDARD.  UNIT WAS O/H. THE O/H FACILITY HAS BEEN INFORMED OF THESE INCIDENTS AND THEY ARE CURRENTLY INVESTIGATING THE1G71 3U3  U  H3WE    E1GL                 
             20090129     EA  2009       1          29         2009FA0000024    220081204G732225765463        SERVO                                   CESSNA206   206H        2073301CE  LYC   O540  IO540AC1A5       EA  MCAULY3D36C B3D36C432   GL  ENGINE          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA13137P                        2060804     L3271948E   80VSA1          FUEL SERVO LEAKED WHILE ACFT WAS PARKED OVERNIGHT.  THE MIXTURE WAS IN CUT OFF POSITION.  FLIGHT MANUAL, SEC 4, NORMAL PROCEDURES PAGE 4-23 SECURING ACFT NR 10 STATES: FUEL SELECTOR VALVE RT OR LT TO PREVENT CROSS FEEDING.  IF THE FUEL SELECTOR VALVE WAS TURNED TO OFF, THIS WOULD HAVE PREVENTED.  THERE IS A POTENTIAL FOR FUEL TO ENTER ENGINE CYLINDERS AND OIL SUMP IF THE FUEL SERVO MIXTURE CUT OFF LEAKS USING FLIGHT MANUAL PROCEDURES.  NEED TO ADDRESS: FLIGHT MANUAL PROCEDURES TO FUEL SELECTOR VALVE OFF.  (K)                                                                                                                                                                                                              1H71 3O3  ORTA4CE    1E4     5  CP58GL    
             20090130     CE  2009       1          30         2009FA0000026    120081224G3600AA3216CW        PUMP                                    BEECH 33    F33A        1151425CE  CONT  O520  IO520BB     17032SO                                              LOW PRESSURE    B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      WP078242T19                     CE1610      830201R                     PILOT REPORTED INSTRUMENT AIR PRESSURE LOW AT IDLE ON RUN UP.  ON TROUBLESHOOTING, THE MECHANIC DETERMINED THE AIR PUMP WAS NOT PRODUCING ENOUGH PRESSURE AT IDLE.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  3A15    E5CE                 
             20090130     GL  2009       1          30         2009FA0000027    120081219G779714251001        WIRE HARNESS                            CIRRUSSR    SR22        2130001GL                                                               ENG COMPARTMENT CHAFED          B  YEBRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05961AG                       0255                                    FOUND THE BLACK PLASTIC WIRE LOOM THAT HOUSES THE MAP WIRING HARNESS FWD OF THE BAFFLE TO HAVE CHAFED THROUGH THE WIRE INSULATION OF THE WIRES IN SEVERAL LOCATIONS.  THIS IS CAUSED BY THE WIRE HARNESS BEING ABLE TO MOVE INSIDE THE LOOM AND THE LOOM BEING MADE FROM A HARDER MATERIAL THAN THE  WIRE INSULATION.  INSTALL NEW WIRE HARNESS AND REMOVE THE PLASTIC LOOM.  SECURE WIRES AS NEEDED.  (K)                                                                                                                                                                                                                                                                                                                                      1L71 3O    NTA00009CH                     
             20090130     EA  2009       1          30         2009FA0000028    220081205G852011B200611SH     CRANKCASE                               PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA                              ENGINE          CRACKED         B  UC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL194149G4622 872               2843191     L3630836A                   FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  2A13    E286                 
             20090130     EA  2009       1          30         2009FA0000029    220081206G852011B200615H1     CRANKCASE                               PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA                              ENGINE          CRACKED         B  UC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL194148P6916 789               2843177     L3616236A                   FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  2A13    E286                 
             20090130     CE  2009       1          30         2009FA0000030    120081228G2497                CIRCUIT BREAKER                         LEAR  55    55LEAR      5170702CE                                                               MAIN BUSS       MALFUNCTIONED   D      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CE03242RB                       55B132                                  ACFT DEPARTED, ENROUTE WITH 2 PASSENGERS, 2 HOURS INTO FLIGHT, JUST PRIOR TO INITIAL DESCENT, ACFT EXPERIENCED A COMPLETE ELECTRICAL FAILURE AND LOSS OF PRESSURIZATION AT FL430.  FLIGHT CREW REGAINED CONTROL OF PRESSURIZATION AROUND FL330 AND RESTORED PWR TO NR 1 COMM RADIO.  ACFT DIVERTED AND MADE A VISUAL NO-FLAP APPROACH & LANDING.  ACFT OVERRAN RUNWAY APPROX 50 FT INTO MUD.  NO PASSENGERS OR CREW WERE INJURED AND ACFT HAD MINOR DAMAGE.  AFTER INITAL INSP, SUSPECT LT MAIN BUSS C/B ISSUE BUT UNABLE TO CONFIRM THIS TO BE THE PROBLEM AT THIS TIME.  ADDITIONAL INSP AND MAINT NEEDED TO CONFIRM C/B OVERLOAD.  (K)                                                                                                       2L72 4F      A10CE                        
             20090205     SO  2009       2          5          2009FA0000036    220081013G7414105005563       MAGNETO                                 CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          FAILED          D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      GL09651BS235                    1711        360237      FP4833B         FLIGHT CREW REPORTED ENGINE SPUTTERED DURING INITIAL CLIMB.  UPON INTERNAL VISUAL INSP OF LT MAGNETO, FOUND BROKEN MAGNETO SHAFT BELOW DRIVE GEAR.  ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT.  ROTATION OF STEEL SHAFT IN ALUMINUM CASTING YIELDED EXCESSIVELY RETARDED TIMING.  MAGNETO WAS "FACTORY NEW" WITH 235.4 HOURS TT AND HAS NOT BEEN OPENED PRIOR TO THIS EVENT.  A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM.  PREVIOUSLY ON 9/9/2008 AT 1112.0 HOURS AIRCRAFT TOTAL TIME, THE RIGHT MAGNETO WAS FOUND TO HAVE FAILED DURING RUN-UP CHECKS WITH THE SAME FAILURE MODE.                                                                                              1L71 3O3  ONTA00009CHE1CE    5  CP36EA    
             20090205     SO  2009       2          5          2009FA0000037    220081218G7414105005563       MAGNETO                                 CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          FAILED          D      D   RETURN TO BLOCK                                                                                 Y  ENGINE STOPPAGE                                                               TXTAXI/GRND HDL  1                      GL0970RB 351                    1653        360157      FP4526B         LT MAGNETO FAILED TO SUSTAIN ENG OPS DURING GROUND RUN-UP CHECK.  UPON INTERNAL VISUAL INSP, FOUND BROKEN MAGNETO SHAFT BELOW DRIVE GEAR.  ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT.  ROTATION OF STEEL SHAFT IN ALUMINUM CASTING YIELDED EXCESSIVELY RETARDED TIMING.  MAGNETO WAS "FACTORY NEW" WITH 350.9 HOURS TT AND HAS NOT BEEN OPENED PRIOR TO THIS EVENT.  A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM. FOR PRECAUTIONARY REASONS, THE RT MAGNETO WAS OPENED AND FOUND TO HAVE THE SAME CRACK BEGINNING.  IT WAS ALSO REPLACED WITH A "FACTORY NEW" MAGNETO OF THE SAME TYPE.                                                                                          1L71 3O3  ONTA00009CHE1CE    5  CP36EA    
             20090205         2009       2          5          2009FA0000050    220081229G7414M3458           ROTOR                                                                                                                                   MAGNETO         BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM02     1059       98100916                                            THE PILOT REPORTED THAT ON CHECKING THE RT MAGNETO THERE WAS AN EXCESSIVE RPM DROP BUT THAT THE ENGINE STILL OPERATED SMOOTHLY ON THAT MAGNETO. UPON DISASSEMBLY OF THE MAG IT WAS FOUND THAT ONE LEG OF THE CAM SLOT ON THE ROTOR SHAFT WAS COMPLETELY BROKEN OFF AT THE BOTTOM OF THE SLOT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20080313000472008031300047SO  2008       3          13         21808            120080218G49101159AC30551103  DUCT                                    GULSTMG1159 GIV         3980115SO                                                               APU INLET       CRACKED         E  CLWAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05589HM6464                   1153                                    A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA12EA                        
20080313000452008031300045SO  2008       3          13         218081153        120080218G49101159AC30551103  DUCT                                    GULSTMG1159 GIV         3980115SO                                                               APU INLET       CRACKED         E  CLWAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05589HM6464                   1153                                    A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA12EA                        
20080204001032008020400103EA  2008       2          4          22497            220080131G8530AEL14995        RETAINER        ECI                     PIPER PA18  PA18        7101802SO  LYC   O360  O360C4P     42289EA                              PUSH ROD        BROKEN          B  WS9RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM078780D                       186308      L4080536E                   ENGINE WAS DISASSEMBLED AND INSPECTED FOR PROP STRIKE INSPECTION.  DURING TEST CELL OPERATION THE TECHNICIAN NOTICED AN OIL LEAK AT THE NR4 CYLINDER.  FURTHER INSPECTION REVEALED THAT THE PUSH ROD TUBE RETAINER BROKE INSIDE THE ROCKER COVER CAUSING THE TUBE AND SEAL TO FALL OUT OF POSITION.                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  1A2     E286                 
             20080520     CE  2008       5          20         2568             120080501G3240215286          BRAKE ASSY                              CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              RT MLG          BROKEN          G      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO19330DK                       5500266                                 RT MLG BRAKE LOCK UP DURING TAXI.  AN INSP BY MAINT HAS DETERMINED THAT THE BRAKE STATOR CAME APART AND LOCKED UP THE BRAKE. THE C/A GIVEN WAS FOR THE REMOVAL AND REPLACEMENT OF THE OF THE RT WHEEL AND TIRE ASSY AND BRAKE.  A GEAR SWING WAS ALSO PERFORMED IAW MM 32-00.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F4  F  A22CE   E1NE                 
20080414000142008041400014EU  2008       4          14         325              120080325G3233D52177          HOLDER          MESSIER                 AMD   FALC20FALCON200   2730150EU                                                               ACTUATOR        BROKEN          B  GQRRO   OTHER                                                                                           K  FLUID LOSS                                                                    LDLANDING        1                      SW05                DRI76878                                            THE PACKING HOLDER BROKE IN 2 PIECES CAUSING HYDRAULIC FLUID LOSS.  THIS PART HAD BEEN MODIFIED IAW SB F200-110 TO PREVENT FUTURE FAILURES.  THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WERE MODIFIED AND IDENTIFIED SDR IAW THE SB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA7EU                         
20080204001072008020400107    2008       2          4          43385883         420080129G34608220868044      FMC                                     RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                                              MALFUNCTIONED   C      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      EA23808BL                       258634                                  UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS.  SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE THE FMS TO INSERT AND FLY AN UNINTENDED TURN.  KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 NO SOLUTION FOR FMS5000 INSTALLED IN AC.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA3EU    E6WE                 
20080402000142008040200014    2008       4          2          433858831        420080129G34618220891008      FMC                                     BEECH MU300 400A        1155402CE  GARRTTTFE731TFE7315BR        WP                                              FAULTED         C      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      EA23808BL                       RK367                                   UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS.  REF SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE THE FMS TO INSERT AND FLY AN UNINTENDED TURN.  KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 INSTALLED IN AC, NO SOLUTION FOR FMS5000 INSTALLED IN AC.                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4F4  FRTA16SW   E6WE                 
             20080710     EU  2008       7          10         5APR577Y1        120080515G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  RT MLG          BROKEN          B  5APRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65591AF1174 1174  0137        591         PR0454      KX164           DURING AN ANNUAL INSPECTION THE RIGHT MAIN WHEEL WAS REMOVED TO REPACK THE WHEEL BEARINGS WHEN IT WAS DISCOVERED THAT THE OUTBOARD BRAKE DISK ON THE RIGHT BRAKE WAS BROKEN INTO TWO PIECES.  THE BRAKE ASSEMBLY WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080710     EU  2008       7          10         5APR577Y2        120080515G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  LT MLG          BROKEN          B  5APRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65729AF1566       0599        729         PR0603      KX359           DURING ANNUAL INSPECTION THE LEFT MAIN WHEEL WAS REMOVED TO REPACK THE BEARINGS AND THE TWO OUTBOARD BRAKE DISCS ON THE LEFT BRAKE WERE FOUND TO BE BROKEN.  REMOVED AND REPLACED BRAKE ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 4T4  TRTA78EU   E26NE   5  CP210NE   
             20080710     EU  2008       7          10         5APR577Y3        120080515G3242244755          BRAKE DISC      BFGOODRICH              PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  RT MLG          BROKEN          B  5APRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65729AF1566       0593        729         PR0603      KX359           DURING ANNUAL INSPECTION RIGHT MAIN WHEEL WAS REMOVED TO REPACK BEARINGS AND THE MIDDLE BRAKE DISC WAS FOUND TO BE BROKEN.  REMOVED AND REPLACED BRAKE ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 4T4  TRTA78EU   E26NE   5  CP210NE   
20080414000162008041400016CE  2008       4          14         6001LENG         120080327G5415555415046810    ATTACH ANGLE                            CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ENGINE          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW176001L10071                  5500169                                 ENGINE NACELLE ATTACHING FITTING ANGLE REMOVED FOR CORROSION. PARTS ARE CADMIUM PLATED, BUT NOT PAINTED. ALSO DISCOVERY IMPROPER DRILL HOLES AND RIVET SET DAMAGE AROUND SEVERAL HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4F4  F  A22CE   E1NE                 
20080508000532008050800053CE  2008       5          8          6001LOXYGEN      120080423G3510176174          OXYGEN BOTTLE                           CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              NOSE            LEAKING         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW176001L                       5500169                                 INSTALLED REPAIRED EMERGENCY OXYGEN BOTTLE IN AC AND SERVICED.  WHEN BOTTLE WAS TURN ON WAS FOUND TO LEAK FROM ON-OFF VALVE.  UNIT WAS REPAIRED ON JANUARY 21,2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
             20080717     CE  2008       7          17         772AF            120080603G361013022           CHECK VALVE                             BEECH 200   B200        1152922CE                                                               BLEEDD AIR SYS  DEFECTIVE       B  VIBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13772AF5763                   BB1001                                  FLAPPERS IN BLEED AIR INLET CHECK VALVE CAME LOOSE AND CHAFED THE INSIDE OF THE HOUSING.  ONE FLAPPER CHAFED A HOLE THROUGH THE HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 4T      A24CE                        
             20080902     CE  2008       9          2          842008N341CS     120080730G3240                BRAKE                                   CESSNA500   550         2076604CE                                                               MLG             CONTAMINATED    C      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      EA63341CS                       5501106                                 THE LOW BRAKE PRESSURE AND ANTI-SKID INOP ANNUNCIATORS ILLUMINATED IN FLIGHT.  AN EMERGENCY WAS DECLARED.  DURING LANDING ROLL OUT BRAKE PRESSURE CAME BACK AND LIGHTS EXTINGUISHED.  THE BRAKES WERE BLED, A SMALL AMOUNT OF AIR NOTED.  OPERATIONAL CHECK OK.  ACFT MADE THREE TAKEOFFS AND LANDINGS WITH NO DEFECTS NOTED.  ACFT RETURNED TO SERVICE.  (S)                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F      A22CE                        
20080225000062008022500006SW  2008       2          25         901012008        120080217G5210S16206327957    DOOR                                    SKRSKYS58T  S58T        8141800SW  PWA   PT6T  PT6T6       52045EA                              MAIN            DEPARTED        L      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL23901CH1531315313             581464                                  DURING POSTFLIGHT INSP, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR MOUNTING, STRUCTURE AND DOOR OPERATION.  AC WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                             2G71 4U4  UNC1H11    E22EA                
20080319002662008031900266SW  2008       3          19         9010208          120080217G5210S16206327957    DOOR                                    SKRSKYS58T  S58T        8141800SW  PWA   PT6T  PT6T6       52045EA                              ZONE 800        DEPARTED        L      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL23901CH1531315313             581464                                  DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSPECTION OF AIRCRAFT FOUND NO DAMAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR MOUNTING, STRUCTURE AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                      2G71 4U4  UNC1H11    E22EA                
20080306002492008030600249SW  2008       3          6          901CHI0208       120080221G5210S16206327957    DOOR                                    SKRSKYS58T  S58T        8141800SW  PWA   PT6T  PT6T6       52045EA                                              DEPARTED        L      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL23901CH1531315313             581464                                  DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR MOUNTING, STRUCTURE, AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                 2G71 4U4  UNC1H11    E22EA                
             20080520     CE  2008       5          20         90XR042708       120080427G2910AS62306H0073    LINE                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              HYDRAULIC SYS   CHAFED          E  T6FAA   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      GL0990XR 342                    2090                                    DURING CRUSE FLIGHT THE PILOTS NOTED THAT MAIN HYDRAULIC SYSTEM LOST PRESSURE.  INITIATED AN UNSCHEDULED LANDING.  AFTER INSPECTION, THE LT ENGINE DRIVEN HYDRAULIC PRESSURE PUMP LINE WAS LEAKING.  THE PRESSURE LINE AND BOTH HYDRAULIC PUMPS WERE REPLACED, WITH NEW PARTS, IAW THE MM.                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTT00008WIE6WE                 
             20081209     WP  2008       12         9          AALA200810280    120081112G5320                INTERCOSTAL                             DOUG  DC9   DC983       3022083WP                                                               ZONE 100        CRACKED         A  AALAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW219401W                       53137                                   INTERCOSTAL CRACKED IN CEILING OF MID CARGO.  REPLACED INTERCOSTAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA6WE                         
             20080903     NM  2008       9          3          ABXR080225       120080729G5330                SKIN                                    BOEING767   767223      1385123NM                                                               BS 615 S34R     DAMAGED         C  ABXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23761CX                       22318                                   SCREW AND COUNTERSINK WASHER INSTALLED IN FUSELAGE SKIN OVER PREVIOUSLY BLENDED AREA AT APPROX STA 615 LONGERON STRINGER 34 RT.  DAMAGED AREA COMPLIED WITH ON PREVIOUS REPAIR.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA1NM                         
             20080903     NM  2008       9          3          ABXR080226       120080731G5330146T35111       SKIN                                    BOEING767   767223      1385123NM                                                               BS 1510 S35-36L DAMAGED         C  ABXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23761CX                       22318                                   APPROX 6 INCH CREASE AT STA 1510, LONGERON STRINGER 36-35 LT, BELOW BULK CARGO DOOR IS OUT OF LIMITS.  REPAIRED SKIN IAW B767-200 SRM 53-60-1.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA1NM                         
             20080903     NM  2008       9          3          ABXR080228       120080801G5330143T35211       SKIN                                    BOEING767   767223      1385123NM                                                               BS 544 S30-31L  DENTED          C  ABXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23761CX                       22318                                   OUTWARD DENT STA 544, STRINGER 31-30 LT REQUIRES REPAIR.  REPAIRED AREA IAW B767 SRM 53-00-01, FIGURE 201.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA1NM                         
20080404000162008040400016EA  2008       4          4          ACOR032408001    220080324G7322383493          PLUG            PREAIR      RSA5        CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              FUEL SERVO      LOOSE           B  ACORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA392162Y1618       70402806    172S9529    L3118151A                   FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-5 S/N 70402806.  DATA REFERENCED AD 2008-06-51 E, SB 08-73-01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    1E10                 
20080404000172008040400017EA  2008       4          4          ACOR032508001    220080325G7322383493          PLUG            PREAIR      RSA10ED1    CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA                              FUEL SERVO      LOOSE           B  ACORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA39377HA604        70259806    T20608499   L1183961A                   FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-10 S/N 70259806. DATA REFERENCED AD 2008-06-51 E, SB 08-73-01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ORTA4CE    E14EA                
20080410002012008041000201CE  2008       4          10         AMCR200800001    120080331G731279646           HEATING ELEMENT                         CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              RT ENGINE       FAILED          B  AMCRO   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      GL09279DV636                    070         141148                      PILOT REPORTED T2 HEATER FAIL ON RT ENGINE. FOUND T2 PROBE BAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4F4  FRTA1WI    E3GL                 
20080404000092008040400009CE  2008       4          4          B3OR20080079     120080318G3233991206313       ACTUATOR                                CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              MLG             OUT OF POSITION B  B3ORD   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      SW0326621     8                 5500593                                 AIRCREW REPORTED LANDING GEAR WARNING HORN SOUNDED AND GEAR-IN-TRANSIT INDICATOR ILLUMINATED AS AIRCRAFT WAS BEING TOWED OVER A BUMP (HANGAR THRESHOLD).  SCHEDULED FLIGHT WAS CANCELLED.  MAINTENANCE CREW WAS ABLE TO DUPLICATE EVENT BY SLIGHT ACCELERATION OF TOW VEHICLE AND OBSERVED NOSE GEAR DOWN AND LOCKED INDICATOR ALSO EXTINGUISHED IN CONJUNCTION WITH THE OTHER REPORTED INDICATIONS.  THE ACTUATOR DEFLECTION TEST IN THE AIRFRAME MM WAS ACCOMPLISHED TO DETERMINE THE SERVICEABILITY OF THE ACTUATOR'S INTERNAL DOWNLOCK MECHANISM WITH SATISFACTORY RESULTS.  DOWNLOCK INDICATOR SWITCH ADJUSTMENT COULD NOT BE VERIFIED DUE TO AN ABSENCE OF REQUIRED TESTING EQUIPMENT.  THE RECENTLY OVERHAULED ACTUATOR WAS REMOVED FOR R1L72 4F4  F  A22CE   E1NE                 
20080402000092008040200009NE  2008       4          2          B3OR2008030      220080125G73210164548240      FCU                                     SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          LEAKING         B  B3ORK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SW035204J     176               3118        9318                        FUEL CONTROL UNIT IS LEAKING FUEL FROM A DIAPHRAM BREATHER HOLE IN THE CASING.  THE LEAKING HOLE IS LOCATED BELOW AND SLIGHTLY IB OF THE PRESSURE REDUCING VALVE ATTACHED TO THE FCU.FUEL LEAK WAS INITIALLY OBSERVED AS A SEEP, PROGRESSING T  O A LOW PRESSURE STEADY TRICKLE THROUGHOUT MULTIPLE ENGINE RUNS.  ALL OTHER FUEL CONTROL FUNCTIONS WERE OPERATING NORMALLY.                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E19EU                
20080403000382008040300038EU  2008       4          3          B3OR2008046      120080213G2910704A44831141    SERVO CONTROL                           SNIAS 350   AS350B2     8680813EU                                                               LT HYD SYSTEM   LEAKING         B  B3ORK   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      SW035204J5313 2137              3118                                    ON A ROUTINE PREFLIGHT INSPECTION, THE LT HYDRAULIC ROLL CONTROL SERVO WAS DISCOVERED TO BE LEAKING HYDRAULIC FLUID AT THE PISTON SHAFT SEAL.  THE LEAK COULD NOT BE DUPLICATED DURING GROUND TESTING WITH A HYDRAULIC POWER CART IAW THE MM INSTRUCTIONS.  SUBSEQUENT FLIGHT TESTING REVEALED THE LEAK PERSISTING WITH A LEAK RATE SUSPECTED TO BE SLIGHTLY OUT OF LIMITS.  OF PARTICULAR NOTE: THE LEAK COULD ONLY BE DUPLICATED WHILE ACTUAL FLIGHT LOADS WERE INDUCED. ASIDE FROM THE LEAK, THE HYDRAULIC SERVO WAS REPORTED TO BE FUNCTIONING NORMALLY.  UNIT WAS REPLACED.                                                                                                                                                                1G71 3U      H9EU                         
             20081124     NM  2008       11         24         B62R20081106002  120081106G5411313W181338113813SPAR                                    BOEING777   777236      1385220NM                                                               NR 2 PYLON      CORRODED        B  B62RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21702BA35345                  27108                                   NR 2 ENG PYLON STRUT, AFT FAIRING HEAT SHIELD LOWER SPAR STRUCTURE, PITTING CORROSION FOUND THROUGHOUT SPAR STRUCTURE, CHORDS, FRAMES 3, 4 & 5.  EVIDENCE OF PITTING CORROSION AND HEAT DAMAGE ON LOWER SIDE OF WEBS.  REF 54-51-71 PG 6.  POSSIBLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS 1 THRU 6 WERE TORN AND WATER LOGGED, SEALS DAMAGED AND STRUT DRAIN CLOGGED.  REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01.  AD 2002-07-07 AND SB 777-54A0017 ARE RELATED TO THIS BUT HAVE NOT BEEN ACCOMPLISHED.  COMPLIANCE WITH AD WILL CORRECT CONDITION.  NOTE:  STRUT DRAIN WAS CLOGGED.  PRIMARY FIRE SEAL DAMAGED.  HEAT SHIELD SEAL DAMAGED.  SECONDARY FLUID SEAL DAMAGED.  PARTS WILL REQUIRE REPAIR OR REPLACEMENT.  2L72 4F    RTT00001SE                     
             20081124     NM  2008       11         24         B62R20081107003  120081107G5411313W3813X       FRAME                                   BOEING777   777236      1385220NM                                                               PYLON           CRACKED         B  B62RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21702BA35345                  27108                                   NR 1 & NR 2 ENG PYLON, STRUT AFT FAIRING HEAT SHIELD SPAR STRUCTURE, NR 5 FRAME P/N 313W3813-X HAS A 4.50 INCH CRACK ON THE LOWER AFT INBD CORNER.  CRACK IS IN THE SAME LOCATION ON BOTH NR 1 & NR 2 ENG PYLON FRAMES.  NR 2 ENG PYLON FRAMES NR 1 THRU NR 4, P/N'S 313W1813-X & 313W3813-X HAVE EVIDENCE OF HEAT DAMAGE AND SURFACE CORROSION.  REF SRM 54-51-71 FIGURE 4.  POSSIBLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS NR 1 THRU NR 6 (NR 2 ENG PYLON) AND NR 6 (NR 1 ENG PYLON) WERE TORN AND WATER LOGGED.  REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01 PG 623.  AD 2002-07-07 AND SB 777-54A0017 ARE RELATED TO THIS BUT HAVE NOT BEEN ACCOMPLISHED.  COMPLIANCE WITH AD WILL CORRECT CONDITION.                2L72 4F    RTT00001SE                     
             20081121     NM  2008       11         21         B62R20081121001  120081106G5320149W1129111037  INTERCOSTAL                             BOEING777   777236      1385220NM                                                               FUSELAGE        CORRODED        B  B62RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21702BA35345                  27108                                   SECTION 43 WING TO BODY FAIRING STRUCTURE LT SIDE.  INTERCOSTALS THAT SUPPORT THE FWD WING TO BODY FAIRINGS HAVE MODERATE TO SEVERE CORROSION.  SURFACE, PITTING, GALVANIC AND EXFOLIATION CORROSION ARE EVIDENT ON THE UPPER AND LOWER FLANGES COMMON TO THE NUT PLATES.  THERE IS EVIDENCE OF MOISTURE AND STANDING WATER IN THE AREA FROM STA 888 TO STA 1040 LT SIDE.  SOME INTERCOSTALS WILL REQUIRE REPAIR OR REPLACEMENT.  REF SRM 53-30-71-01-1.                                                                                                                                                                                                                                                                                        2L72 4F    RTT00001SE                     
20080225002412008022500241    2008       2          25         CA080101001      420080101G3418501177003       ACTUATOR                                CNDAIRCL600 CL6002D24   1390016EA  GE    CF34  CF348C5B1   30052NE                              STICK PUSHER    MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) ONLY ON LANDING WHEN THE PILOTS HAVE FLARED THE NOSE UP AND THE MLG HITS THE GROUND DOES THE ELEVATOR SEEM TO LOCK UP PREVENTING THE PILOTS FROM PRESSING THE NOSE DOWN TO LAND.  TOOK THE COVER OFF THE REMOVED STICK PUSHER ACTUATOR AND FOUND : 1) NOTICE THE TEETH MARKS AT THE SUPPORT POST NEXT TO THE GEAR. 2) SET SCREW WHICH IS STUCK TO THE MOTOR, THIS IS WHAT WE HEARD WHEN SHAKING THE UNIT.  3) THE SCREW WHICH WAS BOUNCING AROUND INSIDE THE BOX, LOOKS LIKE AT SOME POINT IT WAS JAMMED BETWEEN THE DRIVE GEAR AND SUPPORT POST AS EVIDENCED BY TEETH MARKS ON THE SUPPORT POST. (TC NR 20080101001)                                                                                                                     2L72 4F4  FRTA21EA   E00063EN             
20080225002502008022500250EA  2008       2          25         CA080102001      120080101G2750601R930507      FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        UNSERVICEABLE   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  LDLANDING        1                      CA                                                                      (CAN) ON APPROACH, GOING THROUGH 6500FT AT 200KTS, FLAP FAIL MESSAGE ILUMINATED WHEN SELECTED FROM 0 TO 8 DEGREES. FLAPS DID NOT MOVE, REMAINED AT 0 DEGREES. FLAPLESS LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. NOTE: NO SKEW DETECTION LIGHTS WERE ILLUMINATED. FAULT CODES RETRIEVED AND HAVE DETERMINED THAT THE NR1 FECU IS AT FAULT. FECU CHANGED IAW THE AMM 27-51-0. RIG AND FUNCTION CHECKS CARRIED OUT, NO FURTHER MESSAGES OR CODES. AIRCAFT RETURNED TO SERVICE AND NO FURTHER ISSUES NOTED. (TC NR 20080102001)                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
20080225002522008022500252CE  2008       2          25         CA080102002      120080101G57533516505035      BRACKET                                 BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCD4N3HCD4N3A     GL  TE FLAPS        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6626                                                           (CAN) FLAPS REMOVED TO INSPECT FLAP BRACKETS (HINGES) TO PREVENT A POSSIBLE FAILURE ( REFERENCE SDR 20071025007). BOTH OB FLAPS WERE WORN IN THE SAME LOCATION THAT FAILED OTHER AC. ON BOTH OB FLAPS, THE OB HINGE, IB BRACKETS P/N: 35165050-35 (LT) AND 35-165050-34 (RT), AND THE IB HINGE, OB BRACKET P/N: 35-165050-30 (LT) AND 35-165050-31 (RT). (TC NR 20080102002)                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A24CE   E4EA    5  CSTC      
20080225002562008022500256EA  2008       2          25         CA080102006      120080101G5610NP13932114      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) (RT WINDSHIELD SHATTERED IN FLIGHT).  THE WINDSHIELD WAS REMOVED AND REPLACED.   WINDSHIELD, (RT) P/N OFF: 601R33033-14 P/N ON: NP-139321-14 S/N OFF: 02277H7295 S/N ON: 07212H4821 (TC NR 20080102006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20080225002632008022500263SW  2008       2          25         CA080103007      120080103G6720NAS130410       BOLT            BELL        206001044   BELL  206   206L        1181522SW  ALLSN 250C  250C20R2         GL                              T/R PEDAL       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON INSPECTION OF THE AIRCRAFT IT WAS NOTED THAT THE (1) OF THE (3) BOLTS WAS BROKEN AND THE OTHERS SHOWED SIGNS OF CORROSION ALL (3) BOLTS WHERE REPLACED WITH NEW. (TC NR 20080103007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E4CE                 
20080225002652008022500265EA  2008       2          25         CA080104001      120080103G2750855D10096       BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        UNSERVICEABLE   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) CREW FLYING AT LEVEL 340 FOR 30 TO 40 MIN AND THE FLAP FAIL CAME ON WITH NO SELECTION, FLAPS AT 0 DEG. O FLAP LANDING. TEMP AT ALTITUDE WAS -60 DEG.  FERRIED BOTH BPSU`S REPLACED FLAPS FUNCTIONED CHECKED SER (804406 1/4/2008 06:57) (TC NR 20080104001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20080319001712008031900171EA  2008       3          19         CA080104004      120080101G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       1480110343                                                     (CAN) DURING PUSH BACK CREW SELECTED FLAPS TO 20 DEGREES AND RECEIVED A FLAP FAIL CAUTION MESSAGE. MAINT TROUBLESHOOTING LED TO REPLACEMENT OF RT BRAKE POSITION SENSOR UNIT (BPSU) AND RIGGING OF LT AND RT BPSUS. OF NOTE THE FIRST NEWLY INSTALLED RT BPSU (S/N 172, TSN 17175, TSO 4879, CYCLES 3697) HAD TO BE REPLACED AS IT FAILED THE ELECTRICAL RIGGING. (TC NR 20080104004)                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
20080225002682008022500268SW  2008       2          25         CA080104005      120080104G6220206011101109    YOKE                        206L1       BELL  206   206L1       1182107SW  ALLSN 250C  250C30P     03013GL                              M/R HUB         INCORRECT       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10379135   GDLM53264                                           (CAN) FOUND TO BE WRONG, YOKE M/R HUB ASSY, WITH THE INCORPORATION OF STC NR SH296NM, INSTALLATION OF ENGINE. CORRECT PN OF YOKE SHOULD BE 206-011-149-101. (TC NR 20080104005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H2SW    E1GL                 
20080225002692008022500269NM  2008       2          25         CA080105002      120080102G2910992236H18697    SWITCH                                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYD SYSTEM      BROKEN          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      (CAN) SDR BEING SUBMITTED DUE TO (3) OCCURRENCES OF (RUD PRESS) AND (RUD FULL PRESS) CAUTION MESSAGES OVER A PERIOD OF (4) DAYS. (1ST) EVENT OCCURRED DECEMBER 30, 2007 JUST AFTER TAKEOFF AND CAUSED AN AIR TURN BACK TO THE DEPARTURE AIRPORT. MAINT PERFORMED GROUND CHECK, THEN AN OPS CHECK IAW AMM 27-30-38 WITH NO FAULTS FOUND. (2ND) EVENT OCCURRED ON DECEMBER 31, 2007 AGAIN JUST AFTER TAKEOFF. AC RETURNED TO AIRPORT OF DEPARTURE. MAINT TROUBLESHOOTING FOUND RUDDER PRESSURE DROPS APPROXIMATELY 800-1000 PSI ON NR 1 HYD SYS. RUDDER PRESSURE REGULATOR REPLACED BUT WITH NO FIX.  NR 1 HYD SYS BLED AND ALSO NO FIX.  NR 1 LWR ACTUATOR (PN 11200-1 SN UNK) WAS REPLACED AND OPERATION CHECKED IAW AMM 27-20-01 PG 215. (3RD) 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080225002712008022500271WP  2008       2          25         CA080105003      120080101G8011BC31510040      STARTER                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       679                                                            (CAN) ENGINE WOULD NOT START, STARTER NOT ENGAGING. SERVICEABLE STARTER INSTALLED, ENGINE STARTED WITH OUT FURTHER INCIDENT. (TC NR 20080105003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
20080319001732008031900173EA  2008       3          19         CA080106001      120080104G215078279015        ACM                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              NR 1            SMOKE           W      C   ABORTED TAKEOFF                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) SMOKE IN COCKPIT AND CABIN ON T/O ROLL.  DURING T/O ROLL, SMOKE APPEARS IN THE COCKPIT AND CABIN FIRSTS ROWS. ABORTED T/O, RETURN TO BLOCKS. ACM NR1 DETERMINED TO BE THE SOURCE OF THE SMOKE. ACM NR1 DEFERRED IAW MMEL 21-51-1. (TC NR 20080106001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20080319001752008031900175EA  2008       3          19         CA080106003      120080103G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        INOPERATIVE     W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA                                                                      (CAN) FLAP FAIL MESSAGE DISPLAYED WHILE AC PARKED AT THE GATE. TROUBLESHOOTING REVEALED BRAKE AND POSITION SENSOR UNIT (BPSU) RT AND LT OUT OF LIMITS.  MAINTENANCE RIGGED LT BPSU AND REPLACED RT BPSU. (TC NR 20080106003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20080319001782008031900178EA  2008       3          19         CA080106004      120080102G3260895001          PROXIMITY SENSOR                        CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              NLG             MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, A LANDING GEAR DISAGREE WARNING MESSAGE WAS DISPLAYED. CREW CYCLED THE GEAR UNTIL SELECTED DOWN AND GEAR LOCKED DOWN INDICATION (3 GREEN LIGHTS). AC PERFORMED A TURNBACK AND LANDED UNEVENTFULLY (AFTER FUEL DUMPING FOR NOT LANDING OVERWEIGHT). TROUBLESHOOTING PINPOINTED TO THE WEIGHT OFF WHEELS NR 2 SENSOR (PX 11), BEING OFF RIGGING LIMITS. MAINT PERFORMED RE-RIGGING FOLLOWED BY A SUCCESSFUL GROUND TESTS AND AC RETURNED TO SERVICE. AIRFRAME HOURS=7855:04. CYCLES=3748. (TC NR 20080106004)                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E00063EN             
20080225002722008022500272EU  2008       2          25         CA080107001      120080107G6410355A12004008    BLADE                                   SNIAS 350   AS350B2     8680813EU  LYC   LTS101LTS101*          NE                              TAIL ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1592 1592                                                      (CAN) ON DAILY INSPECTION, A CRACK IN THE TRAILING EDGE OF THE TIP OF THE TAILROTOR ASSY WAS FOUND. THE CRACK WAS APPROX .5 INCH LONG FROM TIP OF BLADE LEADING TO T/E ON A DIAGONAL.  SUSPECT THIS CRACK, IF LEFT, WOULD HAVE CAUSED THE TRAILING EDGE CORNER APPROX .7500 OF AN INCH TO DEPART FROM TIP OF THE BLADE. THIS WAS FOUND ON BOTH BLADES ONE BLADE MORE SEVERE THAN THE OTHER. THERE WAS NO INDICATION OF A TAILROTOR IMPACT. (TC NR 20080107001)                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E5NE                 
20080225002732008022500273CE  2008       2          25         CA080107002      120080103G2497                BUSS BAR                                BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  ELECTRICAL      LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       354                                                            (CAN) WHILE PERFORMING SB 24-3871, AN EXTRANEOUS BUSS BAR WAS OBSERVED IN THE RT CB PANEL BETWEEN CB 140 AND CB 255. THIS BUSS BAR WAS ATTACHED ONLY AT ONE END AND WAS LOOSE. NOTE, THE SB ONLY REQUIRES INSPECTION FOR AN EXTRA BUSS BAR BETWEEN CB 327 AND 166. INSPECTION OF BB-1974 SHOWED NO EXTRANEOUS BUSS BARS INSTALLED. (TC NR 20080107002)                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20080204001192008020400119CE  2008       2          4          CA080107003      120080107G32301018100327      TORQUE KNEE                             BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  LT MLG          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE PERFORMING AN INSPECTION ON THE GEAR IT WAS NOTICED THAT GREASE WAS COMING FROM THE HORIZOTAL CRACK IN THE BOTTOM OF THE TORQUE KNEE. A NEW KNEE WAS ORDERED AND REPLACED. (TC NR 20080107003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20080204001182008020400118NM  2008       2          4          CA080107004      120080102G6420A0311           BEARING                                 ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                              PITCH CONTROL   ROUGH           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1722                                                           (CAN) WHILE DOING AD 2003-04-04 THE BEARINGS WERE FOUND ROUGH ON ROTATION. PART WAS REPLACED WITH NEW. (TC# 20080107004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H10WE   E286                 
200805131    200805131    EU  2008       5          13         CA080108005      120080107G36109599021231      HOSE                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  BLEED AIR SYS   CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       9247                                                           (CAN) ON CLIMB OUT TO CRUISE ALTITUDE, IT WAS DISCOVERED THE AC WOULD NOT PRESSURIZE, AND THERE WAS NO BLEED AIR HEAT. AC RETURNED TO BASE. FOUND BLEED AIR HOSE CRACKED. (TC NR 20080108005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
200805141    200805141    EA  2008       5          14         CA080108006      120080108G5752215150622       SKIN            CNDAIR      2151506180  CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  AILERON TAB     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3481                                                           (CAN) AC UNDERGOING TURBO-PROP CONVERSION AT PRESENT.  RT AILERON GEAR TAB INSPECTION REVEALED A CRACK IN THE LOWER SKIN UNDER THE LOWER IB MASS BALANCE WEIGHT MOUNT.  THE CRACK IS APPROX 1.75 IN. LONG AND LOCATED LATERALLY, FWD OF THE BALANCE WEIGHT MOUNT ATTACHMENT FASTENER HOLES. THE REPLACEMENT GEAR TAB WAS INSPECTED AND FOUND CRACKED IN THE SAME LOCATION. THE CUSTOMER AND OEM HAVE BEEN INFORMED. (TC NR 20080108006)                                                                                                                                                                                                                                                                                                         2H72 4R3  RRTA14EA   ATC14   6  CP871     
20080204001172008020400117EA  2008       2          4          CA080108007      120080103G7603C6CE13151       RELEASE CABLE                           DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  BETA SYSTEM     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE RT POWER CONTROL WAS REPORTED STIFF. AFTER AN INSPECTION ON THIS AREA IT WAS NOTICED THE THE BETA RELEASE CABLE HAD BROKEN AND WAS CAUSING THE POWER CABLE TO BE STIFF. A NEW CABLE WAS PURCHASED AND CABLE WAS CHANGED. (TC NR 20080108007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20080204001162008020400116WP  2008       2          4          CA080108009      120080108G7603B5642           LINK                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              THROTTLE        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       721                                                            (CAN) WHILE CONDUCTING AN INSPECTION, IT WAS NOTED THAT THE BEARING LOOKED TO BE SEPERATED FROM THE LINK. THE LINK WAS REMOVED AND INDEED IT WAS. THE LINK AND NEW WASHERS (SB-62) WERE INSTALLED AND NO OTHER ISSUES WERE NOTED. WHILE CONDUCTING RECENT THROTTLE LINKAGE WASHER INSTALLATION, WE ALSO NOTED THAT SOME OF THE LINKS HAD LITTLE SURFACE DAMAGE ON OTHER LINKS PRE-SB WASHER INSTALLATION. (TC NR 20080108009)                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
20080204001152008020400115WP  2008       2          4          CA080109001      120080108G3260BZE67RNT        DOWNLOCK SWITCH                         CVAC  340   340CVAC     242270AWP  ALLSN 501D  501D13D     03004GL  ALLSN A6441 A6441FN606  GL  RT MLG          INOPERATIVE     W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) CREW REPORTED RT MLG GEAR UNSAFE LIGHT ILLUMINATED. REPLACED RT MLG DOWNLOCK SWITCH P/N BZE6-7RNT AND RETURNED TO SERVICE. (TC NR20080109001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4R4  T  6A6     E282    6  CP898     
20080204001142008020400114NM  2008       2          4          CA080109002      120080104G3233NAS771236       BUSHING                                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MLG ACTUATOR    MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN)  REMOVED NR2 MLG RETRACTION ACTUATOR FOR WORK CARD 2339 AND FOUND THE PICKUP FITTING MISSING (HAT) BUSHING. HOWEVER, THE RETRACTION ACTUATOR WAS ASSEMBLED TO FITTING AND IN SERVICE WITHOUT THIS BUSHING. THIS PLACED SEVERE STRESS ON ATTACHMENT HARDWARE AND FITTING DUE TO THE IMPROPER ASSY.  NR2 MLG RETRACTION ACTUATOR FITTING REPLACED ALONG WITH ALL HARDWARE.  NR2 MLG RETRACTION ACTUATOR REPLACED.  RD8-54-1178 ACCOMPLISHED ALONG WITH NDT INSPECTION TO AFFECTED NACELLE STRUCTURE.  MISSING BUSHING REFERENCE: IPC 54-40-00, FIG. 20, ITEM 410, P/N NAS77-12-36. (TC NR 20080109002)                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080204001132008020400113NM  2008       2          4          CA080109004      120080108G3260H1010153        UPLOCK SWITCH                           BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              NLG             FAULTED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) FLIGHT WAS DEPARTING AND THEN DURING THE TAKEOFF ROLL, THE CREW SELECTED THE LANDING GEAR UP. WHEN THE GEAR HAD CYCLED UP THERE REMAINED A RED NOSE GEAR UNSAFE LIGHT. THE CREW CYCLED THE LANDING GEAR 3 TIMES BEFORE THE UNSAFE LIGHT EVENTUALLY WENT OUT. THE AIRCRAFT RETURNED TO THE RAMP AND THE SYSTEM IS BEING TROUBLESHOT. THIS SDR WILL BE UPDATED WHEN A RECTIFICATION IS ESTABLISHED. (TC NR 20080109004)                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20080204001122008020400112NM  2008       2          4          CA080109005      120080105G2131                CIRCUIT BOARD                           DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  PRESS CONTROLLERBURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       3000430004 60498                                               (CAN) THE CREW REPORTED A STRONG BURNING ELECTRICAL ODOR UPON ARRIVAL. MAINTENANCE FOUND A FAULTY PRESSURE CONTROLLER. FURTHER INVESTIGATION REVEALED THAT AN ELECTRONIC CIRCUIT BOARD INSIDE THE CONTROLLER HAD SOME BURN MARKS.  THE CONTROLLER WAS REPLACED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20080109005)                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080204001112008020400111EA  2008       2          4          CA080109009      120080107G7740601509173       CONVERTER                               CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A1     30068NE                              SIGNAL DATA     FAULTY          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         N  FALSE WARNING                                                                 CRCRUISE         1                      CA       6586 6586                                                      (CAN) DURING ENGINE START, AT ABOUT 40 TO 50 PERCENT, N2, ALL LIGHTS ON THE ITT TAPE INSTANTLY LIGHTED UP. WE IMMEDIATELY SHUTDOWN ENGINE. RESIDUAL ITT WAS ONLY 56 AND NR9702, AFTER MOTORING. VISUALLY INSPECTED THE ENGINE FOR SIGNS OF HEAT OR DAMAGE AND FOUND NOTHING. SUSPECTED INDICATION PROBLEM AND DECIDED TO TRY ANOTHER START. START WAS NORMAL.     WHILE WE CRUISED AT FL 390, ABOUT 50NM SOUTH,  NOTICED A HIGH ITT (ALL LIGHTS ON AGAIN) ON THE SAME LT ENGINE. IMMEDIATELY WE REDUCED THRUST TO REGAIN WITHIN LIMITS. ABOUT 5 MINUTES LATER, ITT STARTED RISING GRADUALLY, AGAIN WE REDUCED THRUST. CREW DISCUSSED ALTERNATE PLAN (DIVERTING), ITT STARTED AGAIN. KEPT REDUCING THRUST UNTIL WE HAD TO SHUTDOWN THE LT ENGINE 2L72 4F4  FRTA21EA   E15NE                
20080204001102008020400110EA  2008       2          4          CA080109011      120080106G5610NP13932110      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       5046                                                           (CAN) THE RT WINDSHIELD CRACKED WHILE IN CRUISE. WINDSHIELD WAS REPLACED IAW AMM. (TC NR 20080109011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA21EA                        
20080204001092008020400109EU  2008       2          4          CA080110001      120080108G2571L243M3810103    BATTERY BOX                             UROCOPEC135 EC135P1     8680990EU  PWA   PW206 PW206B      0    NE                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       98                                                             (CAN) DURING A PREFLIGHT CHECK IT WAS NOTED THAT THE BATTERY TRAY WAS CRACKED.  REPLACED WITH NEW PART. (TC NR 20080110001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U3  UO H88EU   E42NE                
20080331000372008033100037EA  2008       3          31         CA080110003      120080110G2797                CONNECTOR                               CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              TE FLAPS        FAILED          W      C   ABORTED TAKEOFF                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) FLAP FAIL MESSAGE ON POWER UP. CODES READ AND BPSU NR 2 WIRING FAILED. MEL 27-51-02-1 APPLIED. WILL PROVIDE UPDATE WHEN MORE INFO BECOMES AVAILABLE (TC NR 20080110003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E00063EN             
20080320000062008032000006EA  2008       3          20         CA080110006      120080105G2750860D10018       FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAULTED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       8560 8560                                                      (CAN) THE CREW RECEIVED A FLAP FAIL .5 HR INTO THE FLIGHT CLIMBING BETWEEN 25000 TO 27000 FT. THE AC RETURNED WITHOUT INCIDENT. MAINT T/S WAS CARRIED OUT AND THE LT AND RT BPSUS WERE SWAPPED FOR T/S. SUSPECTED FAULTY FECU, FECU REPLACED, FUNCTION CHECK C/O AND TEST FLIGHT C/O SATISFACTORY.  (TC NR 20080110006)                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
20080225002762008022500276NM  2008       2          25         CA080111001      120080110G561080260008        WINDSHIELD                              BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  COCKPIT         BROKEN          W      BA  EMER. DESCENT           UNSCHED LANDING                                                         O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) CO-PILOTS FORWARD WINDSHIELD SHATTERED IN FLIGHT AT 25,000 FEET. EMERGENCY DESCENT AND DIVERSION PERFORMED.  MAINT REPLACED THE WINDSHIELD AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20080111001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080225002782008022500278SW  2008       2          25         CA080111002      120080107G575121993           HINGE                                   BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  AILERON         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1925                                                           (CAN) ON INSPECTION, 4 CRACKS FOUND IN CORNERS (TC NR 20080111002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A21CE   E286    5  NP874     
20080306002052008030600205SW  2008       3          6          CA080111003      120080102G575121993           HINGE                                   BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  AILERON         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4718                                                           (CAN) CRACK FOUND DURING SIRP INSP (TC NR 20080111003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A21CE   E286    5  NP874     
20080306002062008030600206SW  2008       3          6          CA080111004      120080109G6410212010750105    BLADE           BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5317BLYC   41616NE                              TAIL ROTOR      DELAMINATED     W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA       4047       AHW00877                                            (CAN) PILOT HEARD A MUFFED LOW POP SOUND, WITH NO UNUSUAL GAUGE, WARNING LIGHTS, OR VIBRATIONS. UPON DEPARTING FOR ANOTHER SKI RUN THE PILOT AGAIN NOTED AN UNUSUAL NOISE. AC WAS LANDED, AN EXTERIOR INSP WAS CONDUCTED.  IT WAS THEN THAT THE DELAMINATING OF T/R BLADE WAS NOTED. AC REMAINED GROUNDED UNTIL ANOTHER SET OF T/R BLADES WERE INSTALLED. UPON INVESTIGATION OF THE T/R BLADE IT APPEARS THE DELAMINATING STARTED FROM A PREVIOUS REPAIR ALBEIT ON THE OTHER SIDE OF THE BLADE ACCORDING TO THE COMPONENT LOG CARD. THE AIR FLOW STARTED TO PEEL BACK THE SKIN AT THIS SPOT, AS THE PEELING PROGRESSED SKIN REMAINED INTACT UNTIL THE ADHESIVE STRENGTH OF THE GLUE WAS EXCEEDED AND WE SEE THE SECONDARY PEELING IB AND OB WHER1G71 4U4  U  H1SW    E17EA                
20080306002072008030600207NE  2008       3          6          CA080111005      220080111G7421UREM38S         SPARK PLUG                                                                 PWA   R985  R985AN14B   52008NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) (2) SEPARATE OCCASIONS NEW UREM38S SPARK PLUGS WERE REMOVED FROM THE PACKAGE AND FOUND TO HAVE CRACKED CERAMIC INSULATORS. TO VERIFY THE PLUGS WERE TESTED AND FOUND TO BE MISFIRING. THE CRACKING IN THE CERAMIC DOES NOT APPEAR TO BE SHIPPING OR MISHANDLING DAMAGE AS THERE IS EVIDENCE OF TRACKING IN THE CRACKS. (TC NR 20080111005)                                                                                                                                                                                                                                                                                                                                                                                                       3  R          5E1                  
20080320000072008032000007EA  2008       3          20         CA080112001      120080110G2420600591435       ADG                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              UNWANTED DEPLOY W      A   UNSCHED LANDING                                                                                 HJ ELECT. POWER LOSS-50 PC   WARNING INDICATION                                  CLCLIMB          1                      CA       1810718107                                                     (CAN) A/C RETURNED DUE TO ADG UNCOMMANDED DEPLOYMENT ON T/O. PRESENTLY THE AUTO DEPLOYMENT SYS IS UNDER MEL UNTIL MAINT PERMITS. UPDATE FURTHER WHEN T/S HAS BEEN C/O. (TC NR 20080112001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20080306002082008030600208NM  2008       3          6          CA080114001      120080109G3230483025          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  LT MLG          FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       42                                                             (CAN) AFTER TAKEOFF, LT MLG DOOR AMBER LIGHT REMAINED ON (FA CONFIRMED LT MLG DOOR OPEN). GEAR EXTENDED THEN L DOOR AMBER LIGHT, LT RED, AND GEAR HANDLE LIGHT REMAINED ON (FA CONFIRMED THE GEAR WAS PARTIALLY EXTENDED).  AFTER ABOUT 5 MINS, LT GREEN LIGHT ILLUMINATED AND LT MLG DOOR CLOSED. AIR RETURN TO BASE FOR LANDING.  MAINT REPLACED LT MLG SOLENOID SEQUENCE VALVE. (TC NR 20080114001)                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080306002092008030600209EU  2008       3          6          CA080114002      120080111G2160342B030000AM    SWITCH                                  AIRBUS320   A320211     3930320EU  CFMINTCFM56 CFM565A1         NE                              TEMP CONTROL    INOPERATIVE     W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) NR 1 BLEED OVERHEAD SHOWED ON ECAM AIR ENG 1 BLD FAULT COMPLETED ECAM ACTION SHORTLY AFTERWARD AIR ENG 2 BLD FAULT COMPLETED ECAM. BOTH FAN AIR VALVES CHECKED IAW AMM 36-11-54-720-001 NFF. BOTH TCT`S REPLACED ( ENG 1 AND 2) IAW AMM 36-11-43. ENG RUNS CARRIED OUT PACKS OPERATED NORMAL. (TC NR 20080114002)                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA28NM   E29NE                
20080306002102008030600210NM  2008       3          6          CA080114003      120080110G2421                SENSOR          LUCAS       31708001A   DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 2 A/C GEN    OPEN            W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                  168                                                 (CAN) HAD A FAILURE OF THE NR 2 AC GEN THE PREVIOUS WEEK, THE AC GEN WAS REPLACED WITH AN O/H UNIT.  THE AC TOOKOFF AND AT 7000 FEET HAD A NR 2 AC GENERATOR FAIL, THE AC RETURNED TO THE AIRPORT. INVESTIGATION WAS C/O AND FOUND THAT THE SPEED SENSOR WAS OPEN. THE UNIT SENT BACK TO THE SHOP REPLACED THE SPEED SENSOR, UNIT REINSTALLED ON THE A/C AND FOUND SERVICEABLE. A/C DEPARTED ON JAN 14-2008 AND NO OTHER REPORT REPORTED. (TC NR 20080114003)                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080306002112008030600211NM  2008       3          6          CA080115001      120080112G3231AR2674          LATCH                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  MLG DOOR        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NOSE LANDING GEAR ALTERNATE RELEASE DOOR FAILS TO OPEN DURING PRE FLIGHT CHECK. ALTERNATE EXTENSION DOOR LATCH BROKEN CAUSING DOOR TO STICK IN CLOSED POSITION. REPLACED LATCH ALL CHECKS OK. (TC NR 20080115001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080306002122008030600212NM  2008       3          6          CA080115002      120080113G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYD SYSTEM      FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       295                                                            (CAN) DURING TAXI OUT THE NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON AT THE TIME. SHUT OFF PTU AND ALL NR 2 HYD SYS CAUTIONS ILLUMINATED AND CONFIRMED NO PRESSURE ON NR 2 SYS. FLUID QTY WAS LOW. RETURNED TO TERMINAL WHERE MAINTENANCE FOUND FLUID COMING FROM ENGINE DRIVEN PUMP DRAIN.   REMOVED EDP PUMP AND FOUND DRIVESHAFT SHEARED. PUMP REPLACED AND SYSTEM FLUSHED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20080115002)                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080306002132008030600213EU  2008       3          6          CA080115003      120080107G2710KA6D8X50        ROD END                                 DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE12501    59300EU                              AT AILERON      BENT            W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA       98   98                                                        (CAN) WHILE RIGGING THE AILERON SYS FOLLOWING MAINT, NOTICED BOTH THE LT AND RT AILERON CONTROL ROD END FITTINGS WERE BENT WHERE THE CONTROL ROD IS ATTACHED TO THE BELLCRANK AT THE MOST OB POINT. NEW STRAIGHT FITTINGS WERE INSTALLED BUT THIS CAUSED THE AILERON SYS TO BIND. THERE IS NO REFERENCE IN THE IPC OR MM REFERENCING BENT ROD ENDS AS BOTH ROD ENDS ON THE CONTROL ROD HAVE THE SAME PN. (TC NR 20080115003)                                                                                                                                                                                                                                                                                                                    1L72 3I3  BRTA57CE   E00069EN             
20080306002142008030600214NM  2008       3          6          CA080115004      120080112G333030180B23D1683   LIGHT                                   DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  CARGO BAY       SHORTED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE CREW REPORTED (TO MOC) THAT THEY HAD THE (SMOKE) WARNING ILLUMINATED. THEY WERE TOLD TO DO A TURNBACK AND RETURN TO AIRPORT WHERE MAINT STAFF MET THE AIRCRAFT.  DURING THE INVESTIGATION, MAINT PERSONNEL FOUND THE SIDEWALL BAGGAGE DOOR LIGHT WIRE HAD COME OFF INTERNALLY AND WAS ARCING ON ITS CASE. LIGHT ASSY REPLACED AND ENGINE RUNS CARRIED OUT. (TC NR 20080115004)                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080306002152008030600215EU  2008       3          6          CA080115005      120080114G2710DSPR116X058     PUSHROD                                 DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE12502114      EU                              AILERON         BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9                                                              (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, INSPECTED THE ROD ENDS ON OUR AC.  ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115005)                                                                                                                                                                                                                                                                                                                                                                                           1L72 3I3  BRTA57CE   E00069EN             
20080306002162008030600216EU  2008       3          6          CA080115006      120080114G2710DSPR116X058     PUSHROD                                 DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE12501    59300EU                              AILERON         BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       37                                                             (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OUR AC. WE ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MAINTENANCE MANUAL. (TC NR 20080115006)                                                                                                                                                                                                                                                                                                                                                                      1L72 3I3  BRTA57CE   E00069EN             
20080306002172008030600217NM  2008       3          6          CA080115007      120080115G2710129307          PCU                                     BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              AILERON         FROZEN          W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       131472175                                                      (CAN) THE AC ARRIVED AT DESTINATION AND WAS ON A TURN-AROUND WHEN THE CREW NOTICED ON TAXI OUT, THAT THE AILERONS HAD FROZEN UP. THE AC RETURNED TO THE RAMP WHERE MAINT INSPECTED THE SYS. IT WAS DETERMINED THAT THE AILERON POWER CONTROL UNIT HAD FROZEN UP.  HEAT WAS PLACED ON THE PCU AND THE CONTROLS FREED UP. THE CONTROL UNIT WAS FLUSHED OF ALL WATER CONTAMINATES AND LUBRICATED. HEAT WAS APPLIED TO THE PCU FOR APPROX (4) HOURS. IT HAD BEEN NOTED BY FLIGHT CREW THAT THE AC HAD BEEN IN A RAINY ENVIRONMENT EARLIER IN THE DAY. THE AC WAS COLD SOAKED FOR (4) HOURS IN -10 DEGREES AND A 50KPH WIND. NO FURTHER FAULTS FOUND. (TC NR 20080115007)                                                                            2L73 4F4  F  A3WE    E2EA                 
20080306002182008030600218EU  2008       3          6          CA080115008      120080114G2710DSPR116X058     CONTROL ROD                             DIAMONDA42  DA42        2990004EU  THIELTTAE125TAE12501    59300EU                              AILERON         BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       50                                                             (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OUR AC.  ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115008)                                                                                                                                                                                                                                                                                                                                                                                        1L72 3I3  BRTA57CE   E00069EN             
20080306002192008030600219EU  2008       3          6          CA080115009      120080110G6797                GROUND WIRE                             SNIAS 350   AS350B      8680801EU  LYC   LTS101LTS101600A3 41560NE                              HYD SERVO       FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       10932      AC67244                                             (CAN) IN THE PROCESS OF DOING RECURRENT TRAINING FLIGHT. AFTER SEVERAL SIMULATED HYD FAILURES IN AND OUT OF GROUD EFFECT HOVER, PROCEEDED TO PRACTICE THE SIMULATED HYD FAILURE. THE SIMULATED PROCEDURE WAS INITIATED FROM 100 FOOT HOVER WITH A VERBAL WARNING THAT WE NOW HAVE A LOSS OF HYD. AT NO TIME WAS THE HYD ACCUMULATOR TEST BUTTON USED TO SIMULATE, HYD FAILURE, IE. HORN AND LIGHT. FROM THE HOVER THEY ACCELERATED TO 60 KNOTS, AT WHICH TIME THE HYD ON/OFF SWITCH ON THE COLLECTIVE WAS SELECTED TO THE HYD OFF POSITION, AND THEY MAINTAINED 60 KNOTS THROUGHOUT THE CIRCUIT. ON DOWNWIND FOR EAST LIMA TAXIWAY AT 500 FEET ABOVE GROUND. THE PILOT IN COMMAND WAS INFORMED TO WIDEN OUT HIS CIRCUIT SO THAT HE WOULD NOT HAV1G71 3U3  U  H9EU    E5NE                 
20080320000092008032000009EA  2008       3          20         CA080115010      120080113G5250                LATCH                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              LAVATORY DOOR   STUCK           W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                  3261508                                             (CAN) ON SHORT FINAL A PASSENGER GOT STUCK INTO LAVATORY COMPARTMENT. THE F/A TRIED TO UNLOCK THE DOOR LATCH BUT THE PASSENGER ELECTED TO KICK THE DOOR OFF.  IMPORTANT DAMAGES WERE DONE TO THE DOOR HINGE AND LOCKING MECHANISM. AT THIS TIME, INVESTIGATION COULD NOT IDENTIFY THE CAUSE OF THE INCIDENT. (TC NR 20080115010)                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
20080306002212008030600221NE  2008       3          6          CA080115012      220080111G7240                COMBUST CHAMBER                         SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              ENGINE          FOD             W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2190                               22386                       (CAN) DURING A 600 HR ENGINE INSPECTION, A BORESCOPE INSPECTION WAS CONDUCTED IN THE COMBUSTION CHAMBER AREA( INTERNAL) AN OBJECT WAS DISCOVERED HANGING OUT INTO THE FLAME PATH JUST UPSTREAM OF THE POWER TURBINE. THE OBJECT WAS PROTRUDING FROM AN INNER COOLING HOLE IN THE COMBUSTION CHAMBER. AFTER DISCUSSION WITH MFG, THE AC WAS REMOVED AND AN ENGINE TEARDOWN WAS CONDUCTED. THE ITEMS REMOVED AND ENGINE REASSEMBLED AND TESTED ON THE A/C. THE OBJECT COULD NOT BE IDENTIFIED AT THIS LEVEL AND WAS TAKEN BY THE MFG SERVICE REP FOR TESTING. HAVE A FEW BORESCOPE IMAGES AVAILABLE IF REQUIRED. (TC NR 20080115012)                                                                                                              1G71 3U3  U  H9EU    E00054EN             
             20080520     CE  2008       5          20         CA080116001      120080115G53404552803060003   FITTING                     45528030040 LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6170 6170                                                      (CAN) DURING DAILY INSP A CRACK WAS NOTICED ON LT MAIN IB LANDING GEAR DOOR ACTUATOR FITTING, A NEW PART IS ORDERED AND WILL BE REPLACED WHEN RECEIVED. LT IB MAIN GEAR DOOR P/N 4552803004-003 FITTING IS ITEM 69 ON ATTACHED IPC. (TC NR 20080116001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTT00008WIE6WE                 
             20080520     EU  2008       5          20         CA080116002      120080109G32305322012289      DRAG LINK                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NLG             CRACKED         W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT, THE INTRANSIT LIGHT CAME ON IN THE COCKPIT FOR THE NOSE GEAR. THE GEAR WAS THEN SELECTED DOWN AND LOCKED. THE CAPTAIN AND MAINT FELT THERE WAS MORE THEN JUST A SIMPLE INDICATION PROBLEM AND RETURNED THE AC TO THE HOME BASE. AS A SAFETY PRECAUTION THE PASSENGERS WERE OFFLOADED ON THE RUNWAY. THE RT DRAG LINK WAS FOUND TO BE CRACKED. THERE WAS NO TELLTALE SIGNS THAT WOULD CAUSE THE LINK TO CRACK LIKE IT DID. FROM THE LOOK OF THE CRACK IT WAS ALL NEW. THE REST OF THE PC-12S IN THE FLEET WERE CHECKED AND NO OTHER DRAG LINKS WERE CRACKED. THE LINK WAS REPLACED, SWINGS WERE COMPLETED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080116002)                                                          1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20080306002242008030600224CE  2008       3          6          CA080116007      120080112G28203032791         LINE                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  LT NACELLE      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) FUEL FLOW INDICATION LINE FOUND CHAFED AND LEAKING. NEW LINE INSTALLED. (TC NR 20080116007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20080306002262008030600226CE  2008       3          6          CA080116009      120080108G760311452411411     BELLCRANK                               BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  POWER LEVER     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE RT POWER LEVER BELLCRANK LOCATED IN THE BOTTOM OF THE PEDESTAL WAS REPLACED DUE TO WEAR.  AFTER REMOVAL THE PART WAS FOUND TO BE CRACKED. (TC NR 20080116009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20080306002312008030600231NE  2008       3          6          CA080116014      220080106G7310                FUEL SYS                                CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ENGINE          LOW PRESSURE    W      D   RETURN TO BLOCK                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          77771                       (CAN) DURING PRE TAKEOFF ACTIVITES, THE LOW FUEL PRESSURE WARNING ILLUMINATED. AS THE AC TAXIED BACK TO THE RAMP, THE ENGINE SHUT ITSELF DOWN. ENGINE RESTARTS WERE UNSUCCESSFUL.  THE FUEL FLOW DIVIDER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080116014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4F4  F  A22CE   E1NE                 
20080306002322008030600232EA  2008       3          6          CA080116015      220080104G7250                TURBINE BLADES                          BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                              ENGINE          FRACTURED       W      A   UNSCHED LANDING                                                                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        HOHOVERING       1                      CA                                          TH0463                      (CAN) DURING HOVER THE CREW NOTED VIBRATION FOLLOWED BY CHIP DETECTOR LIGHT ILLUMINATION AND LOSS OF POWER. POST FLIGHT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND ASSOCIATED DAMAGE. IT WAS REPORTED THAT THE PILOT HAD DIFFICULTY STARTING THE ENGINE PRIOR TO THIS FLIGHT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080116015)                                                                                                                                                                                                                                                                                                                                              1G72 4U4  U  H4SW    E22EA                
20080306002342008030600234EA  2008       3          6          CA080116017      120080115G321315101103        HOUSING                                 DHAV  DHC7  DHC7102     2802708EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  STRUT           CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE FWD SIDE AT ABOUT THE ONE OCLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS DEEPER THAN THE 0.040. THE LANDING GEAR HAS A 60 000 LANDING LIFE LIMIT AND A 10 000 LANDING INSPECTION REQUIREMENT, THIS GEAR HAD 44 528 LANDINGS SINCE NEW AND 5925 LANDINGS SINCE INSPECTION. THE HOUSING WILL BE REPLACED.  (TC NR 20080116017)                                                                                                                                                                                                                                             2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20080324004282008032400428EA  2008       3          24         CA080116020      220080109G7200                ENGINE                                  PIPER PA46  PA46350P    7104602SO  PWA   PT6   PT6*        52043EA                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         BM SMOKE/FUMES/ODORS/SPARKS  OVER TEMP                                           CRCRUISE         1                      CA                                          RR0005                      (CAN) PILOT REPORTED ENGINE TROUBLE AND ATTEMPTED TO RETURN TO BASE. ENGINE WAS SHUTDOWN BY THE PILOT, AND AC LANDED SHORT OF THE RUNWAY CAUSING SUBSTANTIAL DAMAGE TO THE AIRFRAME. INITIAL INVESTIGATION INDICATES NO OBVIOUS GAS PATH OR TURBINE BLADE DAMAGE, HOWEVER NO OIL WAS VISIBLE ON THE DIPSTICK.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080116020)                                                                                                                                                                                                                                                                                                                          1L71 3O3  TRTA25SO   E2NE                 
20080324004292008032400429NE  2008       3          24         CA080116021      220080109G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              POWER LOSS      W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          17458                       (CAN) CLIMBING THROUGH 4000 FT, ENGINE PWR WAS LOST. ACTIVATION OF THE EMERGENCY POWER LEVER HAD NO EFFECT. THE ENG WAS SECURED AND THE AC WAS ABLE TO RETURN TO POINT OF DEPARTURE. INITIAL INVESTIGATION REVEALS AN EXTERNAL OIL LEAK AND A SEIZED PROP SHAFT ROTOR. THE ENGINE HAS BEEN IMPOUNDED BY THE AUTHORITIES AND WILL BE INVESTIGATED IN THE MFG FACILITY. UPDATES WILL BE PROVIDED IN DUE COURSE. (TC NR 20080116021)                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA                 
20080324004312008032400431    2008       3          24         CA080116022      420080109G6122                MOUNT                                   BEECH 95    D95A        1153408CE  LYC   O360  IO360B1B    41514EA  HARTZLHCC2Y HCC2YK2     GL  GOVERNOR        MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                          L1832351A                   (CAN) AFTER ENGINE REPLACEMENT FOR OVERHAUL A PRELIMINARY GROUND RUN WAS CARRIED OUT. IT WAS FOUND THAT THE PROPELLER WOULD NOT FEATHER WHEN PERFORMING A GOVERNOR CHECK. THE PROBLEM WAS TRACED TO THE GOVERNOR MOUNT PAD WHICH HAD NOT HAD AN OIL GALLERY COMPLETELY DRILLED PREVENTING PROPELLER CONTROL. MAINT REPLACED THE GOVERNOR PAD AND THE AC PROPELLER CONTROL SYS FUNCTIONED NORMALLY (TC NR 20080116022)                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  3A16    1E10    5  CP920     
20080324004322008032400432EA  2008       3          24         CA080116023      220080111G85207106403         CRANKCASE                               PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              NR 1 ENGINE     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1829                          RL489461A                   (CAN) DURING SCHEDULED NR 1 EVENT INSPECTION, AME FOUND LT ENGINE, NR 5 CYL DIFFERENTIAL PRESSURE TEST VERY LOW.  NR 5 CYL REMOVED FOR DETAILED INSP AND POSSIBLE REPLACEMENT. UPON FURTHER INSP MAINT FOUND AN APPROX 4 INCH CRACK, STARTING FROM NR 5 CYL LOWER FWD MOUNT STUD BASE, ALONG CYL. BASE INTO RT CASE EXTENDING APPROX 3.5 INCH TOWARD NR 5 CYL COVER OIL DRAIN PORT IN THE CASE. LT ENGINE REPLACEMENT UNDERWAY. (TC NR 20080116023)                                                                                                                                                                                                                                                                                             1L72 3O3  O  A20SO   E14EA                
20080306002362008030600236EA  2008       3          6          CA080116024      120080113G326016868101        PROXIMITY SWITCHMESSIER                 CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              NLG             MISINSTALLED    W      B   EMER. DESCENT                                                                                   N  FALSE WARNING                                                                 APAPPROACH       1                      CA                  07MDT0422                                           (CAN) DURING APPROACH, GEAR WAS SELECTED DOWN AND NLG INDICATED AMBER. NO GEAR DISAGREE MESSAGE POSTED. GEAR WAS RAISED NORMALLY AND MISSED APPROACH WAS EXECUTED.  AT THAT MOMENT QRH ACTIONS WERE CARRIED OUT FOR GEAR MALFUNCTION. NOSE GEAR INDICATION BECAME RED. TROUBLESHOOTING WAS CARRIED OUT VIA RADIO WITH ENGINEERING NOSE GEAR WOULD NOT INDICATE DOWN. A LOW APPROACH WAS CONDUCTED AT AIRPORT TO VISUALLY CHECK NOSE GEAR POSITION. GEAR APPEARED DOWN.  EMERGENCY DECLARED.  FOLLOWED BY AN UNEVENTFUL LANDING.  THE AC WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE.  AFTER DEPLOYMENT TEST ON LANDING GEAR AND FUNCTIONAL TEST ON PSEU THE PROBLEM WAS DISCOVERED. THE PROBLEM WAS AN INAPPROPRIATE 2L72 4F4  FRTA21EA   E15NE                
20080331000392008033100039NE  2008       3          31         CA080117001      220080110G7200                ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              LEFT            FLAMED OUT      W      A   UNSCHED LANDING                                                                                 X  ENGINE FLAMEOUT                                                               CRCRUISE         1                      CA       21835                              872629                      (CAN) FLIGHT,IN CRUISE, LT ENGINE FLAMED OUT WITH NO PREVIOUS WARNINGS. FLIGHT CREW TRIED TO RESTART LT WITHOUT SUCCESS. AC LANDED. NO ENGINE EXCEEDANCES FOUND. NO EVIDENCE OF WATER CONTAMINATION IN MAIN FUEL TANKS AND FUEL FILTER HOUSING.  PERFORMED A VISUAL EXTERNAL AC INSP AND NO EVIDENCE OF LIGHTNING STRIKE. CHECKED ENGINE THROTTLE RIGGING, FOUND OK. CHECKED FEEDBACK CABLE, FOUND OK. DURING T/S THE ENGINE STARTS NORMALLY, AND ALL ENGINE PARAMETERS ARE STABLES AND NORMAL. POWER ASSURANCE CHECK PERFORMED AND ALL ENGINE PARAMETERS ARE WITHIN SERVICEABLE LIMITS.                                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
20080306002372008030600237SW  2008       3          6          CA080117002      120080117G6420                BEARING         BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              T/R HUB         UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6085 801                                                       (CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET.  ASSY SEND FOR O/H. (TC NR 20080117002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 4U4  U  H1SW    E17EA                
20080306002382008030600238EU  2008       3          6          CA080117003      120080111G2821571712A         BYPASS VALVE                            SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101600A2 41560NE                              FUEL SYSTEM     CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) THE AC LANDED AFTER FLYING SEVERAL HOURS ON A SEISMIC JOB. WHILE DOING A QUICK DI, THE ENGINEERS NOTICED FUEL ON THE TRANSMISSION DECK. IT WAS DISCOVERED THAT THE FUEL FILTER BYPASS INDICATOR PLASTIC HOUSING ON THE BYPASS VALVE ASSY (PN 57171-2A) WAS CRACKED AND WAS LEAKING FUEL ON THE TRANSMISSION DECK. IT IS NOT KNOW HOW MANY HOURS THE AC FLEW THAT DAY WITH THIS FUEL LEAK. THE VALVE ASSY WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080117003)                                                                                                                                                                                                                                                                 1G71 3U3  UNCH9EU    E5NE                 
20080324004342008032400434NM  2008       3          24         CA080117004      120080115G5330143A321220      SKIN                                    BOEING737   737800*            NM                                                               BS 480 S21L     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       11057                                                          (CAN) UNDERGOING MAINT,  LIGHTNING STRIKE ON RIVET AT BS 480,1.3INCHES BELOW STRINGER 21, LT SIDE. REPAIRED IAW EA 5330-02286.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20080325000012008032500001WP  2008       3          25         CA080117005      220080111G72618941171         ADAPTER                                 SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  ENG OIL FILTER  CRACKED         W      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      CA                                          P54055                      (CAN) DURING THE DAILY INSPECTION IT WAS NOTICED THAT THERE WAS OIL IN THE BOTTOM OF THE COWLING. FURTHER INSP REVEALED THAT THE (3) OF THE (4) TANGS FOR THE STUDS WHICH HOLD DOWN THE OIL FILTER ADAPTER WERE CRACKED. TOTAL TIME ON THIS PART IS UNDETERMINED BECAUSE IT IS ON CONDITION.                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
20080306002392008030600239NE  2008       3          6          CA080117006      120080116G792128E252          THERMOSTAT                              SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              NR1 POSITION    UNSERVICEABLE   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            HOHOVERING       1                      CA                                                                      (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP BEGAN TO RISE TO LIMIT. (TC NR 20080117006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G72 3U3  U  H1NE    E1GL                 
20080320000102008032000010EA  2008       3          20         CA080117007      220080115G7200                ENGINE                                  BEECH 99    99          1154002CE  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  LEFT            FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA       119014605                          PCE22135                    (CAN) WHILE DOING PILOT TRAINING, THE LT OIL PRESSURE WARNING LIGHT CAME ON. PILOTS LOOKED DOWN AT OIL PRESSURE GAUGE, THE PRESSURE WAS DROPPING SO THEY SHUTDOWN THE ENGINE AND FEATHERED THE PROP. THEY RETURN TO BASE. ENGINE REMOVED FOR FURTHER INSPECTION. (TC NR 20080117007)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T3  T  A14CE   E4EA    6  CP15EA    
20080306002402008030600240CE  2008       3          6          CA080117008      120080114G32301158200381      SPROCKET                                BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  MLG             WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSP OF THE NLG RETRACT MECHANISM CHAIN FOR TENSION AND LUBRICATION, MAINT NOTED THE DUAL LINK CHAIN WAS ONLY RUNNING ON ONE LENGTH OF CHAIN RATHER THAN (2).  AC WAS INSPECTED MORE CLOSLEY AND THE BRAZE/SPROCKET ASSY WHICH IS INTERMEDIATE BETWEEN LANDING GEAR MOTOR AND RETRACT ACTUATOR FOR THE NOSE GEAR WAS FOUND MISALIGNED AND DISPLACED. UPON REMOVAL OF THE SPROCKET AND IT`S HOUSING IT WAS NOTED THE UNDERLYING AC STRUCTURE WAS CRACKED AND NOT PROVIDING ADEQUATE SUPPORT TO THE SPROCKET ASSY FOR PROPER OPERATION AND ALIGNMENT. THE LACK OF ALIGNMENT BETWEEN THE CHAIN AND SPROCKET CAUSED THE DUAL LINK CHAIN TO SKIP OVER ONE SPROCKET AND ONLY UTILIZE HALF OF THE CHAIN FOR GEAR RETRACTION AND EXTENSION.1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20080220000152008022000015EA  2008       2          20         CA080117010      120080116G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       1301713017                                                     (CAN) DURING DESCENT, CREW REPORTED A FLAP FAIL CAUTION MESSAGE WITH NO FLAP SELECTION. AN EMERGENCY WAS DECLARED AND AN UNEVENTFUL FLAPLESS LANDING WAS CARRIED OUT. THE AC WAS FERRIED TO MAINTENANCE BASE WERE THE LT BRAKE POSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED. A SUCCESSFUL FLIGHT TEST WAS COMPLETED AND THE AC RETURNED INTO SERVICE. THE UNIT HAS ACCUMULATED 30:20 FLIGHT HOURS SINCE REPAIR. (TC NR 20080117010)                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20080220000162008022000016EA  2008       2          20         CA080117011      120080116G5610601R3303319     WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       8194 8194                                                      (CAN) LT COCKPIT SIDE WINDOW SHATTERED IN DESCENT.  THE CREW DID NOT REPORT ANY IMPACT OR PROBLEM WITH THE WINDOW PRIOR TO INCIDENT. VISUAL INSPECTION OF THE WINDOW INDICATES THAT ONLY THE OUTER PLY WAS DAMAGED. THE SIDE WINDOW WAS REPLACED, TESTED AND THE AC RETURNED TO SERVICE. (TC NR 20080117011)                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20080220000172008022000017EA  2008       2          20         CA080118000      120080116G5610NP1393216       WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF343B      30069NE                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       8931                                                           (CAN) COPILOTS WINDSHIELD INNER PANE SHATTERED AT 37,000 FT ON DESENT.  NO EVIDENCE OF HEATER FAILURE WAS OBSERVED. (TC NR 20080118000)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20080306002412008030600241SW  2008       3          6          CA080118001      120080105G6310206040230019    FREEWHEEL UNIT                          BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              MAIN ROTOR      LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            5                                                         (CAN) AFTER FLIGHT THE FREEWHEEL ASSY WAS DISCOVERED LEAKING FROM THE FWD HSG CAP. FREEWHEEL ASSY CHANGED, LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20080118001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E4CE                 
20080306002422008030600242EU  2008       3          6          CA080118002      120080118G2571                BATTERY BOX                             UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              FUSELAGE        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1889                                                           (CAN) DURING DAILY INSPECTION FOUND (2) BROKEN HEAD OF RIVETS ON BATTERY TRAY. RIVETS REPLACED AND AIRCRAFT, SERVICEABLE (TC NR 20080118002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G72 3U3  UNCR0001RD E34NE                
20080220000182008022000018EA  2008       2          20         CA080118003      120080115G2420820465          ADG                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              UNWANTED DEPLOY W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA       1668716687                                                     (CAN) WHILE AC  WAS IN CRUISE AT 30000 FT, ADG DEPLOYED UN-COMMANDED. ALL ELECTRICAL SYSTEMS WERE POWERED. TRIED SWITCHING BACK TO IDG POWER. ADG WOULD NOT SWITCH OVER. MAINTENANCE REPLACED ADG AUTO DEPLOYMENT CONTROLLER AND ADG RESTORE PUMP. (TC NR 20080118003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
20080306002432008030600243NE  2008       3          6          CA080119001      220080118G731415473           PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       797  797                                                       (CAN) FUEL PUMP LEAKING OIL FROM DRAIN LINE. PUMP REMOVED AND NEW PUMP INSTALLED. DEFECT RECTIFIED. (TC NR 20080119001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  O  H11NM   1E4                  
20080220000192008022000019EA  2008       2          20         CA080121001      120080116G5610NP1393219       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       1258812588                                                     (CAN) ON CLIMB OUT THROUGH 6000 FT CREW SELECTED WINDSHIELD HEAT. THE (L WSHLD HEAT) EICAS MESSAGE ILLUMINATED. ABOUT 15 SECONDS LATER CAPTAINS FRONT WINDSHIELD OUTER PLY BEGAN CRACKING. SPIDER WEB LIKE CRACKING CONTINUED UNTIL WHOLE OUTER PANE APPEARED SHATTERED. CAPTAINS FRONT WINDSHIELD WAS REPLACED. AS A PRECAUTION, THE LT WINDSHIELD TEMPERATURE CONTROLLER PN 1659-1 WAS ALSO REPLACED. (TC NR 20080121001)                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20080220000202008022000020EA  2008       2          20         CA080121002      120080120G27505275102         FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        DEFECTIVE       W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) FLAPS FAILED ON INITIAL SELECTION FROM 0 TO 8 DEGREES JUST AFTER PUSHBACK FOR HEADSTART FLIGHT. OAT WAS -29 C OVERNIGHT.  MAINTENANCE GOT CODES FROM FECU, CLEARED FAULT AND RESET FLAPS. FLAPS FUNCTION CHECKED SERVICEABLE, BUT DUE TO RECENT HISTORY IT WAS DECIDED TO FERRY THE AC FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING IS UNDER WAY AND INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20080121002)                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
20080325000022008032500002    2008       3          25         CA080121003      420080102G3497                WIRE                                    BOEING737   737217      1384464NM  PWA   JT8   JT8D17A     52049NE                              TAWS COMPUTER   INOPERATIVE     W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) TAIL 523 ON JAN 2ND APPROACH BACK COURSE ON RWY 15 YELLOWKNIFE 1040FT ASL 350FT AGL LEVEL FLIGHT 140K  IN THIS CASE THE FLIGHT CREW EXPERIENCED A TAWS GENERATED A PICTORIAL DISPLAYED IMPACT WARNING. THE CREW WAS IN VISUAL CONDITIONS AND SAW NO DANGER OF IMPACT. THE AC LANDING WITHOUT FURTHER INCIDENT. IN THE FOLLOWING WEEKS, AC EQUIPPED WITH THE UNIVERSAL TAWS COMPUTER (STC ST10622SC) EXPERIENCED SIMILAR ANOMALIES.  UNIVERSAL AVIONICS WAS CONTACTED CONCERNING THE ISSUE. THIS NORTH REGION AIRPORT DATA BASE WAS ALREADY UNDER REVIEW DUE TO OTHER OPERATOR COMPLAINTS. A NEW DATA BASE WAS RELEASED AND FORWARDED. ATTEMPTS TO LOAD THE NEW DATA BASE INTO THE TAWS UNITS FAILED DUE TO A COMMUNICATION PROBLEM BETWEEN2L72 4F4  F  A16WE   E2EA                 
20080220000212008022000021EU  2008       2          20         CA080121004      120080118G7820L24266710000    BAFFLE                                  ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA  MUHBR MTV   MTV9*       EU  EXHAUST         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INTERNAL BAFFLE ATTACH WELD WAS FOUND CRACKED DURING A 100 HOUR INSPECTION. (TC NR 20080121004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O0 A76EU   1E10    5  CP24NE    
20080220000222008022000022EU  2008       2          20         CA080121005      120080118G6230350A37000402    GUIDE                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              SWASHPLATE      WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       602                                                            (CAN) DURING A SCHEDULED 100 HOUR INSPECTION THE COLLECTIVE LEVER WAS RAISED TO EXAMINE THE SWASHPLATE GUIDE.  IT WAS DISCOVERED THAT THE SELF ADHESIVE TAPE APPLIED TO THE GUIDE WAS BUNCHED UP BETWEEN THE ROTATING SWASHPLATE AND THE SWASHPLATE GUIDE.  THE ROTATING SWASHPLATE CONTACTED THE SWASHPLATE GUIDE LEAVING LIGHT WEAR MARKS AROUND THE CIRCUMFERENCE.  THE SWASHPLATE GUIDE WAS REPLACED AND WILL BE SENT TO THE MFG FOR EVALUATION AND SERVICEABILITY CHECK. (TC NR 20080121005)                                                                                                                                                                                                                                               1G71 3U3  U  H9EU    E19EU                
20080220000232008022000023NM  2008       2          20         CA080121007      120080116G2436                VOLT REGULATOR                          BOEING727   727225      1384077NM  PWA   JT8   JT8D15      52051NE                                              ODOR            W      O   OTHER                                                                                           BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT CREW SHUTDOWN CHECKLIST, ON APU POWER, SMOKE ALARM SOUNDED IN THE AC LAVATORY.  LAVATORY INSP REVEALED SOME SMOKE.  ALARM SILENCED WHILE INSPECTING THE LAVATORY AREA.  AFTER APPROXIMATELY 30 SECONDS, THE ALARM SOUNDED AGAIN, AND THE AC POWERED DOWN.  MAINT  INSPECTED THE LWR E/E COMPARTMENT AND FOUND SUBSTANTIAL AMOUNT OF SMOKE WITH AN ELECTRICAL BURNING ODOR. FIRE DEPARTMENT WAS CALLED BY THE FLIGHT CREW.  MAINT DISCONNECTED THE MAIN AC BATTERY AND DISCONNECTED THE BATTERY CHARGER. NO OBVIOUS FAULTS WERE NOTED WITH THE BATTERY OR CHARGER AND BOTH UNITS DID NOT APPEAR TO BE OVERHEATED. THE AC WAS THEN REPOWERED USING ONLY EXTERNAL POWER WITH NO FURTHER SMOKE EVIDENT. INSP OF ALL ELECTRICAL R2L73 4F4  F  A3WE    E2EA                 
20080220000242008022000024WP  2008       2          20         CA080121008      120080109G6310369D25351DSN    SPRAG CLUTCH                            HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              MAIN ROTOR      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       958                                                            (CAN) DURING 300 HOUR INSPECTION PART WAS FOUND TO HAVE PITTING ON SEVERAL ELEMENTS.  SPRAG CLUTCH REPLACED. (TC NR 20080121008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H3WE    E4CE                 
20080220000272008022000027SO  2008       2          20         CA080121009      120080108G2421ALU8421R        ALTERNATOR                              PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCC4Y HCC4YR2     GL                  INOPERATIVE     W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA            278                                                       (CAN) IN CRUISE, AC STARTED TO LOOSE ELECTRICAL POWER. FIRST INDICATION, THE TRANSPONDER FAILED. AC THEN RETURNED TO AIRPORT. BOTH LT AND RT ALTERNATOR FAIL INDICATOR LIGHTS REMAINED OUT DURING THE FLIGHT. UPON INSP NEITHER ALTERNATOR WAS CHARGING THE SYS. THE ONLY POWER SUPPLY WAS THE AC BATTERY. THE LT ALTERNATOR WAS FOUND TO BE UNSERVICEABLE. THE RT ALTERNATOR, BECAUSE OF THE ADDED ELECTRICAL LOAD PUT ON IT, CAUSED THE ALTERNATOR BELT TO SLIP ON THE PULLEY, MAKING THE ALTERNATOR INOPERATIVE. ALL AC RADIOS, NECESSARY LIGHTS AND DEICING HEAT WAS ON AT THIS TIME. (TC NR 20080121009)                                                                                                                                   1L72 3O3  O  A20SO   E14EA   5  CP52GL    
20080220000282008022000028EA  2008       2          20         CA080121011      220080104G7414BL600646201     MAGNETO                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              RT MAGNETO      FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            890                                                       (CAN) DURING MAGNETO CHECK PRIOR TO FLIGHT, THE RT MAGNETO FAILED. MAGNETO REPLACED AND CHECKED SERVICEABLE. (TC NR 20080121011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   E295                 
20080220000292008022000029NE  2008       2          20         CA080122001      220080108G7414BL600646201     MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              RT              UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            767                                                       (CAN) RT MAGNETO FOUND UNSERVICEABLE ON PREFLIGHT. MAGNETO CHANGED, GROUND RUN AND LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20080122001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20080220000302008022000030NM  2008       2          20         CA080122002      120080105G5320                WEB                                     DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2452                                                      (CAN) DURING MAINT ROUTINE INSP, THE NOSE LANDING GEAR GROUND LOCK MECHANISM WAS FOUND HARD TO OPERATE. FURTHER INVESTIGATION REVEALED THAT THE FLOOR WEB AT ZONE 112, STA X97 WAS CRACKED CAUSING THE GROUND LOCK LEVER TO CONTACT THE PIVOT TUBE ARM. THE CRACKED AREA WAS REPAIRED IN AUGUST 2006 IAW RD8-53-0638. THE AC HAS ACCUMULATED 2451:46 HOURS AND 3379 CYCLES SINCE REPAIRED. THE OLD PATCH WAS REPLACED IAW THE ABOVE RD AND THE AC WAS RELEASED INTO SERVICE. (TC NR 20080122002)                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081104     CE  2008       11         4          CA080122003      120080121G5350                STRUCTURE                               CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  TAIL CONE       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16225                                                          (CAN) WHILE INSPECTING SOME ITEMS, MFG CONTINUED AIRWORTHINESS PROGRAM IT WAS NOTICED THAT 2 CRACKS CAME FROM THE RUDDER CABLE HOLES AND ANOTHER CRACK CAME FROM THE NUTPLATE UNDER THE DOUBLER. CONTINUED AIRWORTHINESS INSP 53-40-04 COVERS THIS INSPECTION BUT IS N/A BY S/N ON OUR ACFT. A NEW BULKHEAD IS ORDERED AND WILL BE CHANGED BEFORE NEXT FLIGHT. (TC NR 20080122003)                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E5CE    5  CP47GL    
20080220000312008022000031SO  2008       2          20         CA080122005      120080111G3213753227          YOKE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA  HARTZLHCE2Y HCE2YK2     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3004                   273354                                  (CAN) DURING ANNUAL INSP, A CRACK WAS FOUND ON THE OB SIDE OF THE LT MAIN LANDING GEAR YOKE.  THE CRACK WAS ALONG THE EDGE OF THE CASTING MARK AT THE TOP WHERE THE OLEO SHAFT IS ATTACHED TO THE YOKE. THE CRACK WAS FOUND BY VISUAL INSPECTION. (TC NR 20080122005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  1A10    1E4     5  CP9EA     
20080220000322008022000032GL  2008       2          20         CA080122007      320080122G61103GFR34C703      PROPELLER                               CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL                  LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       202                                                            (CAN) AFTER START UP AND REPOSITION OF AC FOR FUEL, A HYD LEAK WAS NOTED FROM THE PROPELLER, RUNNING FROM THE BLADE ROOT TO THE BLADE TIP. THE PROPELLER WAS REMOVED AND ROUTED TO A OVERHAUL SHOP FOR REPAIR. (TC NR 20080122007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20080220000332008022000033NE  2008       2          20         CA080122008      220080118G8550                LINE                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN1     52008NE  HARTZLHCB3R HCB3R302    GL  OIL SYSTEM      OBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN ENG WAS REMOVED FOR O/H, IT WAS DISCOVERED THAT IN THE OIL DELIVERY LINE THERE WAS PLASTIC DEBRIS FROM THE CONTAINERS USED TO REPLENISH THE ENGINE OIL.  THERE WAS POOR MAINTENANCE PRACTICE WHEN OPENING THESE CONTAINERS TO POUR THE OIL IN THE TANK IN THE AC, THE CAPS WERE NOT FULLY REMOVED FROM THE CONTAINERS. THERE WERE NUMEROUS ITEMS IN THE OIL SYS AND THIS HAS THE POTENTIAL TO RESTRICT THE FLOW OF THE OIL RESULTING IN SHUTDOWN OF THE ENGINE.  CARE MUST BE TAKEN WHEN CARRYING OUT THIS TASK AND THIS NEEDS TO BE COMMUNICATED TO ANYONE WHO IS SERVICING THESE AC. (TC NR 20080122008)                                                                                                                           1H71 3R3  RRCA806    5E1     5  CP28EA    
20080220000342008022000034    2008       2          20         CA080122009      420080120G345710706           ANTENNA                                 BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  GPS             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GPS ANTENNA WAS REPLACED DUE TO NO SIGNAL TO UNS-1K FMS. UPON REMOVING ANTENNA FROM FUSELAGE (UPPER COCKPIT ROOF), FOUND HEAVY CORROSION ON ANTENNA AND SOME CORROSION ON FUSELAGE SKIN. A QUICK REVIEW OF THE RECORDS SHOWS THAT THIS ANTENNA WAS LIKELY INSTALLED AT THE FACTORY (2001) THERE WAS NO SEALANT UNDER THE ANTENNA AND NO GASKET MATERIAL EITHER. THERE WAS SOME SEALANT AROUND THE EDGE. THE CO-AX CONNECTER WAS ALSO CORRODED. REPLACED ANTENNA, CLEANED, ETCHED, ALODINED AND PRIMED THE SKIN AND RETURNED A/C TO SERVICE. (TC NR 20080122009)                                                                                                                                                                           2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20080220000362008022000036SW  2008       2          20         CA080122010      120080111G6230206010447109    BEARING                                 BELL  206   206L4       1182110SW                                                               SWASHPLATE ASSY CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19193275   EAJG11437                                           (CAN) DURING A PHASE INSP, MECHANIC FOUND A CHAFED AREA ON TOP OF THE COLLECTIVE LEVER BEARING EAR P/N 206-010-447-109.  FURTHER INSP REVEALED CHAFING AT BOTTOM OF BOTH SWASHPLATE ROTATING RING BEARING EARS. CHAFED AREAS APPROX 0.020-0.040 INCH DEPTH. MECHANIC POSITIONED THE COLLECTIVE STICK FULL DOWN AND CYCLIC FULL FWD WHILE CAUTIOUSLY LINING UP EACH ROTATING RING WITH THE COLLECTIVE LEVEL FOR A CLEARANCE CHECK. BOTH WERE CONTACTING. REPLACED SWASHPLATE, DRIVE LINK AND M/R PITCH CHANGE LINK ASSY`S. COLLECTIVE AN CYCLIC CONTROLS WERE RE-RIGGED. (TC NR 20080122010)                                                                                                                                                     1G71 3U    NCH2SW                         
20080220000392008022000039SO  2008       2          20         CA080123001      220080119G8530                CYLINDER                                CESSNA150   150H        2071818CE  CONT  O200  O200A       17020SO  MCAULY1A101 1A101DCM    GL  NR 4            LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            721                           684508A                     (CAN) WHILE CARRYING OUT MAINT, CYLINDER NR 4 WAS FOUND LOW ON COMPRESSION 45/80.  AIR WAS LEAKING THROUGH THE EXHAUST. (TC NR 20080123001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  3A19    E252    5  NP918     
20080220000402008022000040SW  2008       2          20         CA080123002      120080122G322099353           COLLAR                                  GULSTM690TP 690         0141720SW  GARRTTTPE331TPE3315251K      NM  HARTZLHCB3T HCB3TN5     GL  NLG             WORN            W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) UNSAFE NOSE GEAR, CIRCLING AT AIRPORT,  DECIDED TO FLY AC TO ANOTHER AIRPORT. AC CAME BY SLOW WITH GEAR DOWN. NOSE LOOKED DOWN HOWEVER NOSE WHEEL WAS COCKED TO THE RT. PILOT CIRCLED TO THE WEST UNTIL EMERG EQUIPMENT WAS IN PLACE. THEN LANDED RUNWAY 29. HELD THE NOSE OFF AS LONG AS HE COULD THEN LET IT DOWN. NOSE GEAR COLLAPSED. 4 PEOPLE ON THE TAIL WE PULLED THE NOSE GEAR DOWN, THEN TOWED AC TO OUR HANGAR.   IT WAS NOTED THAT THEIR WAS A CROSSWIND WHEN THE AC DEPARTED  MINOR DAMAGE TO NOSE DOORS. MAINT IS LOOKING INTO THE PROBLEM. MAINT FOUND EXCESSIVE WEAR IN NOSE GEAR TRUNNION SLOT (PN 9935-1) AND DAMPING COLLAR (PN 9935-1, -3). EXCESSIVE WEAR CAUSED BINDING AND PREVENTED NOSE WHEEL FROM CENTERING WHEN 1H72 3T4  T  2A4     E2WE    6  CP15EA    
             20081229     CE  2008       12         29         CA080123003      120080123G32450923150         TUBE                                    CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE  MCAULY4HFR344HFR34C762  NE  NLG TIRE        DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       51                                                             (CAN) THE FLAT WAS DISCOVERED UPON LANDING AND THE A/C WAS SHUTDOWN BECAUSE IT WAS UNABLE TO TAXI. THE FENDER AND THE WHEEL WERE REPLACED. UPON INSP OF THE FLAT TIRE IT WAS DISCOVERED THAT THE INNER TUBE WAS SPLIT ALONG THE SEAM, THERE WAS NO ISSUES OR HOLES IN THE TIRE AND THE ASSY WAS ASSEMBLED CORRECTLY.                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T3  TRTA7CE    E4EA    6  C3PNE     
20080220000432008022000043SW  2008       2          20         CA080123007      120080115G281071494R          FUEL TANK                               BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  OUTBOARD        CRACKED         W      K   NONE                                                                                            KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA       2686                                                           (CAN) GAS FUMES WERE DETECTED AROUND AC.  WHEN RT OB FUEL TANK WAS REMOVED A CRACK WAS FOUND ON A REPAIRED RADIUS OF THE LATERAL RE-ENFORCEMENT INDENT OF THE TANK.  720 HOURS SINCE THE TANK WAS REPAIRED. (TC NR 20080123007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  O  A21CE   E286    5  NP874     
20080220000442008022000044SW  2008       2          20         CA080123008      120080115G281071493R          FUEL TANK                               BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  INBOARD         CRACKED         W      K   NONE                                                                                            KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA       2686                                                           (CAN) GAS FUMES WERE DETECTED AROUND AC.  WHEN THE RT IB FUEL TANK WAS REMOVED A CRACK WAS FOUND AROUND THE FUEL VENT INTERCONNECT WELD. (TC NR 20080123008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  A21CE   E286    5  NP874     
20080220000562008022000056NM  2008       2          20         CA080124001      120080123G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 WOW        FAULTY          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) GEAR WOULD NOT RETRACT AFTER TAKEOFF, RETURN TO FIELD. CREW ELECTED TO RETURN BASE. MAINTENANCE FOUND THE NLG NR 2 WOW HARNESS TO BE AT FAULT.  NEW HARNESS INSTALLED, AIRCRAFT RETURNED TO SERVICE. (TC NR 20080124001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080220000572008022000057NM  2008       2          20         CA080124002      120080124G2910                SWIVEL                                  BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              NR 6 SLAT       LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       8455 709                                                       (CAN) AC WAS DISPATCHED AND DURING CRUISE FLIGHT, THE FLIGHT ENGINEER NOTICED THAT THE (A) SYS HYDRAULICS INDICATED .1250 OF A TANK REMAINING. THE CREW DECIDED TO DECLARE AN EMERGENCY AND THE LANDING GEAR NEEDED TO BE CRANKED DOWN. THE AC LANDED SAFELY AND WAS TOWED OFF THE RUNWAY TO THE RAMP.  MAINT TROUBLESHOT THE SNAG AND FOUND THAT THE NR 6 LEADING EDGE SLAT WAS LEAKING HYD FLUID FROM A LEAK IN THE SWIVAL ASSY OF THE SLAT. THE ACTUATOR WAS REMOVED AND REPLACED AND THE HYD SYS WAS REPLENISHED. THE AC WAS FUNCTION TESTED SERVICEABLE AND RETURNED TO SERVICE. (TC NR 20080124002)                                                                                                                                       2L73 4F4  F  A3WE    E2EA                 
20080220000592008022000059SW  2008       2          20         CA080124003      120080117G3210D212664201      CROSSTUBE                               BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              LG              CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2236                   30294                                   (CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOLLOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EXCESSIVE DEFLECTION, TOTAL SPREAD WAS 107 INCHES AND SYMMETRICAL TO THE MIDPOINT OF THE CROSSTUBE. THESE MEASUREMENTS ARE ACCEPTABLE WITH THE ICA-D212-664 MANUAL. THE CRACK WAS ON THE LOWER PART OF THE UPPER PORTION OF TUBE AND 4.5 INCHES FROM MIDPOINT. AT THE TIME OF DISCOVERY THE HELICOPTER WAS BEING USED FOR HELI-SKIING. NO HARD LANDING HAD OCCURED DURING ITS INSTALLATION LIFE. MEMOS TO INSPECT THE OTHER AC LANDING GEAR HAS BEEN SENT TO THE ENGINEERS. (TC NR 20080124003)   1G71 4U4  U  H1SW    E17EA                
20080220000602008022000060WP  2008       2          20         CA080124005      220080122G72608937373         NUT                                     SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  GEAR SHAFT      BACKED OUT      W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA            2034                                                      (CAN) A/C CAME IN TO THE MAINT HANGER DUE TO HAVING A CHIP LIGHT COME ON IN THE COCKPIT. INSP FROM MAINT NOTICED THAT THERE WAS METAL ON THE CHIP DETECTOR OF ENGINE P-54121. AT THAT TIME THE ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR FURTHER INSP. THE ENGINE WAS DISMANTLED TO FIND THAT THE HIGH SPEED PINION NUT (HSP) PN 893737-3, WAS STARTING TO BACK OFF FROM ITS OVERHAULED TORQUE SPECIFICATIONS.  THE HSP WAS OVERHAULED ON THE 22 JULY 05. THE NUT WHEN TORQUED IS SUPPOSED TO HAVE A PIN PN S815N4-0-200 STAKED BESIDE THE NUT TO PREVENT IT FROM BACKING OFF. UPON FURTHER INSPECTION OF THE PIN AREA IT DOES NOT LOOK LIKE THERE WAS EVER A PIN INSTALLED AT THE TIME OF INSP, WITH THE NUT BACKING OFF OF THE HSP THIS COUL2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081104     SW  2008       11         4          CA080124006      120080123G79218945682         LINE                                    FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  OIL COOLER      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAF WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LINE WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD CHAF IN THE FUTURE (TC NR  20080124006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081104     SW  2008       11         4          CA080124007      120080123G79218945682         LINE                                    FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  OIL COOLER      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAFE WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LINE WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD NOT CHAFE IN THE FUTURE. (TC NR 20080124007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081104     WP  2008       11         4          CA080124008      220080121G7313310323259       FUEL NOZZLE                             SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED FUEL NOZZLE CHANGE A NOZZLE WAS FOUND TO BE CRACKED IN THE AREA, SECONDARY MANIFOLD FITTING THAT MFG SAYS TO INSPECT. (TC NR 20080124008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081104     WP  2008       11         4          CA080124009      220080120G7310310323259       FUEL NOZZLE                             SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE                  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FUEL NOZZLE FOUND CRACKED ON SECONDARY MANIFOLD DURING SCHEDULED NOZZLE CHANGE IN THE AREA THAT MFG SAYS TO INSPECT FOR CRACKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20080220000612008022000061EA  2008       2          20         CA080124011      120080124G5330                SKIN PANEL                              DHAV  DHC7  DHC7102     2802708EA                                                               FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                              068                                     (CAN) WHILE CONDUCTING A CORROSION INSP ON AC, VENEZUELAN REGISTRATION YV1000, IAW THE CUSTOMERS EQUALIZED MAINT PROGRAM. NUMEROUS AREAS OF CORROSION WERE DETECTED THROUGHOUT THE AC.  A THRESHOLD AND REPETITIVE CORROSION INSP PROGRAM IS MANDATED BY ADCF-98-03 AND IS TO BE CARRIED OUT IAW THE AC CORROSION PREVENTION AND CONTROL MANUAL (PSM 1-7-5). NO INFORMATION IS AVAILABLE TO KNOW IF THE THRESHOLD OR REPEAT CORROSION INSPECTIONS WERE COMPLIED WITH.  WHILE CONDUCTING THE 3-YEAR REPETITIVE DISBOND INSP REQUIRED BY ADCF-94-15 IAW MFG SB 7-51-1 AND THE NDT MANUAL (PSM 1-7-7A) PART 5, SEVERAL AREAS OF DISBOND WERE FOUND ON THE FUSELAGE SKIN PANELS, HORIZONTAL STABILIZER SKIN PANELS AND WING PANELS. IN ADDITION, ARE2H74 4T      A20EA                        
20080220000642008022000064SO  2008       2          20         CA080124013      220080109G8530636242          GUIDE           CONT                                                       CONT  O550  IO550D      17042SO                              EXHAUST         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       296                                                            (CAN) 5 CYLINDER ASSYS RECEIVED FOR REPAIR DUE TO LOW COMPRESSION. ABNORMALLY HIGH WEAR WAS FOUND INSIDE THE EXHAUST GUIDES. WEAR PATTERNS ON THE EXHAUST VALVES AND SEATS INDICATED THAT THEY WERE NOT PROPERLY ALIGNED CAUSING THE VALVE STEMS TO WEAR AGAINST THE GUIDES. (TC NR 20080124013)                                                                                                                                                                                                                                                                                                                                                                                                                                                       3  O          E3SO                 
20080220000652008022000065SO  2008       2          20         CA080124014      220080111G8530628309          GUIDE           CONT        655483A11                                      CONT  O200  O200A       17020SO                              CYLINDER        UNDERSIZE       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       188                                                            (CAN) EXHAUST VALVE GUIDES FOUND TO BE 0.002 INCH SMALLER THAN THEY SHOULD BE AFTER 2 CYLINDERS WERE SENT IN FOR REPAIR DUE TO STUCK EXHAUST VALVES. (TC NR 20080124014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               3  O          E252                 
             20081219     CE  2008       12         19         CA080124015      120080123G575355250007983     BEARING                                 CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              TE FLAP         MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ACFT ARRIVED AT OUR FACILITY FOR PAINT.  UPON DISASSEMBLY MX NOTED THE BOLT SECURING THE RT FLAP CENTRE AFT ROLLER WAS LOOSE.  FURTHER INVESTIGATION AND REMOVAL DETERMINED THAT THE BEARING AND SHIM REQUIRED TO BE UNDER THE HEAD OF BOLT WAS MISSING AND PROBABLY NOT INSTALLED THE LAST TIME MX WAS DONE IN THAT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                1L72 4F4  F  A22CE   E1NE                 
20080220000662008022000066SO  2008       2          20         CA080124016      220080123G8530636242          GUIDE           CONT        655471A4                                       CONT  O550  IO550D      17042SO                              CYLINDER        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       803                                                            (CAN) RECEIVED CYLINDER FOR REPAIR DUE TO LOW COMPRESSION. WHEN RESURFACING THE VALVE SEATS IT WAS NOTED THAT THE INTAKE GUIDE AND SEAT DID NOT PROPERLY LINE UP. THIS COULD HAVE CAUSED THE LEAK THAT RESULTED IN LOW COMPRESSION. (TC NR 20080124016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                3  O          E3SO                 
20080220000672008022000067CE  2008       2          20         CA080125001      120080122G7931                OIL SYSTEM                              CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                              PRESSURE        UNKNOWN         W      BE  EMER. DESCENT           ENGINE SHUTDOWN                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       576                                                            (CAN) APPROXIMATELY 5 -7 MINUTES AFTER TAKEOFF, THE WARNING LIGHT (LOW OIL PRESS R ) WAS OBSERVED ON THE M.A.P. AND (0) ON THE OIL PRESSURE INDICATOR TAPE . A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED FOLLOWED BY THE DECLARATION OF AN EMERGENCY. ENG IS STILL UNDER INVESTIGATION TO DETERMINE THE CAUSE. (TC NR 20080125001)                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA22CE   E00059EN             
20080220000682008022000068EA  2008       2          20         CA080125002      120080122G2752                ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              FLAP            FAILED          W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON FINAL AFTER SELECTING FLAP TO 8 DEGREES. AN EMERGENCY WAS DECLARED AND THE AC CONDUCTED A FLAPLESS LANDING WITHOUT FURTHER INCIDENT. THE AC WAS FERRIED. ALL FLAP ACTUATORS WERE REPLACED AND THE AC WAS RELEASED. A SUCCESSFUL TEST FLIGHT WAS CONDUCTED AND THE AC RETURNED INTO SERVICE. ALL FLAP ACTUATORS WERE SENT TO THE SHOP FOR LOW TEMPERATURE TORQUE CHECK. RT NR 4 FLAP ACTUATOR P/N 854D100-20 S/N OFF 1911, TSN 8231 TSR 2946 CSN 6684 CSR 2558 RT NR 3 FLAP ACTUATOR PN 853D100-20 S/N OFF 2604, TSN 8231 TSR 2946 CSN 6684 CSR 2558 RT NR 2 FLAP ACTUATOR P/N 852D100-19 S/N OFF 5996 TSN 2946 TSR 2946 CSN 2558 CSR 2558 RT NR 1 FLAP ACTUATOR PN 852D100-19 SN OFF 59482L72 4F4  FRTA21EA   E15NE                
20080220000692008022000069EA  2008       2          20         CA080126001      120080118G5610NP13932113      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              LT/ CAPTAIN     BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       14906                                                          (CAN) (CAPTAINS WINDSHIELD SHATTERED IN FLIGHT. PRESSURIZATION STAYED NORMAL AND THE AC CONTINUED.  MAINT IS GOING TO CHANGE THE WINDSHIELD). REPLACED THE WINDOW  WINDSHIELD, MAIN PILOT, NP-139321-13 01355H5650 TSO: 14906.50 CSO: 12838 (TC NR 20080126001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20080220000702008022000070EA  2008       2          20         CA080126002      120080117G76031603730003      THROTTLE CONTROL                        CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              LT ENGINE       MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) CREW REPORTED LT ENG REMAINED AT HIGH POWER SETTING WHEN AC BROUGHT TO IDLE. N1 REMAINED BETWEEN 82 AND 91 PERCENT.  IFSD PILOT COMMANDED IN FLIGHT SHUTDOWN: CONFIRMED, AFTER (ABORTED APPROACH) PILOT SHUTDOWN THE LT ENG USING FIRE PUSH DURING (GO AROUND). LANDED ON ONE (RT) ENGINE.  NOT POSSIBLE TO LAND THE A/C WITH (LT) AT 82 TO 90 PERCENT N1 FWD THRUST, NO ABILITY TO RETARD LT THRUST LEVER TO REDUCE THRUST AND EFFECT FUEL SHUTOFF.   CONTROL ASSY, THROTTLE PUSHPULL (LT) P/N: 1603730 AND NR 8722, 003 S/N: UKN (TC NR 20080126002)                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20080220000722008022000072EA  2008       2          20         CA080126003      120080116G5610601R3303320     WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              COCKPIT         CRACKED         W      AB  UNSCHED LANDING         EMER. DESCENT                                                           O  OTHER                                                                         CRCRUISE         1                      CA       9573                                                           (CAN) AC DIVERTED, FOS SIDE WINDOW CRACKED IN FLT, CREW DECLARED EMRG NO PRESS ISSUES. NOTED CREW USED MASKS. MASKS NOT DROPPED IN CABIN.  SIDE WINDOW P/N:601R33033-20, S/N: 04023H4068: CO-PILOT SIDE WINDOW 9573 HRS / 6860 CYCLES (TC NR 20080126003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E00063EN             
20080220000732008022000073EA  2008       2          20         CA080126004      120080124G5210NAS76A16011     BUSHING                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              PAX DOOR        MIGRATED        W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       24960                                                          (CAN) CREW REPORTED THAT AT 12000 FT PAX DOOR WARNING MSG POSTED. FOLLOWED QRH AND RETURNED TO FIELD.  FOUND BUSHING IN FWD LATCH CAM FITTING MIGRATED. REINSTALLED BUSHING IN UPPER FWD CAM LEVER REF AMM 52-11-23.  NOTE: AC WAS PRE SB 601R-52-110 CONFIGURATION.  MECHANISM GA, PASS DOOR LATCH MFG 601R31903,  BUSHING: P/N: NAS76A16-011 MIGRATED 24960:41 TSN / 22803 CSN (TC NR 20080126004)                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
20080220000742008022000074EU  2008       2          20         CA080128001      120080121G271019004212401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408EU  GE    CF34  CF3410E5A1  30022NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AILERON CONTROL CABLES INSP, ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NO 128, 165 AND J/C 27-11-00-003-RT/2 SNAGS NR 87, 166.  THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643, C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 2635 C02 CHECK.  (TC NR 20080128001)                                                                                     2L72 4F4  FRTA57NM   E00070EN             
20080220000752008022000075EA  2008       2          20         CA080128002      120080127G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN EXERCISING FLAPS DURING MAINTENANCE COLD WEATHER CHECKS, FLAP FAIL MESSAGE SHOWED AS SOON AS FLAPS SELECTED.  A/C FERRIED, MFG FSR CALLED TO ATTEND HANGAR FOR TEARDOWN AND INSPECTION.  MORE TO FOLLOW. (TC NR 20080128002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20080520     SW  2008       5          20         CA080128004      120080128G2720                CONTROL CABLE                           AIRTRCAT802 AT802A      0390308SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  RUDDER          STUCK           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       499                                                            (CAN) DURING INSP, THE LT RUDDER CABLE WAS FOUND SNAGGED ON THE WATER RUDDER CABLE PULLEY GUARD.  (TC NR 20080128004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20080220000782008022000078SW  2008       2          20         CA080128007      120080118G6730206076062       SERVO                                   BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              MAIN ROTOR      NOISY           W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       6987                                                           (CAN) WORN LINKAGE AND PILOT VALVE CAUSED SERVO TO MAKE LOUD GROWLING NOISE. THIS WAS AN INTERMITTENT PROBLEM THAT COULD BE INDUCED BY CERTAIN CONTOL INPUTS. THE SOUND WAS FINALLY DETERMINED TO BE COMING FROM THE RT SERVO AND IT WAS REPLACED. THERE WERE NO CONTROL PROBLEMS ENCOUNTERED AND THE SERVO HAS SINCE BEEN OVERHAULED. (TC NR 20080128007)                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UO H2SW    E1GL                 
20080220000792008022000079SW  2008       2          20         CA080129003      120080116G7921MS172244        NUT                                     BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              OIL COOLER BLOW UNDERTORQUED    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1650 1650                                                      (CAN) DURING 100 HR, LUBRICATION OF T/R HANGER BEARINGS, IT WAS NOTED THAT THE AFT HEAT SHIELD WAS FREE TO ROTATE, UP ON FURTHER INSPECTION IT WAS FOUND THAT THE AFT SPANNER NUT WAS LOOSE, BUT THE LOCK WASHER WAS STILL IN THE LOCK POSITION. RECORDS SHOW THAT THIS PART WAS NEVER TAKEN APART OR WORK ON SINCE THE AC LEFT THE FACTORY. (TC NR 20080129003)                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  UO H2SW    E1GL                 
20080220000802008022000080WP  2008       2          20         CA080129005      120080128G6310C1883           SPRAG CLUTCH                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1620                                                           (CAN) DURING OVER HAUL, THE CAGE OF THE SPRAG CLUTCH WAS FOUND CRACKED IN 8 PLACES. (TC NR 20080129005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  O  H11NM   1E4                  
             20080520     EA  2008       5          20         CA080130001      120080128G3246AN620A          BOLT            AIRCRFTPRDTS            DHAV  DHC6  DHC6100     2802610EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  FLOAT ASSY      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION, THE TIE ROD TO FUSELAGE LUG WAS FOUND TO HAVE ONE OF THE (2) ATTACH BOLTS BROKEN. THE BREAK OCCURRED IN THE THREADED AREA OF THE BOLT. BOTH BOLTS WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. THIS AC IS OPERATED IN A GENERALLY ROUGH WATER ENVIRONMENT, WITH SWELLS, LARGE WAVES AND LARGE BOAT WAKES MAKING THE LANDING AREA CHALLENGING AT TIMES. (TC NR 20080130001)                                                                                                                                                                                                                                                                                                                                        1H72 3T3  TRTA9EA    E4EA    6  CP15EA    
20080220000812008022000081EU  2008       2          20         CA080130002      120080115G321229022979        HEAD            AIRCRUISERS             BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              EMERGENCY FLOAT LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AN INSPECTION THE EMERGENCY FLOAT SYS WERE DEPLOYED ACCIDENTALLY. (2) REFURBISHED KITS (PN:28022969) WERE ORDERED. BOTH VALVE ASSY (PN: 105-E-0031) WERE REBUILDED INCLUDING SHEARHEAD ASSY. (PN:29022979) NITROGEN PRESSURE WAS BROUGHT UP TO 3200PSI AND CHECK FOR LEAK. AFTER 2 DAYS PRESSURE STARTED TO DROP SLOWLY. BOTTLE WERE REFILLED WITH NITROGEN TO 3200 PSI AND PRESSURE CONTINUE TO DROP SLOWLY ON LT SIDE. BOTTLE WAS REMOVED FROM FLOAT AND CHECK FOR LEAK. LEAK WAS FOUND COMING FROM SHEARHEAD ASSY. SHEARHEAD WAS REPLACED AND FLOAT RETURNED TO SERVICE. (TC NR 20080130002)                                                                                                                                    1G72 3U3  U  H3EU    E4CE                 
20080221000012008022100001CE  2008       2          21         CA080131003      120080116G7110B140048         LATCH                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  COWLING         INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       309                                                            (CAN) THE LOWER FWD COWLING HOOK AND CAM ASSY FAILING TO LATCH WITH THE UPPER COWL ASSY WHEN INSTALLING THE COWLS ON THE ENGINE. IT IS POSSIBLE TO HAVE THE ALIGNMENT MARKS INDICATE A SUCCESSFUL LATCH WHEN IN FACT THE HOOK MAY HAVE MISSED THE CAM DURING ROTATION OF THE HOOK. A THOROUGH VERIFICATION OF A SUCCESSFUL LATCH, IN ADDITION TO THE VISUAL ALIGNMENT MARKS INDICATION, IS REQUIRED WHEN INSTALLING ENGINE COWLS. (TC NR 20080131003)                                                                                                                                                                                                                                                                                           1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20080221000022008022100002NE  2008       2          21         CA080131008      320080109G6114                WASHER          HAMSTD                  DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            603   B1991                               B1991           (CAN) PROP MODEL 2D30-237 S/N B1991. UPON RECEIPT CUSTOMER WAS COMPLAINING THAT PROP WAS NOT CYCLING. ONCE PROP WAS DISMANTLED A CRACKED THRUST BEVEL WASHER WAS NOTICED. THE THRUST WASHER IS CRACKED RIGHT THROUGH, CAUSING THE BLADE TO HANG UP INSIDE OF THE BARREL. THIS UNIT HAS 603.3 HRS SLOH IN NOV 17/05. (TC NR 20080131008)                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3R3  RRCA806    5E1     5  CP206     
20080319001792008031900179CE  2008       3          19         CA080201001      120080130G3230C6189CL         CHAIN                                   BEECH 99    99          1154002CE  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  NLG             BENT            W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, A LOUD NOISE WAS HEARD AND THE GEAR FAILED TO RETRACT (3) GREEN INDICATION DURING INSP THE AFT NOSE GEAR CHAIN WAS BROKEN AND THE REMOTE CIRCUIT BREAKER WAS FOUND POPPED NOSE CHAIN AND MASTER LINK REPLACED AND SYS INSPECTED 5 GEAR CYCLES C/O AND NO FAULTS FOUND RECORDS INSPECTED FOR COMPLIANCE WITH AD 72-10-04 PART A FOUND CARRIED OUT AT INTERVALS NOT EXCEEDING 100 HOURS (TC NR 20080201001)                                                                                                                                                                                                                                                                                                                   1L72 3T3  T  A14CE   E4EA    6  CP15EA    
             20080520         2008       5          20         CA080201002      220080201G74141051324         SPRING                      107902010                                                                                                   IMPULSE COUPLINGMISMANUFACTURED W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1220                                                      (CAN) MAGNETO WAS RECEIVED ON AN ENG FOR INSP, DUE TO VIBRATION. MAG ROTOR WAS SPUN BY HAND TO INSPECT BEARINGS AND WHEN THE IMPULSE COUPLING FLYWEIGHTS CONTACTED THE STOP PINS THE FORCE REQUIRED TO WIND UP THE SPRING WAS FOUND TO BE LESS THAN NORMALLY REQUIRED. THE MAG HAD A 500 HOUR INSP PERFORMED 116.2 HOURS AGO AND IT APPEARS THAT THE SPRING WAS IMPROPERLY WOUND AT THAT TIME. REPAIR OF MAG IS BEING HELD OFF PENDING ESTIMATE OF ENTIRE ENGINE. (TC NR 20080201002)                                                                                                                                                                                                                                                                                                     
             20081104     NE  2008       11         4          CA080204001      220080201G7261                OIL SYSTEM                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              NR 1 ENGINE     OVERSERVICED    W      BE  EMER. DESCENT           ENGINE SHUTDOWN                                                         WJ INADEQUATE Q C            WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DUE TO HIGH OIL TEMP INDICATION, NR 1 ENGINE WAS SHUTDOWN BY THE CA, ACFT LANDED IN IAD WITHOUT INCIDENT AND TAXIED TO THE GATE UNDER ITS OWN POWER.  MAINT INSPECTED ACFT. INVESTIGATION OF ENGINE WAS BELIEVED TO BE OVER SERVICED. WHEN MAINT OPENED THE OIL TANK APPROX. 3 QUARTS OF OIL SPILLED OUT OF THE TANK. SUSPECT THE REMOTE REPLENISHMENT SYS TO BE AT FAULT FOR THE OVER SERVICING AND HAS PLACED IT ON MEL. AFTER PROPER SERVICING LEVELS ARE MEET AND UNEVENTFUL ENGINE RUNS ARE CARIED OUT THEY PLAN TO PUT THE ACFT BACK INTO SERVICE.                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
20080319001802008031900180NM  2008       3          19         CA080204004      120080131G32328290018013      ACTUATOR                                DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  RT MLG DOOR     UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       21658166                                                       (CAN) RT MAIN GEAR DOOR CAUTION LIGHT AFTER T/O. GEAR CYCLED WITH NO CHANGE, FLIGHT RETURNED TO  BASE.  MAINT SUSPECTS THE FWD DOOR ACTUATOR TO BE AT FAULT. THE ACTUATOR WAS REPLACED AND FUNCTION CHECKS WERE C/O SERVICEABLE. THE ACTUATOR WAS REPAIRED 166 HOURS AGO, I HAVE REQUESTED A TEARDOWN REPORT AND WILL UPDATE FURTHER WHEN THE INFORMATION IS AVAILABLE. CURRENT A/C HOURS: 43033:33 CYCLES: 47150 (TC NR 20080204004)                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20080319001822008031900182NE  2008       3          19         CA080204005      220080204G72503024211         TURBINE WHEEL                                                              PWA   PT6   PT6A135     52043NE                              ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7075                                                           (CAN) THE CT DISK WAS FOUND WITH (4) VISUAL CRACKS AT (3) OF THE FIRTREES. THE CRACKS ARE LOCATED AT THE EDGE OF THE TOP SERRATION RADIUS WITH THE FIRTREE FACE. THE CRACKS ARE BELIEVED TO BE RELATED TO CORROSION, THEY ARE QUITE OPEN WITH SIGN OF OXIDATION. CRACKS WERE NOTICED VISUALLY AFTER THE REMOVAL OF CORROSION AT THE EDGE ON THE FIRTREE FACE SIDE. THE FPI TEST BEFORE AND AFTER THE REMOVAL OF CORROSION COULD NOT DETECT THE CRACKS. INVESTIGATION IS ON-GOING FURTHER RESULT WILL FOLLOW. (TC NR 20080204005)                                                                                                                                                                                                                       4  T          E4EA                 
20080319001852008031900185SW  2008       3          19         CA080205004      120080201G5302427034851103    SUPPORT                                 BELL  427   427         1182207SW                                                               T/R GEARBOX     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       631                                                            (CAN) T/R GEARBOX SUPPORT CAST SURFACE FOUND CRACKED AT LWR FWD LEG, ATTACHMENT POINT FOR THE VERTICAL FIN. (TC NR 20080205004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U      R00001RC                     
20080319001862008031900186EU  2008       3          19         CA080205005      120080121G7603350A57105721    BALL JOINT                              SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              THROTTLE LINK   WORN            W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHEN THROTTLE WAS RETARDED DURING ENGINE START, T4 CONTINUED TO INCREASE. EMERGENCY SHUTOFF PULLED AND ENGINE MOTORED AS T4 REACHED 900C FOR 2 SECONDS.  INVESTIGATION FOUND THE THROTTLE LINK DISCONNECTED BUT THE LOCKING PIN WAS PROPERLY ENGAGED AND IN THE PROPER POSITION. INCIDENT WAS DUPLICATED 2 OUT OF 3 TIME ON TESTING. PARTS INSPECTED AND FOUND, END EQUIPPED AND BALL JOINT BOTH WORN. (TC NR 20080205005)                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E19EU                
             20081104     WP  2008       11         4          CA080205007      220080129G72603588941         BEARING                                 SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  GEARBOX         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) TACH/GEN IDLER ASSY DUAL SPUR GEAR, CENTER ANTI FRICTION BEARING FOUND WITH AN UNUSUALLY HIGH AMOUNT OF RADIAL PLAY AND WAS EXTREMELY ROUGH WHEN TURNED OVER BY HAND. THE ENGINE WAS REMOVED DUE TO CARBON STEEL PLATELETS FOUND IN THE OIL SAMPLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20080319001882008031900188SW  2008       3          19         CA080205008      120080204G7603540122519       POWER CABLE                             GULSTM690TP 690A        0141722SW  GARRTTTPE331TPE3315251K      NM  HARTZLHCB3T HCB3TN5     GL  POWER LEVER     FROZEN          W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) DURING A TEST FLIGHT, THE LT POWER LEVER CABLE FROZE AND WOULD NOT RESPOND TO INPUTS. THE OAT AT THE TIME WAS -28 DEG C. THE POWER SETTING WAS AT MAX ITT FOR TEST PURPOSES.  SINCE THE PILOT COULD NOT REDUCE POWER, THE ENGINE WAS SHUTDOWN AND THE PROPELLER WAS FEATHERED. THE AC RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. UPON INVESTIGATION, MOISTURE WAS FOUND IN THE POWER LEVER CABLE. THE MOISTURE WAS REMOVED FROM THE CABLE AND THE CABLE WAS INSPECTED SERVICEABLE. THE AC WAS RETURNED TO SERVICE. (TC NR 20080205008)                                                                                                                                                                                          1H72 3T4  T  2A4     E2WE    6  CP15EA    
             20081104     NE  2008       11         4          CA080206004      220080116G7200                ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              LEFT            VIBRATION       W      AE  UNSCHED LANDING         ENGINE SHUTDOWN                                                         E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA                                          807605                      (CAN) CREW REPORTED SEVERE NOISE AND VIBRATION FELT ON LT ENGINE. SHUT ENGINE DOWN AS PRECAUTION AND RETURNED TO FIELD. ENGINE/QEC REMOVED AND REPLACED. SIGNIFICANT DAMAGE TO TURBINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20080319001942008031900194NE  2008       3          19         CA080206008      220080117G7320                COUPLING                                BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE                              FUEL SYSTEM     WORN            W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          93137                       (CAN) DURING CRUISE, THE ENGINE PARAMETERS WERE OBSERVED TO INCREASE REACHING NEAR MAXIMUM LIMITS. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND PERFORM A SINGLE ENGINE LANDING. POST FLIGHT INVESTIGATION REVEALED A WORN COUPLING BETWEEN THE FUEL PUMP AND FUEL CONTROL. (TC NR 20080206008)                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20080319001962008031900196NE  2008       3          19         CA080206009      220080122G7261                OIL SYSTEM                              CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                              ENGINE          EMPTY           W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB AT APPROX FL190, THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND PERFORMED A COMMANDED SHUTDOWN OF THE ENGINE. THE AC WAS DIVERTED TO AN ALTERNATE LANDING SITE.  POST FLIGHT INSP REVEALED NO INDICATION OF OIL ON THE SIGHT GLASS. NO SIGNS OF EXTERNAL LEAKAGE. THE ENGINE HAS BEEN REMOVED AND RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED TO TC WHEN AVAILABLE. (TC NR 20080206009)                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA22CE   E00059EN             
20080319001972008031900197NE  2008       3          19         CA080206010      220080123G7261                OIL SYSTEM                              DHAV  DHC8  DHC8201     2809001NM  PWA   PW120 PW123            NE                              ENGINE          LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                          AT0006                      (CAN) THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. SIGNS OF EXTERNAL LEAKAGE WERE FOUND AT POST FLIGHT INSP. THE ENG HAS BEEN REMOVED FOR INVESTIGATION AND REPAIR.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080206010)                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE                
20080319001982008031900198NE  2008       3          19         CA080206011      220080124G73103035989         TUBE                                    FOKKERF27   F27MK50            EU  PWA   PWA120PW125B           NE                              FUEL SYSTEM     PUNCTURED       W      FEA ACTIVATE FIRE EXT.      ENGINE SHUTDOWN         UNSCHED LANDING                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                          124341                      (CAN) DURING CLIMB, AN ANTI-ICE WARNING FAULT WAS NOTED. 20 MINUTES LATER, AN ENGINE FIRE WARNING ANNUNCIATED. THE CREW FIRED ONE EXTINGUISHER BOTTLE AND SHUTDOWN THE ENGINE AND AN EMERGENCY WAS DECLARED. POST LANDING INVESTIGATION REVEALED THAT AN ENGINE SUPPLIED FUEL TUBE (PN 3035989) HAD BEEN PUNCTURED BY APPARENT FRETTING AND ABRASION AGAINST AN AIRFRAME SUPPLIED WIRING HARNESS.  THE SUSPECTED TUBE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE FURNISHED AS AVAILABLE. (TC NR 20080206011)                                                                                                                                                                                                                    2H72 4T4  TRTA817    E20NE                
20080319001992008031900199NE  2008       3          19         CA080206012      220080124G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          70322                       (CAN) THE CREW NOTED A LOW OIL PRESSURE WARNING DURING CRUISE AND ELECTED TO SHUTDOWN THE ENGINE. POST FLIGHT INSPECTION REVEALED OIL RESIDUE IN THE TAIL PIPE AND METAL PARTICLES ON THE OIL FILTER. THE ENGINE WAS REMOVED FOR INVESTIGATION.  MFG WILL CONTINUE TO INVESTIGATE THE EVENT AND REPORT FINDINGS ONCE ROOT CAUSE IS ESTABLISHED. (TC NR 20080206012)                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
20080319002002008031900200NE  2008       3          19         CA080206013      220080129G7261                OIL CAP                                 CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ENGINE          LOOSE           W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         WJ INADEQUATE Q C            WARNING INDICATION                                  CLCLIMB          1                      CA                                          70730                       (CAN) DURING CLIMB AT FL150, THE LOW OIL PRESSURE WARNING ANNUNCIATED AND PRESSURE WAS OBSERVED TO DROP TO 35 PSIG. THE ENGINE WAS SHUTDOWN BY THE CREW WHEN THE PRESSURE REDUCED TO 20 PSIG AND THE AC RETURNED TO BASE.  POST FLIGHT INVESTIGATION INDICATES THAT THE OIL FILLER CAP MAY NOT HAVE BEEN PROPERLY SECURED PRIOR TO THE FLIGHT. (TC NR 20080206013)                                                                                                                                                                                                                                                                                                                                                                              1L72 4F4  F  A22CE   E1NE                 
20080319002012008031900201EA  2008       3          19         CA080206014      220080104G8530SL32006WA21P    CYLINDER HEAD                                                              LYC   O320  O320E2D     41508EA                              ENGINE          CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       292                                                            (CAN) CYLINDER HEAD FOUND CRACKED AT OIL RETURN LINE BOSS, AT PIPE-THREADED FITTING HOLE. (TC NR 20080206014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          3  O          E274                 
20080319002022008031900202NE  2008       3          19         CA080207005      120080108G6410SB7306102       BEARING                                 SKRSKYS92   S92A               NE  GE    CT7TS CT78A       30136NE                              T/R BLADE       DEBONDED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       42         A11100355                                           (CAN) UPON A SCHEDULED 50HR INSP, A BOROSCOPING OF THE TAIL ROTOR BLADES HAD BEEN CARRIED OUT, TO CHECK PIVOT BEARINGS FOR DEBONDING FROM TAIL ROTOR SPARE. ON ONE TAIL ROTOR BLADE A BEARING WAS SUSPECTED TO BE DEBONDED. UPON FURTHER INSPECTION WITH REMOVAL OF THE BEARING FROM THE TAIL ROTOR BLADE, IT WAS CONFIRMED THAT THE INNER PLATE OF THE PIVOT BEARING WAS TOTALLY SEPARATED FROM THE BLADE SPAR. AFTER LOOKING AT THE BEARING PLATE IT WAS CLEARLY VISIBLE THAT THE ADHESIVE MATERIAL USED TO BOND THE PLATE TO THE SPAR HAD ONLY ADHERED TO THE PLATE OF THE BEARING AND NOT TO THE SPAR. (TC NR 20080207005)                                                                                                                  2G72 4U4  U  R00024BOE8NE                 
20080319002032008031900203NE  2008       3          19         CA080207006      220080129G7310230360801       LINE                                    BAC   146   146200A     1500266EU  LYC   ALF502ALF502R5    41580NE                              FUEL SYSTEM     MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       307843062                                                      (CAN) THE ENGINE FUEL LINES WERE FOUND NOT TO BE CORRECTLY INSTALLED IAW AMM 73-10-08-401.  TUBES , FUEL SYS, REMOVAL / INSTALLATION.   AFFECTIVITY: ON AC ALL - DATE: EEP 01/02 (P).  THIS HAS RESULTED IN (3) OF THE (4) ENGINES FUEL LINES TO CHAFE WITH THE ENG INLET ANTI-ICE AIR SUPPLY TUBE. ONE OF THE ENGINE FUEL LINES WAS CHAFED THROUGH AND WAS ALLOWING FUEL TO LEAK OUT. (TC NR 20080207006)                                                                                                                                                                                                                                                                                                                                      2H74 4F4  F  A49EU   E6NE                 
             20080520         2008       5          20         CA080207007      420080130G2562ELT97A2560000000ELT                                     DORNERDO32  DO328100    2996000NM  PWA   119   PW119C           NE  HARTZLHDE6C HDE6C3B     NE                  FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       134                                                            (CAN) NUMEROUS UNCOMMANDED ELT ACTIVATIONS WITH ELT97.  HAVE HAD ACTIVATIONS WITH THE AC INFLIGHT AND PARKED ON THE APRON. THE LASTEST WAS WITH ELT S/N-4584 ON JANUARY 30, 2008.  THE AC HAD BEEN PARKED ON THE APRON FOR ROUGHLY 2 HOURS WHEN THE ELT SIGNAL WAS DETECTED. ALL ELTS HAVE BEEN CONFIRMED AS DEFECTIVE AFTER AN ACTIVATION BY REPLACEMENT OR BY SWAPPING WITH ANOTHER AC.  DEFECTIVE ELTS HAVE BEEN RETURNED TO THE MFG FOR REPAIR OR REPLACEMENT. ATTEMPTS TO GET SUPPORT FROM MFG HAVE YEILDED LIMITED RESULTS. (TC NR 20080207007)                                                                                                                                                                                           2H72 4T4  TRTA45NM   E20NE   6  CP34NE    
20080319002042008031900204EA  2008       3          19         CA080207010      220080204G7322105217          CARBURETOR                              CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              ENGINE          LOOSE           W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA            731                                                       (CAN) CARB HEAT SEEMED TO HAVE A SLIGHTLY EXCESSIVE DROP AT HIGHER RPM. (TC NR 20080207010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274                 
20080319002052008031900205EU  2008       3          19         CA080207011      120080131G6130312089001       PROP BRAKE                              AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  NR 2            SEIZED          W      F   ACTIVATE FIRE EXT.                                                                              JA WARNING INDICATION        FLAME/FIRE                                          TXTAXI/GRND HDL  1                      CA                                          PCE120893                   (CAN) AFTER ARRIVAL AT DESTINATION, THE AC TAXIED TO THE TERMINAL. PRIOR TO PASSENGER DEPLANING, THE CREW OBSERVED A MASTER WARNING (PROP UNLOCK). THE F/O REPORTED THAT THE NR 2 ENG WAS ON FIRE AND THE NR 2 CONDITION LEVER WAS SELECTED TO SHUTOFF POSITION. THE F/O OBSERVED THAT THE FIRE CONDITION WAS STILL EVIDENT AND THUS THE GROUND ENGINE FIRE CHECK LIST WAS CARRIED OUT. NO FIRE INDICATION WAS OBSERVED ON THE FLIGHT DECK AND INSPECTION OF THE ENG AND NACELLE BY MAINT FOUND NO INDICATION OF FIRE. THE PROP BRAKE REPLACEMENT PROCEDURE WAS COMPLETED, SYS CHECKED SERVICEABLE AND THE AC RETURNED TO SERVICE. (TC NR 20080207011)                                                                                          2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20080319002062008031900206CE  2008       3          19         CA080208001      120080206G561050420066317     WINDOW                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  LT COCKPIT      DEPARTED        W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMBOUT AT APPROX 3PSI DIFFERENTIAL, THE LT COCKPIT SIDE WINDOW BLEW OUT OF AIRCRAFT.  IT IS DIFFICULT TO DETERMINE THE CAUSE AS THERE IS VERY LITTLE REMAINING OF THE ORIGINAL WINDOW. (TC NR 20080208001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20080520         2008       5          20         CA080208002      420080208G2562AK450           ELT                                     BEECH 60    60          1153602CE  LYC   O541  TIO541E1C4  41536EA  HARTZLHCF3Y HCF3YR2     GL                  FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN TESTING THE ELT AT ITS ANNUAL INSP THE ELT HAD NO MODULATION AND NO OUTPUT POWER. THE ELT REPLACED WITH A SERVICEABLE UNIT. (TC NR 20080208002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A12CE   E10EA   5  CP31EA    
20080319002072008031900207NE  2008       3          19         CA080208003      220080204G721070BM052000      REDUCTION GB                            SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                                              MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5479 2482                                                      (CAN) DURING DAILY INSPECTION SMALL FLAKES WERE FOUND ON THE NON-MAGNETIC CHIP PLUG ON (MODULE) MO 5.  ENGINE OIL WAS CHANGED OIL FILTER WAS CHANGED ALL MAG PLUGS INSPECTED AND CLEANED. A/C FLEW FOR 11.1 HRS AND SMALL FLAKES WERE FOUND ON SAME PLUG. A/C WAS GROUNDED AT THIS TIME AND MFG WAS INFORMED.  A OIL SAMPLE WAS SENT FOR EVALUATION AND CAME BACK AS NORMAL. MFG HAS DECIDED TO REPLACE THE MO 5. (TC NR 20080208003)                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E00054EN             
20080319002082008031900208EA  2008       3          19         CA080208005      220080129G8530734352          PUSHROD                                 MAULE M5    M5235C      5460135SO  LYC   O540  O540J1A5    41532EA  HARTZLHCC2Y HCC2YR1     GL  ENGINE          DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1235                                                           (CAN) THE INTAKE AND EXHAUST PUSHRODS LOCATED AT THE NR1 CYL POSITION WERE NOT DRILLED THROUGH ON ONE END. THIS WOULD NOT ALLOW OIL TO TRAVEL UP THE PUSHROD TO THE ROCKER. (TC NR 20080208005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  O  3A23    E295    5  CP920     
20080319002122008031900212CE  2008       3          19         CA080211001      120080207G27201303800033      TRANSDUCER                              BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  RUDDER BOOST    FAILED          W      C   ABORTED TAKEOFF                                                                                 F  FLT CONT AFFECTED                                                             TOTAKEOFF        1                      CA       188  188                                                       (CAN) THE AC WAS DISPATCHED ON A MEDIVAC FLIGHT AND UPON STARTING THE TAKEOFF ROLL AN UNCOMMANDED RUDDER INPUT WAS FELT BY THE PILOTS. THE AC RETURNED TO THE HANGER WHERE MAINT BEGAN TO TROUBLESHOOT THE PROBLEM. IT WAS DISCOVERED THAT THE LT RUDDER BOOST TRANSDUCER (P/N130-380003-3) FAILED WHICH SIMULATED ENGINE FAILURE AND CAUSED THE RUDDER BOOST SYS TO ACTIVATE. THE TRANSDUCER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080211001)                                                                                                                                                                                                                                                                                  2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20081222     CE  2008       12         22         CA080211002      120080205G2750552500079       ROLLER                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              CENTER FLAP AFT OUT OF ADJUST   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CAMPAIGN NOTICE 851-27-50-043, FLAP CTR AFT BEARING INSTALLATION, COMPLIED WITH. NO FAULTS FOUND ON LT FLAP INSTALLATION. RT FLAP AFT CENTER ROLLER BEARING FOUND TIGHT, BEARING WOULD NOT TURN UNLESS FLAP WAS HELD WITH PRESSURE APPLIED. NO DAMAGE TO BEARING OR SUPPORT FOUND. AFT CENTER ROLLER BOLT ADJUSTED IAW MM 27-51-04, PG 208 PARA B-5-B(2).  WORK DOCUMENTED ON ASD-MP-01 REPORT NR859-02/04/08.                                                                                                                                                                                                                                                                                                                            1L72 4F4  F  A22CE   E1NE                 
20080319002142008031900214EA  2008       3          19         CA080211006      220080208G73103011849         LINE                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  FUEL SYSTEM     CRACKED         W      A   UNSCHED LANDING                                                                                 KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) PILOT REPORTED HEAVY GAS ODOR IN COCKPIT AFTER TAKEOFF,  ACCOMPANIED BY A MIST. MAINT ENGINEER FOUND A CRACKED FUEL LINE IN THE  NR 2 ENGINE NACELLE THAT CONNECTS THE START CONTROL UNIT TO THE FUEL CONTROL UNIT CAUSING A FUEL LEAK THAT WAS SUBSEQUENTLY SUCKED INTO THE ENGINE COMPRESSOR SECTION AND THEN TRANSMITTED TO THE CABIN OF THE AC THROUGH THE BLEED AIR SYS. (TC NR 20080211006)                                                                                                                                                                                                                                                                                                                                         1L72 3T4  T  A14CE   E4EA    5  CSTC      
20080319002152008031900215NM  2008       3          19         CA080211007      120080207G3213101683          ROLLER          MESSIER                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  STRUT           SEIZED          W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA                  DEC128384                                           (CAN) AFTER SELECTING LANDING GEAR DOWN THE LT MAIN GEAR REMAINED UP, THE LANDING GEAR WAS CYCLED UP AND DOWN AGAIN, THE LT GEAR CAME DOWN NORMALLY, (3) GREENS. THE AC WAS FERRIED BACK TO BASE, GEAR DOWN, FOR MAINT.  AFTER CARRYING OUT (2) GEAR SWINGS ON JACKS THE LT GEAR REMAINED UP ON THE 2ND DOWN SELECTION, APPROX (1) MINUTE LATER THE LT GEAR RELEASED AND EXTENDED TO DOWN AND LOCKED. IT WAS DISCOVERED THAT THE UPLOCK ROLLER ON THE SHOCK STRUT ASSY WAS SEIZED, THE ROLLER WAS REMOVED LUBRICATED AND RE-INSTALLED. FURTHER RETRACTIONS AND EXTENSIONS WERE CARRIED OUT WITHOUT ANY PROBLEMS, AC RETURNED TO SERVICE. (TC NR 20080211007)                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080520     NM  2008       5          20         CA080211009      120080204G271019004212401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401 AND P/N 190-04209-401, RT P/N 190 -05550-401 AND P/N 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 5 AND J/C 27-11-00-003-RT/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211009)                                                                                                                                                                                            2L72 4F4  FRTA57NM   E00070EN             
             20080520     NM  2008       5          20         CA080211011      120080111G271019004212401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSPECTION ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401 AND P/N 190-04209-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REF J/C 27-11-00-003-LT/1 AND J/C 27-11-00-003-RT/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. AIR CANADA FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211011)                                                                                                                                                                                     2L72 4F4  FRTA57NM   E00070EN             
             20080520     NM  2008       5          20         CA080211012      120080123G271019004212401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NR 128, 165 AND J/C 27-11-00-003-RT/2 SNAGS NR 87, 166. THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643 C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 2635 C02 CHECK. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211012)                                                     2L72 4F4  FRTA57NM   E00070EN             
             20080520     EA  2008       5          20         CA080211013      120080210G2720274001          PCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              RUDDER          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            4499                                                      (CAN) TASK NR RJ2-27-900-714 FOR THE BACKLASH AND FUNCTIONAL CHECK OF RUDDER CONTROL SYS WAS CARRIED OUT ON THIS AC DURING A HEAVY MAINT CHECK. TEST RESULT PARAMETERS WERE FOUND BEYOND LIMITS. FURTHER INVESTIGATION DURING RECTIFICATION LEAD TO THE DISCOVERY OF THE NR 2 RUDDER PCU LINKAGE ROD BEING FOUND COMPLETELY SHEARED OFF.  THERE WERE ALSO DAMAGE TO THE RUDDER ATTACH FITTING AND THE VERTICAL STABILIZER BRACKET.  A NEW PCU IS ON ORDER AND THE FAILED UNIT WILL BE REPLACED BEFORE AC IS RELEASED FROM HEAVY CHECK. ENGINEERING DEPART HAS BEEN CONTACTED FOR DAMAGE EVALUATION AND POSSIBLE ISSUE OF A REPAIR EO FOR THE RUDDER FITTING AND BRACKET. THOSE UNITS WILL BE REPLACED AS WELL IF THEY ARE FOUND BEYOND REPAIR. I2L72 4F4  FRTA21EA   E15NE                
             20080520     NM  2008       5          20         CA080211014      120080131G271017005825401     CONTROL CABLE                           EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING CONTROL CABLES INSP ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P/N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB OF THE RIB 12, 15, 17 AND AT RIB 20.  FLEET ENGINEERING AS BEEN ADVISED (TC NR 20080211014)                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA56NM   E00063EN             
             20080520     NM  2008       5          20         CA080211015      120080207G271017005825401     CONTROL CABLE                           EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 170-05825-401, P/N 170-05826-401, RT PN 170-05827-401, PN 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB OF THE 17  FLEET ENGINEERING HAVE BEEN ADVISED (TC NR 20080211015)                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA56NM   E00063EN             
20080319002172008031900217SW  2008       3          19         CA080211017      120080208G2913206076030101    PUMP                                    BELL  206   206L3       1182108SW                                                               HYDRAULIC SYS   DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, AC LOST HYDRAULICS. AC LANDED SAFELY. MAINT FOUND HYDRAULICS PUMP SPLINE ROUNDED OFF. TACH GENERATOR SPLINES WORN AS WELL. (TC NR 20080211017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U      H2SW                         
20080319002192008031900219CE  2008       3          19         CA080211018      120080206G3233508202085       ACTUATOR                                BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  NLG             FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA            1711                                                      (CAN) DURING DESCENT INTO INTENDED AIRPORT THE NLG INDICATOR INTRANSIT LIGHT STAYED ILLUMINATED WHEN LANDING GEAR EXTENDED. MAIN GEAR DOWN AND LOCKED LIGHT WERE GREEN. A FLY-BY WAS CARRIED OUT WITH GROUND MAINT VERIFYING THAT THE NLG WAS INDEED ONLY HALF WAY DOWN WITH MAINS FULLY DOWN. AN EMERGENCY EXTENSION WAS ATTEMPTED AND FAILED TO EXTEND THE NLG. THE CREW DECLARED AND EMERGENCY. A LANDING WAS CARRIED OUT WITH ENGINES SHUTDOWN AND PROPS FEATHERED. THE AC WAS LANDED WITH A TOTAL NLG COLLAPSE. THE AC WAS REMOVED FROM RUNWAY. (TC NR 20080211018)                                                                                                                                                                        1L72 3T4  T  A14CE   E4EA    6  CP15EA    
             20080520     CE  2008       5          20         CA080211019      120080104G282020282004500R    SELECTOR                                CESSNA172   172M        2072418CE  THIELTTAE125TAE12501    59300EU                              FUEL SYS        MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. (TC NR 20080211019)         1H71 3O3  BNT3A12    E00069EN             
20080319002212008031900221EA  2008       3          19         CA080212001      120080212G5711C6WM10271       ADAPTER                                 DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  SPAR            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSEMBLY (P/N C6WM1027-1) INSPECTION FOR CRACKS) A CRACK WAS FOUND ON THE LT FRONT SPAR ADAPTER. REPLACED LT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NR 61542. (TC NR 20080212001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081229     CE  2008       12         29         CA080212003      120080201G575355250007        SUPPORT                                 CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              TE FLAP         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A CAMPAIGN NOTICE OF THE RT FLAP CENTER BRG INSTALLATION, BOTH OF THE AFT FLAP BEARINGS WERE FOUND LOOSE AND WORN DUE TO THE LOCATING PIN ON THE BEARINGS NOT INSTALLED INTO MATING HOLES OF FLAP RIB EXTENSIONS.  FLAP ROLLER PN KJS 112603 AND BOTH CENTER AFT FLAP ROLLER SUPPORT BRGS P/N 5525000-79 WERE REPLACED.FLAPS FUNCTION CHECK SERVICEABLE AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                              1L72 4F4  F  A22CE   E1NE                 
20080319002232008031900223EA  2008       3          19         CA080212004      120080129G5411C6WM10271       ADAPTER                                 DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  SPAR            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSY (P/N C6WM1027-1) INSP FOR CRACKS) A CRACK WAS FOUND ON THE RT FRONT SPAR ADAPTER. REPLACED RT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NO 61542.  ALSO REPLACED WEB SUB ASSY SPAR P/N C6W1030-S102 AND WEB NOSE SPAR C6W1056-62 SRM PSM 1-6-3, CHAPTER 51-10-00 AND 51-30-00. (TC NR 20080212004)                                                                                                                                                                                                                                                                                                                                                      1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20080319002272008031900227EA  2008       3          19         CA080212005      220080208G7320                LINK            BENDIX                  HUGHES269   269C        4470504WP  LYC   O360  HIO360D1A   41514EA                              FUEL INJECTOR   DISCONNECTED    W      R   AUTOROTATION                                                                                    RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) THE COTTER PIN SECURING THE IDLE MIXTURE LINK BLOCK TO THE MIXTURE CONTROL ARM BECAME DISLODGED. THIS ALLOWED THE MIXTURE LINK BLOCK TO BECOME DISCONNECTED FROM THE MIXTURE CONTROL ARM. RESULTING A LOSS OF CONTROL OVER FUEL FLOW TO THE ENGINE AND THE ENGINE RETURNED TO GROUND IDLE POWER. (TC NR 20080212005)                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  4H12    1E10                 
20080319002292008031900229EU  2008       3          19         CA080213001      120080208G2421729722C         GENERATOR       HONEYWELL               AIRBUS310   A310               EU  GE    CF6   CF680C2A5        NE                              APU             CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       3248819916 PP1269                                              (CAN) DURING TROUBLESHOOTING FOR HIGH OIL CONSUMPTION ON THE APU, FOUND A 7 INCHES CRACK ON THE GENERATOR HOUSING. THE IDG WAS REPLACED AND THE UNIT WAS SENT TO THE VENDOR FOR INVESTIGATION. (TC NR 20080213001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA35EU   E13NE                
             20080520     CE  2008       5          20         CA080213002      120080211G3250MC09543022      TUBE                                    CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  NLG STEERING    STUCK           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       828                                                            (CAN) PROBLEM WAS DISCOVERED DURING PRE-INSP RUN UP. WHEN FULL RUDDER DEFLECTION WAS APPLIED THE RUDDER MOVEMENT WAS RESTRICTED AND WOULD ONLY RELEASE WHEN ALTNATE RUDDER PRESSURE WAS APPLIED. (TC NR 20080213002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A19    E223    5  NP50GL    
20080319002312008031900231NM  2008       3          19         CA080213003      120080120G5610070303          WINDSHIELD                              DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  COCKPIT         CRACKED         W      BI  EMER. DESCENT           CABIN DEPRESSURIZATION                                                  O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) WHILE IN CRUISE FLIGHT, THE F/O HEATED WINDSHIELD SHATTERED WITH NO APPARENT WARNING. THE CREW DEPRESSURIZED THE CABIN AND DESCENDED IAW THEIR CHECKLISTS AND CONTINUED THE FLIGHT TO THEIR DESTINATION. THE AC WAS ON A NON REVENUE FLIGHT TO A MAINT FACILITY FOR THE COMPLETION OF A C-CHECK. THE WINDOW HAS BEEN REPLACED AND NO DEFINITIVE REASON FOR THE FAILURE HAS BEEN DETERMINED. THE TT ON THE WINDOW CAN NOT BE ACCURATELY DETERMINED BUT THE WINDOW HAS A MANUFACTURE DATE OF JAN 20, 2000. (TC NR 20080213003)                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080520     GL  2008       5          20         CA080213004      120080206G2133811441A010302   OUTFLOW VALVE                           BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              CABIN PRESSURE  FAILED          W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CLCLIMB          1                      CA       607                                                            (CAN) DURING CLIMB, THROUGH FL270, CABIN ROC (RATE OF CLIMB) INCREASED TO 3000 FPM (FT PER MINUTE), CABIN ALTITUDE STARTED TO CLIMB.  MANUAL PRESSURIZATION WAS SELECTED RESULTING IN AN INABILITY TO REDUCE CABIN ALTITUDE.  AC DESCENDED, EICAS (CABIN ALT) MESSAGE POSTED AND OXYGEN MASKS DEPLOYED.  AN EMERGENCY WAS NOT DECLARED. TROUBLESHOOTING WAS CARRIED OUT, RT SAFETY VALVE FAILED THE TEST. BOTH SAFETY VALVES WERE REMOVED, THE INVESTIGATION IS ONGOING. (TC NR 20080213004)                                                                                                                                                                                                                                                    2L72 4F4  FRTT00005NYE00010LA             
             20080520     GL  2008       5          20         CA080213005      120080103G2133811441A010302   OUTFLOW VALVE                           BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              CABIN PRESSURE  MALFUNCTIONED   W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA       419  419                                                       (CAN) DURING CRUISE AT 45,000 FEET, THE PILOT REPORTED THAT THE CABIN ALT CLIMBED TO 22 000 FT, OXYGEN MASKS DEPLOYED AND AN EMERGENCY DESCENT WAS CARRIED OUT.  WAITING MORE INFO FROM CUSTOMER. THE MFG HAS INSPECTED THE VALVES AND THEY CONCLUDE THE VALVES WERE (NO FAULT FOUND). THE INVESTIGATION IS ONGOING. (TC NR 20080213005)                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTT00005NYE00010LA             
20080319002342008031900234NM  2008       3          19         CA080213006      120080122G3246314353          WHEEL                                   DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  LT MLG          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE DAILY INSP, IT WAS NOTED THAT THE LT MAIN WHEEL WAS LOOSING AIR ON A DAILY BASIS. THE WHEEL ASSY WAS REMOVED AND SENT FOR INSP. INSP REVEALED THAT THE INNER RIM HALF WAS CRACKED AT THE FUSE PLUG AND FURTHER INSP REVEALED CRACKING AT THE BRG RACE. THIS WHEEL WAS REMOVED FOR THE FIRST TIME OFF OF A RECENTLY PURCHASED AC AND TOTAL TIME ON THIS PART IS UNDETERMINED. (TC NT20080213006)                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081229     CE  2008       12         29         CA080213007      120080131G2910SEEDESCRIPTION  HOSE                                    CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              HYD SYS         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1036                                                           (CAN) DURING INSP OF FLAP SYS FOUND 6 HYD HOSES FOR SPEED-BRAKE/LIFT-DUMP ACTUATORS WITH MINOR HYD FLUID SEEPAGE. THE FOLLOWING PN HOSES WERE REPLACED. AE1011925E0087, AE1011925E0094, AE1011925E0121, AE1011888E0132, AE1011924E0103, AE1011933E0086.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRCT00012WIE35NE                
             20080520     EU  2008       5          20         CA080213008      120080208G2913                PUMP                                    AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  HYD SYSTEM      MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) SHORTLY AFTER DEPARTURE, THE CREW OBSERVED A LOW PRESSURE INDICATION ON THE BLUE HYDR SYS. THE AC RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE BLUE SYS PUMP AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080213008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20080520     NE  2008       5          20         CA080213010      320080209G6114                SEAL            HAMSTD      54H60117    LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  PUMP HOUSING    TORN            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ON TAKEOFF FROM AIRPORT, THE CREW OBSERVED A LOW OIL INDICATION ON THE NR 1 PROPELLER. THE AC RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.  MAINT REPLACED THE NR 1 PROPELLER ASSY. THE AC WAS RETURNED TO SERVICE AFTER SATISFACTORY LEAK CHECK AND GROUND RUN. IT WAS DETERMINED THAT THE FLUID LOSS WAS DUE TO A DAMAGED FRONT PROPELLER PUMP HOUSING SEAL (TC NR 20080213010)                                                                                                                                                                                                                                                                                                                                   2H74 4T4  T  A1SO    E282    6  CP906     
             20080521     CE  2008       5          21         CA080213013      120080104G282320282004500R    SELECTOR                                CESSNA172   172M        2072418CE  THIELTTAE125TAE12502114      EU                              FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER TWO FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE SECOND PART. (TC1H71 3O3  BNT3A12    E00069EN             
             20080522     CE  2008       5          22         CA080213014      120080104G282320282004500R    SELECTOR                                CESSNA172   172M        2072418CE  THIELTTAE125TAE1250299       EU                              FUEL SYSTEM     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE THIRD PART. (TC 1H71 3O3  BNT3A12    E00069EN             
20080319002372008031900237GL  2008       3          19         CA080214001      120080212G27202227271400      RUDDER PEDAL                            DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  COCKPIT         CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       3435                                                           (CAN) IT HAS BEEN NOTICED THAT ALTHOUGH THIS AREA IS LUBRICATED IAW THE MFG MAINT SCHEDULE WITH LPS2, THIS AREA CONTINUOUSLY CORRODES TO THE POINT THAT IT AFFECTS THE POSITIONING OF THE RUDDER PEDALS. (TC NR 20080214001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081104     SW  2008       11         4          CA080214002      120080213G7714                DRIVE SHAFT                             SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110U   01514WP  HARTZLHCB3T HCB3TN5     GL  TACH GENERATOR  FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) TROUBLESHOT NO RPM INDICATION. REMOVED TACH GENERATOR FROM RT ENGINE, DRIVE SHAFT WAS STILL STUCK IN THE ENGINE. IT APPEARS THAT THE SHAFT SEPARATED FROM THE ARMATURE INSIDE. REMOVED THE SHAFT, NO DAMAGE TO THE ENGINE DRIVE. INSTALLED SERVICEABLE PART AND TESTED FINE.  (TC NR 20080214002)                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20080319002422008031900242CE  2008       3          19         CA080214005      120080214G27501013800005      DRIVE SHAFT                             BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  FLAP DRIVE      SEIZED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) FLAPS WOULD NOT RETRACT AFTER TAKEOFF AND CIRCUIT BREAKER OPENED. AIRCRAFT RETURNED TO AIRFIELD. FLAP DRIVE SHAFT WAS FOUND SEIZED AND BOUND UP NEAR MOTOR. MOTOR AND DRIVE SHAFT WERE REPLACED. (TC NR20080214005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20080603     NM  2008       6          3          CA080214007      120080121G291082970009325     HYDRAULIC LINE                          DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120            NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       34968                                                          (CAN) WHILE ENROUTE THE "IB ROLL SPL HYD" AND NR 1 "HYD ISO VLV" CAUTION LIGHTS ILLUMINATED. CHECKED THE HYD QUANTITY AND NOTICED NR 1 QUANTITY AT 1.0 AND DECREASING. COMPLETED THE QRH CHECKLIST AND THEN BRIEFED THE F/A AND PASSENGERS. MADE A VISUAL APPROACH AND LANDING WITHOUT ANY FURTHER EVENTS.  MAINT INVESTIGATION DETERMINED THE LEAK TO BE FROM THE NR 1 HYD SYS PRESSURE MANIFOLD ENGINE DRIVEN PUMP INLET PRESSURE TUBE FLARE AND FITTING. THE FLARE WAS FOUND TO BE CRACKED AND THE FITTING HAD EVIDENCE OF PITTING CORROSION. THE TUBE AND FITTING WERE BOTH REPLACED IAW THE AIRCRAFT MM AND SUBSEQUENTLY TESTED SERVICEABLE. (TC NR 20080214007)                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080521         2008       5          21         CA080214008      420080213G25620010009C        ELT                                                                                                                                     CABIN           CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1                                                              (CAN) BATTERY CASE FOUND CRACKED DURING ANNUAL RECERTIFICATION. BATTERY KNOWINGLY NEVER DROPPED. UNKNOWN CAUSE OF CRACK, LOCATED AT BOTTOM OF THE CASE IN ANTENNA STOWAGE CHANNEL. (TC NR 20080214008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
             20080521     WP  2008       5          21         CA080214009      120080114G3260                DOWNLOCK SWITCH                         CVAC  440   440         2422902WP  ALLSN 501D  501D13D     03004GL  ALLSN A6441 A6441FN606  GL  MLG             DEFECTIVE       W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 DEDESCENT        1                      CA                                                                      (CAN) ON APPROACH, ON A FERRY FLIGHT AND WHEN GEARS SELECTED DOWN, THE LT GEAR DID NOT INDICATE DOWN AND LOCKED, LANDING WAS ABORTED.  AFTER COMPLETING THE INDICATION, MALFUNCTION CHECKLIST, FOUND IN FACT THAT THE LT GEAR WAS DOWN AND LOCKED.  FOR PRECAUTIONARY MEASURES IN THE COMPANY PROCEDURES AN EMERGENCY LANDING WAS DECLARED THAN PROCEEDED WITH NORMAL LANDING. FOLLOWING MAINT INVESTIGATION FOUND LT MLG DOWNLOCK SWITCH DEFECTIVE, THE SWITCH WAS REPLACED AND RIGGED IAW MM AND AC RETUNED TO SERVICE. (TC NR 20080214009)                                                                                                                                                                                                   2L72 4R4  T  6A6     E282    6  CP898     
             20080521     NE  2008       5          21         CA080214010      120080209G53403322203         ATTACH FITTING              3035941     SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              SEATBELT        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SUBJECT AC CRASHED ON APPROACH TO LANDING.  OPERATOR REPORTED TO THAT AN AFT-FACING CABIN SEAT BELT ATTACH FITTING FAILED ON IMPACT, PERMITTING THE SEAT BELT TO DETACH.  INSP OF FAILURE SHOWS THAT UNEXPECTED PRYING LOADS CAUSED THE FAILURE OF THE ALUMINUM ATTACH FITTING.  A DESIGN CHANGE IS REQUIRED TO PREVENT SIMILAR OCCURRENCES. I AM THE APPROVAL HOLDER FOR THE MODIFICATION THAT INTRODUCES THESE SEATS INTO THE AC.  HAVE RECOMMENDED THAT THE OPERATOR REFRAIN FROM USING THESE SEATS FOR TAKEOFF AND LANDING UNTIL A FIX CAN BE INCORPORATED. AC IS EN-ROUTE BY TRUCK TO MY FACILITY. I HAVE CONTACTED THE SEAT MFG REQUESTING ENGINEERING ASSISTANCE TO ADDRESS THIS DEFECT. (TC NR 20080214010)                       1G72 3U3  U  H1NE    E1GL                 
             20081230     CE  2008       12         30         CA080214011      120080124G251005142121        SEAT BACK       CESSNA                  CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1C235 1C235LFA    GL  COCKPIT SEAT    BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       4056                                                           (CAN) SEAT BACK FRAME BROKEN JUST ABOVE INSERT ON THE OTBD SIDE. NOTEWORTHY ITEM: THIS SEAT DID HAVE A STEAL BAR INSTALLED IAW AD 2007-05-10. WE DO NOT KNOW WHETHER THIS WAS A CONTRIBUTING CAUSE TO THE FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10    5  NP12EA    
             20080521         2008       5          21         CA080215001      420080207G23704954200001      VIDEO MONITOR                           BOEING767   7673Y0             NM  PWA   4060  PW4060      52119NE                              CABIN           FIRE            W      O   OTHER                                                                                           AB FLAME/FIRE                SMOKE/FUMES/ODORS/SPARKS                            LDLANDING        1                      CA                                                                      (CAN) AFTER LANDING AND AFTER PASSENGERS HAD DEPLANED, THE F/A STILL ONBOARD THE AC NOTICED ONE OF THE BULKHEAD INFLIGHT ENTERTAINMENT MONITORS HAD FLAMES AND SMOKE EMINATING FROM IT.  AFTER INSPECTION OF VIDEO MONITOR, MAINT FOUND A PLUG MELTED AT PIN.  HARNESS WAS DISCONNECTED FROM P1 DISCONNECT ABOVE NO SMOKING SEATBELT SIGN. COAX CABLE ALSO DISCONNECTED. MONITOR REMOVED. FOUND CB ON P-37 PANEL IN E/E COMPT POPPED. VIDEO MONITOR MFR P/N: 02190830-1, MFG CODE: P0173 (TC NR 20080215001).                                                                                                                                                                                                                                   2L72 4F4  FRTA1NM    E24NE                
             20081105         2008       11         5          CA080215002      420080214G31307013348931      DAU                                     LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                                              MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THIS DAU WAS ORIGINALLY REMOVED FROM ANOTHER OPERATOR ACFT WITH THE FAULT, LOSS OF N1 AND N2 INDICATION. MFG TESTED THE UNIT AND RETURNED IT TO SERVICE WITH NO FAULT FOUND, WITH ALL THE APPROPRIATE CERTIFICATION. THE UNIT WAS INSTALLED ON OUR ACFT IN NR1 POSITION WITH THE PROPER FUNCTION CHECK CARRIED OUT. DURING ENGINES RUN, ALL ENGINES INDICATIONS WERE NORMAL. A FEW HOURS LATER, WHILE THE ACFT WAS TAXIING OUT THE NR1 ENGINE INDICATION STARTED TO FLICKER. ACFT RETURNED TO OUR HANGAR WHERE THE DAU NR1 WAS REPLACED. DAU WILL BE RETURNED TO  WILL ALL THE PROPER DOCUMENTATION TO MAKE SURE THIS UNIT GET FINALLY REPAIRED. (TC NR 20080215002)                                                                      2L72 4F4  FRTT00008WIE6WE                 
20080320000112008032000011SO  2008       3          20         CA080215003      120080214G78209948200         MUFFLER                                 PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)FOUND OVER THE PAST YEAR THAT USING PRESSURE TESTING VS VISUAL HAS CAUGHT MANY PIN HOLE LEAKS IN THE MUFFLER. IN THE PAST WE WERE FINDING LARGE CRACKS IN BEHIND WHEN WE PRESSURE TESTED EVERY 200 HOURS WHICH YOU COULD NOT SEE VISUALLY SO WE BEGAN PRESSURE TESTING ALL THE TIME VERSUS VISUAL. ALSO FOUND THAT AFTER INSTALLATION OF NEW EXHAUST, PIN HOLES BEGAN TO SHOW BETWEEN 800-1000 HOURS LATER AND THEN PIN HOLES WOULD BEGIN TO SHOW EVERY 100 HOURS AFTER THAT. REALIZED THAT IF WE HAD NOT PRESSURE TESTED THE SYS, WOULD NOT FIND THE PIN HOLES AND WE WOULD END UP WITH A MAJOR REPAIR 100 HOURS LATER. SO WE NOW PRESSURE TEST THE EXHAUST SYS EVERY 100 HRS COMMERCIAL AND ANNUALLY WITH PRIVATES. THIS HAS LOWER THE OV1L71 3O3  O  2A13    E274    5  NP88614   
             20080521     GL  2008       5          21         CA080215005      220080215G7230                CASE HALF                               BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              COMPRESSOR      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON SPLITTING THE COMPRESSOR CASE HALVES FOR AN INSPECTION, IT WAS NOTED THERE WERE AREAS OF THE PLASTIC COATING THAT WERE MISSING.  CASES REPLACED. (TC NR 20080215005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E4CE                 
20080325000032008032500003SO  2008       3          25         CA080215007      120080209G5520486104          BOLT                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  ELEVATOR STOP   BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE INSP OF THE ELEVATOR STOPS. WHEN THE DOWN STOP WAS PHYSICALLY TEST FOR SECURITY THE BOLT HEAD POPPED OFF. UPON CLOSER INSP THE BOLT WAS CRACKED AND WAS BEING HELD IN PLACE BY THE NORMAL ELEVATOR DOWN PRESSURE. NO OTHER DAMAGE WAS NOTED, BOLT REPLACED AC RETURNED TO SERVICE. (TC NR 20080215007)                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20080521     EA  2008       5          21         CA080215008      220080209G7314RG9080J4A       PUMP                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  FUEL SYSTEM     ERRATIC         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       482                                                            (CAN) RT ENGINE DRIVEN FUEL PUMP REPLACED DUE TO ERATIC PRESSURE INDICATIONS. (TC NR 20080215008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20080521     WP  2008       5          21         CA080215009      120080111G2497                CONNECTOR                               CVAC  440   440         2422902WP  ALLSN 501D  501D13      03004GL  ALLSN A6441 A6441FN606  GL  CONTROL PANEL   DAMAGED         W      EF  ENGINE SHUTDOWN         ACTIVATE FIRE EXT.                                                      GJ MULTIPLE FAILURE          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ON CLIMBOUT, AT 5500FT, THE ADI, HSI AND VSI WENT UNSERVICEABLE AT THE SAME TIME, COMPLETE LOSS OF ELECTRICAL POWER, RT SIDE. AT THE SAME TIME, THE NR 2 ENGINE FIRE WARNING (ILLUMINATED) CAME ON ALL 3 ZONES. CREW COMPLETED ENGINE FIRE DRILL. ATC ADVISED OF THE EMERGENCY, THE AC LANDED WITH NO OTHER INCIDENT REPORTED.  AFTER INVESTIGATION FOUND THE RT AC CONTROL PANEL CONNECTOR DAMAGED AT PIN NR 10.  BOTH THE AC CONTROL PANEL UNIT AND THE CONNECTOR WAS REPLACED AND TESTED SERVICEABLE. A FLEET CAMPAING WAS CARRIED OUT TO INSPECT ALL THE AC CONTROL PANEL CONNECTORS FOR CONDITION AND NO DEFECT DETECTED. (TC NR 20080215009)                                                                                        2L72 4R4  T  6A6     E282    6  CP898     
             20080521         2008       5          21         CA080215010      420080214G22152R5310A         SERVO                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              AUTOPILOT       MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       5702 5702                                                      (CAN) AUTOPILOT UNSERVICEABLE, EICAS MESSAGE (AP FAIL) ON FOR APPROX 3-5 SECONDS, THEN DISAPPEARS.  AUTOPILOT AILERON SERVO FAILED. FAULT CODES 22110239PA1 AND 22110239PA2 RECORDED. (TC NR 20080215010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA56NM   E00063EN             
             20080521     EA  2008       5          21         CA080215011      120080214G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       7867 7867                                                      (CAN) DURING SELECTION OF FLAPS FROM 30 DEG TO 45 DEG ON APPROACH RECEIVED (FLAP FAI) MESSAGE ON EICAS. FLAPS FAILED TO MOVE WITH INDICATION OF 34 DEG. NORMAL LANDING. MAINT INSP FOUND NO ABNORMALITIES. FLAP DRIVE SHAFTS REMOVED AND LUBRICATED IAW  COMPANY POLICY. (TC NR 20080215011)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
             20080521     EU  2008       5          21         CA080215012      120080214G3150B19030W04       DISPLAY                                 UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 LDLANDING        1                      CA       1874 1874                                                      (CAN) THERE HAS BEEN REPORTS OF NUMEROUS SYS FAILURE REPORTS FROM THE VEMD SUCH AS NF/NR, MODULE, OVERLIMITS, LANE FAILURES AND LIGHTING FAILURES AND NONE OF THESE FAILURES ACTUALLY OCURRED.  THIS IS A PROBLEM WITH THE SOFTWARE AND HAS BEEN A PROBLEM ON THESE UNITS WITH YELLOW FAILURES EVERY DAY. (TC NR 20080215012)                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  UNCR0001RD E34NE                
             20081229     CE  2008       12         29         CA080215013      120080207G2810S51812          LINE            CESSNA                  CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE  MCAULY4HFR344HFR34C762  NE  BLADDER VENT    WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7218                                                           (CAN) LT AND RT NACELLE FUEL BLADERS WERE FOUND COLLAPSED. GROUND HANDLER REPORTED AIR RUSHING INTO TANK AFTER FILLER CAP REMOVAL WHILE PREPARING TO FUEL ACFT.  FUEL VENT LINES WITHIN INTEGERAL WING TANK WERE FOUND TO HAVE HARD/BRITTLE RUBBER COUPLER HOSES WHICH LEAKED FUEL INTO THE VENT SYS AND WAS TRAPPED IN A LOW SYS IN THE VENT LINES CAUSING BLOCKED VENT LINES AND COLLAPSING THE BLADDER TANKS DURING FLIGHT. RUBBERS REPLACED AND SYS OPS NORMAL.                                                                                                                                                                                                                                                                             1L72 3T3  TRTA7CE    E4EA    6  C3PNE     
             20080521     EA  2008       5          21         CA080217002      120080211G5610NP13932111      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         BROKEN          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       11342                                                          (CAN) CAPTAINS WINDSHIELD BROKE CLIMBING THROUGH 19000 FT. FOLLOWED QRH AND RETURNED TO FIELD.  WINDSHIELD IS A POST SB CONFIGURATION (TC NR 20080217002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA21EA                        
             20080521     EA  2008       5          21         CA080217003      120080211G5610NP13932111      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       12616                                                          (CAN) ON ROTATION CAPTAINS WINDSHIELD CRACKED. FOLLOWED QRH AND RETURNED TO THE FIELD.  WINDSHIELD IS A POST SB CONFIGURATION. (TC NR 20080217003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA21EA                        
             20080521     EA  2008       5          21         CA080218001      120080216G324190004433        CONTROL UNIT                            CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              ANTI SKID SYS   FAULTY          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA       8195                                                           (CAN) ON LANDING, CREW RECEIVED IB ANTI-SKID CAUTION MESSAGE. AFTER TAXIING CLEAR OF ACTIVE RUNWAY IT WAS DETERMINED BOTH LT MAIN TIRES FLAT. MAINT FOUND MDC FAULT CODES INDICATED FAULTY ASCU. ASCU REPLACED, AXLE INSP. FOR OVERTEMP AND TIRES REPLACED. FUNCTION CHECKS C/O WITH NO FURTHER FAULTS. (TC NR 20080218001)                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E00063EN             
200805141    200805141    EU  2008       5          14         CA080218002      120080218G71300292827110      HEAT SHIELD     TMECA       ARRIEL2B    SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              ENGINE          CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5478 2479                                                      (CAN) WHILE REPLACING THE MO5, SEVERAL HOLES WERE NOTICED. THESE HOLES WERE DUE TO RUBBING AND WERE ONLY THROUGH THE OUTER LAYER OF THE HEAT SHIELD. (TC NR 20080218002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H9EU    E00054EN             
             20081230     CE  2008       12         30         CA080218003      120080218G326030A01002203202  INDICATOR                               CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA  HARTZLHCF3Y HCF3YR1     GL  MLG FLOAT       MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) IT WAS FOUND DURING AN INSP OF THE FLOATS THAT THE MLG INDICATOR COVERS COULD BE INSTALLED ON THE WRONG FLOAT.  IF INSTALLED INCORRECTLY THE GEAR INDICATION IS REVERSED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ORTA4CE    E14EA   5  CP31EA    
             20081230     CE  2008       12         30         CA080218004      120080218G2820051338216       SELECTOR                                CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              FUEL SYS        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSP THE FUEL SELECTOR DRIVE ASSY WAS FOUND TO BE WORN OUT. THIS ALLOWED A TANK SELECTION TO BE MADE WITHOUT THE SELECTOR POSITIONING BALL AND SPRING HSG REACHING THE DETENT IN THE FUEL SELECTOR HSG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
             20080521     EU  2008       5          21         CA080218005      120080218G7720955017820       THERMOCOUPLE                            SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              ENGINE          GROOVED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       478                                                            (CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS BEEN FOUND. (TC NR 20080218005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H9EU    E00054EN             
             20080521     EU  2008       5          21         CA080218006      120080218G77229550178220      THERMOCOUPLE                            SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              ENGINE          GROOVED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       478                                                            (CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS BEEN FOUND. (TC NR 20080218006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H9EU    E00054EN             
             20081113     EU  2008       11         13         CA080219002      120080208G6730                SERVO                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              FLLIGHT CONTROL MALFUNCTIONED   W      L   ABORTED APPROACH                                                                                EF VIBRATION/BUFFET          FLT CONT AFFECTED                                   APAPPROACH       1                      CA       101282345                                                      (CAN) ALSO APPLIES TO SERVO SC5081-1 S/N 229 TSN 8917.4 TSO 2342.6 AND SERVO SC5082-1 S/N 361 TSN 5634.5 TSO 2345.1. A/C WAS APPOACHING FOR LANDING AND WHEN THE COLLECTIVE WAS REDUCED THERE WAS A VIOLENT VIBRATION, SEVERE ENOUGH TO CAUSE CONCERN ABOUT LOSS OF CONTROL OF THE HELICOPTER. COLLECTIVE WAS INCREASED AND THE VIBRATION LEVEL RETURNED TO A NORMAL LEVEL. ALL M/R SERVOS WERE REPLACED AT ACRO HELIPRO AND SUBSEQUENT TEST FLYING HAS PROVEN THAT TO BE THE ROOT CAUSE. THERE WAS SOME LOW POWER VIBRATIONS EXPERIENCED IN THE PAST 12 MONTHS AND MOST OF THE RELATED DYNAMIC COMPONENTS HAD BEEN REPLACED AND INSPECTIONS PERFORMED. THE VIBRATIONS WERE WITHIN LIMITS AND NEVER REACHED A LEVEL OF IMMEDIATE CONCEARN LIKE T1G71 3U3  U  H9EU    E19EU                
             20080603     NM  2008       6          3          CA080219004      120080218G327065715611        SKID                                    BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              TAIL SKID       DEFECTIVE       W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) UPON GEAR RETRACTION, TAIL SKID LIGHT REMAINED ILLUMINATED. A/C RETURNED TO STATION WHERE SKID TIP WAS REPLACED, SWITCH CONTACT CONFIRMED AND A/C RETURNED TO SERVICE. (TC NR 20080219004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L73 4F4  F  A3WE    E2EA                 
             20080521     NM  2008       5          21         CA080219005      120080219G5320654659244       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               BS 790          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOOR CHANNEL AT BS 790, RBL 8 AFT CARGO PIT CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20080219005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080219006      120080219G5321654659247       FLOOR PANEL                             BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL CORRODED AT BS 767+6, LBL 3 AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080219007      120080219G5320654659249       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727+8, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080521     EA  2008       5          21         CA080220001      120080219G76033018024         ROD END                                 DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  NR 2 THROTTLE   BENT            W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) THE PILOT REPORTED A DEFECT NR 2582A: ABOUT 10 MINUTES AFTER TAKEOFF, THE RT ENGINE NR 2 THROTTLE LEVER WAS STUCK.  WORKED THE THROTTLE BACK  AND FORTH IN CRUISE 3 - 4 TIMES AND FOUND OK.  ON FINAL APPROACH INTO ARRIVAL AIRPORT, THE NR 2 THROTTLE WAS DIFFICULT TO MOVE AGAIN.  MAINT LATER FOUND THE WIRE WITH A 1.5 INCH LONG RIGID SPOT AT 18 INCHES FROM THE ROD END ATTACHMENT. THE ROD END P/N: 3008787 WAS FOUND BENT ALSO. BOTH PART WERE REPLACED AND RE-RIGGED THE ENGINE IAW MM. THE ENGINE WAS RECENTLY REPLACED AND HAS 3.4 HOURS SINCE LAST OVERHAUL.  (TC NR 20080220001)                                                                                                                                             1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20080521     SW  2008       5          21         CA080220002      120080218G56102719442004      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  COCKPIT         DELAMINATED     W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       4902                                                           (CAN) DURING THE CRUISE PORTION OF FLIGHT, THE CREW WITNESSED THE RT SIDE COCKPIT HEATED WINDSHIELD PHYSICALLY DELAMINATING . THE CREW INDICATED THE AC WAS OPERATING AT A 6.0 PSI DIFFERENTIAL WHICH IS WITHIN THE MAXIMUM 7.25 PSI DIFFERENTIAL FOR THE AC. NO ACTION WAS TAKEN BY THE CREW OR WAS DEEMED NECESSARY AND THE WINDOW DELAMINATION WAS MONITORED CLOSLY UNTIL LANDING.  MAINT HAS REPLACED THE WINDSHIELD. (TC NR 20080220002)                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20080521         2008       5          21         CA080220003      220080220G7414                BEARING                                                                                                                                 MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       122                                                            (CAN) MAG WAS RECEIVED FOR INSPECTION DUE TO ENGINE OVERSPEED. WHEN THE ROTATING MAGNET (ROTOR) WAS SPUN BY HAND THERE WAS NOTICEABLE SIDE PLAY IN THE BEARINGS. THE END PLAY WAS MEASURED AND FOUND TO BE .003 NR.   MFG HAS A LIMIT OF NO SIDE PLAY ALLOWED. THE MAG WAS INSPECTED AND NO OTHER DEFECTS WERE FOUND. SHIMS WERE ADDED TO THE BEARINGS TO THE PROPER PRELOAD AND THE MAG WAS TESTED AND RETURNED TO SERVICE. THIS WAS A FACTORY NEW MAGNETO WITH ONLY 121.5 HOURS IN SERVICE. (TC NR 20080220003)                                                                                                                                                                                                                                                                         
             20080521     EA  2008       5          21         CA080220005      220080130G7200                ENGINE                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6*        52043EA  HARTZLHCB4M HCB4MP3     GL                  MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT, THE PROPELLER AUTO-FEATHERED UNCOMMANDED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. POST FLIGHT INSP REVEALED A GRINDING NOISE WHEN TURNING THE PROP BY HAND. REDUCTION GEARBOX WAS CONTAMINATED WITH OIL. THE ENGINE HAS BEEN SENT FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220005)                                                                                                                                                                                                                                                                                                            2L72 4T3  TRTA24CE   E2NE    6  CP56GL    
200805141    200805141    NE  2008       5          14         CA080220006      220080206G7250                TURBINE BLADES  PWA         PW127       AEROSPATR72 ATR72212    8680945EU  PWA   PW120 PW127            NE                              ENGINE          FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE ITT WAS NOTED TO RISE TO 800 DEGREES C, FOLLOWED BY SMOKE IN THE CABIN. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND RETURN TO POINT OF DEPARTURE. POST FLIGHT INSPECTION INDICATED FRACTURED POWER TURBINE BLADES AND EVIDENCE OF OIL LEAKAGE. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED. (TC NR 20080220006)                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA53EU   E20NE                
             20080521     NM  2008       5          21         CA080220007      120080115G7931                OIL SYSTEM                              DORNERDO32  DO328100    2996000NM  PWA   119   PW119B           NE                              ENGINE          LOW PRESSURE    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE OIL PRESSURE WAS NOTED TO DROP. THE CREW SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. ENGINE IS BEING SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA45NM   E20NE                
             20080521     NE  2008       5          21         CA080220008      220080211G7200                ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                                              SEIZED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RB PARTIAL RPM/PWR LOSS      SMOKE/FUMES/ODORS/SPARKS                            CLCLIMB          1                      CA                                                                      (CAN) SHORTLY AFTER TAKEOFF, WHEN SELECTING BLEED AIR ON, THE CREW HEARD TWO (2) LOUD BANGS FOLLOWED BY SEEING SPARKS FROM THE EXHAUST.  PILOT SECURED THE ENGINE AND RETURNED TO POINT OF DEPARTURE.  POST FLIGHT INSP REVEALED A SEIZED PROP AND IMPACT DAMAGE INSIDE EXHAUST DUCT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220008)                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA24CE   E26NE                
             20080521     NM  2008       5          21         CA080220009      120080220G5320654659249       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220010      120080220G5320654659247       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220011      120080220G5320654659249       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867+14, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220012      120080220G5340650163312       STRINGER CLIP                           BOEING737   7374S3      1384711NM                                                               BS 294.5 S13L   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) TIE CLIP AT BS 294.5, S13L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220013      120080220G5310651768537       DOOR FRAME                              BOEING737   7374S3      1384711NM                                                               L1 DOOR         GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) L1 DOOR CUTOUT FRAME AT STA 349, WL 216 GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220014      120080220G4910656612115       SHROUD                                  BOEING737   7374S3      1384711NM                                                               APU             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) APU UPPER SHROUD CRACKED FWD OF FWD LATCH REPAIRED IAW CUSTOMER EA. (TC NR 20080220014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220015      120080220G531365617777        STRINGER SPLICE                         BOEING737   7374S3      1384711NM                                                               BS360 S15L      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) STRINGER SPLICE AT BS 360, STR 15L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220016      120080220G532065465926        CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS767+6, LBL11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220017      120080220G5320654659247       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727 F +8, LBL 11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220018      120080220G5534655484221       SKATE ANGLE                             BOEING737   7374S3      1384711NM                                                               VERTICAL STAB   CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) V STAB TO FUSELAGE SKATE ANGLE LT CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220019      120080220G53206546592503      CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727E+8, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
200805141    200805141    NM  2008       5          14         CA080220020      120080220G53206546592503      CHANNEL                                 BOEING737   7374S3      1384711NM                                                               FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6 - BS247+14, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220020)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220021      120080220G5320654659247       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220021)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080220022      120080220G5320654659247       CHANNEL                                 BOEING737   7374S3      1384711NM                                                               AFT CARGO PIT   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+4, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220022)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080521     EA  2008       5          21         CA080221001      120080212G2810CT2P10011       FUEL TANK                               DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  FORWARD         DETERIORATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16085                                                          (CAN) THIS FWD FUEL TANK ENCLOSURE WAS FOUND BADLY DETERIORATED DUE TO ITS AGE, THERE WERE OLD REPAIRS FOUND CARRIED OUT. THIS ASSEMBLY HAD BEEN BULGING DUE TO THE FUEL, CAUSING CLOSER TOLERANCES TO THE ELEVATOR CONTROL PUSH/PULL TUBE.  THIS ASSEMBLY HAS NOW BEEN REPLACED WITH A NEW CERTIFIED UNIT MADE FROM ALUMINUM IAW STC SA 06-51 MDL P/N VT2MK1555, ISSUE 1. (TC NR 20080221001)                                                                                                                                                                                                                                                                                                                                                  1H71 3T4  T  A806    E4EA    6  CP15EA    
             20081230     CE  2008       12         30         CA080221002      120080208G7820PN04504003      MUFFLER                                 CESSNA150   150L        2071826CE  CONT  O200  O200A       17020SO  MCAULY1A101 1A101DCM    GL  EXHAUST SYS     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS IS AN ON GOING ISSUE. THIS EXHAUST MUFFLER PASSED THE VISUAL INSP AS CF90-03. WHEN PRESSURE TESTED WITH AIR AND WATER, 3 PIN HOLES SHOWED. 2 WERE IN OPEN BARE METAL SURFACE. ONE WAS IN THE LONGITUDINAL SEAM. ANOTHER EXPERIENCED AME WAS IN MY SHOP FOR OTHER REASONS.  ASKED HIM TO VISUALLY INSPECT IAW CF90-03. EVEN THOUGH HE KNEW THERE WERE LEAKS, SO HE LOOKED MORE INTENSELY, HE WAS UNABLE TO FIND ANY, VISUALLY. THIS IS A 50 PERCENT FAILURE RATE FOR ACFT IN MY SHOP.  AGAIN, THIS SHOP ONLY DOES BUBBLE TESTS AS THE VISUAL TEST, IAW CF90-03.                                                                                                                                                                       1H71 3O3  O  3A19    E252    5  NP918     
             20080521     EA  2008       5          21         CA080221003      120080220G2913601R751547      PUMP                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              HYD SYSTEM      UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       8050                                                           (CAN) CREW RECEIVED A GEAR DISAGREE MESSAGE AFTER TAKEOFF WITH AN APPLICABLE RED NOSE GEAR INDICATION AND 2 MAIN GEAR AMBER MESSAGES. CREW ACTIONED THEIR QRH AND DO AN ALTERNATE EXTENSION, A/C RETURNED. PSEU CODES RETRIEVED AND THE AC WAS ROUTED WHERE MAINT WILL INVESTIGATE FURTHER. NOSE GEAR OLEO SERVICED TO C/O AND 3A HYD PUMP TO BE REPLACED. MORE INFORMATION TO FOLLOW. (TC NR 20080221003)                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
             20080603     SW  2008       6          3          CA080221004      120080209G6320PT6T3B          GEARBOX                                 BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              MAIN ROTOR      MISMANUFACTURED W      O   OTHER                                                                                           J  WARNING INDICATION                                                            HOHOVERING       1                      CA       37                                                             (CAN) MAINT WAS TROUBLESHOOTING OIL PRESSURE PROBLEMS. THE POWER SECTION ALWAYS APPEARED THAT IT HAD LOTS OF OIL. VISUAL INDICATION. THE OIL PRESSURE FLUCTUATIONS OCCURRED FEB. 5TH.  IN THE TROUBLESHOOTING PROCESS A LITTLE OIL WAS BEING DRAINED AND YET THE VISUAL INDICATION THERE WAS LOTS OF OIL. ON FEB. 9TH THE PWR SECTION WAS REMOVED DUE TO LOSS OF OIL PRESSURE. A TECH REP WAS BROUGHT TO THE BASE AND IT WAS NOTICED THAT THE LOWER HOLE INTO THE GEARBOX OF THE OIL LEVEL INDICATOR WAS NOT DRILLED INTO THE CASE. SINCE THE OIL COULD NOT DRAIN OUT OF THE VISUAL INDICATOR THE OIL LEVEL APPEARED FULL. (TC NR 20080221004)                                                                                                  1G71 4U4  U  H4SW    E22EA                
             20081104     SW  2008       11         4          CA080221005      120080216G5302206031327101    FITTING                                 BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6996                                                           (CAN) LOWER LT TAILBOOM ATTACH FITTING FOUND CRACKED IN WEB AREA ON SCHEDULED INSPECTION. POSSIBLE ALIGNMENT ISSUES FROM THE MFG. REPLACED WITH UPGRADED ONE PIECE FITTING AND LONGERON. (TC NR 20080221005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  UO H2SW    E1GL                 
             20080603     NE  2008       6          3          CA080221007      220080208G7200PT6A68          ENGINE                                                                     PWA   PT6   PT6A68           NE                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         JEAWARNING INDICATION        VIBRATION/BUFFET          FLAME/FIRE                NRNOT REPORTED   1                      CA                                                                      (CAN) DURING A TRAINING MISSION, THE PILOT REPORTED HIGH ITT, VIBRATION AND FLAME FROM THE ENGINE EXHAUST AND ELECTED TO SHUTDOWN THE ENGINE. LANDED WITHOUT INCIDENT. ENGINE WILL BE REMOVED AND RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221007)                                                                                                                                                                                                                                                                                                                                                                                                                  4  T          E26NE                
             20080521     NE  2008       5          21         CA080221008      220080213G7200                ENGINE                                  DHAV  DHC8  DHC8*              NM  PWA   PW121 PW121       52124NE                                              FLAMED OUT      W      O   OTHER                                                                                           RX PARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT                                     APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH, ENGINE SHUTDOWN UNCOMMANDED AS FLAPS WERE BEING EXTENDED FOR LANDING. POST FLIGHT INSP REVEALED UNSTABLE FUEL FLOW AND LOW ITT AT IDLE POWER. FUEL PUMP AND FUEL CONTROL ARE BEING RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221008)                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE                
             20080521     NE  2008       5          21         CA080221009      220080214G7320                EEC                                     AEROSPATR72 ATR72202    8680940EU  PWA   PW120 PW124B           NE                              ENGINE          FAULTED         W      A   UNSCHED LANDING                                                                                 RE PARTIAL RPM/PWR LOSS      VIBRATION/BUFFET                                    CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, AN EEC FAULT WAS FOLLOWED BY AN ENGINE POWER LOSS AND VIBRATION. THE CREW SHUT THE ENGINE DOWN AND DIVERTED THE FLIGHT ACCORDINGLY. POST FLIGHT INVESTIGATION REVEALED BOTH OIL FILTERS TO BE CONTAMINATED WITH DEBRIS AND THAT THE PROPELLER COULD NOT BE ROTATED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221009)                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA53EU   E2ONE                
             20080521     NE  2008       5          21         CA080221010      220080214G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, A LOUD NOISE WAS HEARD FOLLOWED BY REDUCTION IN ENGINE POWER TO ZERO. THE AC LANDED ON A PUBLIC ROAD. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA                 
             20080603         2008       6          3          CA080221011      420080217G6122                GOVERNOR                                AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              PROPELLER       LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND DIVERT THE AIRCRAFT TO AN ALTERNATE LANDING SITE. INITIAL INVESTIGATION REVEALED SIGNIFICANT EXTERNAL OIL LEAKAGE FROM THE PROPELLER OVERSPEED GOVERNOR AREA. THE COMPONENT WAS REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221011)                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRT        E20NE                
200805141    200805141    NE  2008       5          14         CA080221012      220080214G7314LW15473         PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA       936                                                            (CAN) DURING THE PREFLIGHT CHECK THE ENGINE DRIVEN FUEL PUMP FOUND LEAKING OIL. (TC NR 20080221012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081104         2008       11         4          CA080221013      420080214G3416066030620010    ALTIMETER                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  COCKPIT         INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA            112                                                       (CAN) FLAG CAME INTO VIEW IN PILOTS ENCODING ALTIMETER AND NEEDLE FROZE. RETURNED TO NORMAL MOMENTS LATER. MAINT WAS NOT ABLE TO DUPLICATE THE SNAG. THERE IS AN SDR 20070914001 PERTAINING TO THE SAME DEFECT ON THIS SN UNIT, AS INSTALLED IN A DIFFERENT PC12. THE REPAIR REPORT AT THAT TIME INDICATED THE DEFECT HAD BEEN CONFIRMED AND REPAIRED. (TC NR 20080221013)                                                                                                                                                                                                                                                                                                                                                                      1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080521     NM  2008       5          21         CA080222001      120080219G3246L8121482629     BEARING                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  MLG WHEEL       DISINTEGRATED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19373233                                                       (CAN) DURING SERVICE CHECK ON THE RAMP, LINE MAINT OBSERVED THAT NR3 MAIN WHEEL ASSY HUB CAP WAS MISSING AND NOTICED THE PRESENCE OF METAL CHIPS. THE AC WAS REMOVED FROM SERVICE.  MAIN WHEEL ASSY WAS REMOVED AND THE FOLLOWING DAMAGES WERE OBSERVED: BOTH WHEEL BRGS WERE DISINTEGRATED ALONG WITH DAMAGE TO THE WHEEL HUB AND BRAKE KEYS, BRAKE DISKS, WHEEL NUT AND MLG AXLE.  FOLLOWING OBSERVATIONS WERE NOTICED DURING THE INITIAL INVESTIGATION: THE WHEEL NUT WAS IN PLACE AND SECURED WITH THE TWO LOCK BOLTS. THERE WAS NO LOCKING WIRE OBSERVED. THE WHEEL HUB CAP WAS MISSING BUT (2) OF THE (3) HOLDING SCREWS WERE STILL FIXED TO THE WHEEL FRAME. INSP OF THE INNER BEARING CLEARLY INDICATES THE CORRECT PN L713049*2-629. PN2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080521     SO  2008       5          21         CA080222002      220080221G8530655475A         CYLINDER                                                                   CONT  O470  O470*       17026SO                              ENGINE          UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FACTORY NEW CYLINDER ASSY RECEIVED FROM MFG WITH INCORRECT EXHAUST AND INTAKE VALVE GUIDES INSTALLED. INTAKE GUIDE P/N 655166 AND EXHAUST GUIDE P/N 636242 ARE REQUIRED IAW SB 04-11. UNABLE TO DETERMINE P/N OF GUIDES ACTUALLY INSTALLED IN NEW CYLINDER. SUSPECT INTAKE AND EXHAUST VALVE GUIDES INSTALLED IN WRONG LOCATIONS. CYLINDER SUBJECT TO WARRANTY THROUGH MFG. (TC NR 20080222002)                                                                                                                                                                                                                                                                                                                                                  3  O          E273                 
             20080521     EU  2008       5          21         CA080222003      120080220G2897                WIRE HARNESS                            AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  BOOST PUMP      CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING TROUBLESHOOTING OF A FUEL BOOST PUMP SNAG, MAINT DISCOVERED THE RELATED WIRING HARNESS HAD BEEN DAMAGED DUE TO CHAFING ON THE EDGE OF THE FIXED CARGO LINER PANEL AT THE AFT SIDE OF THE 91VU SHELF. THE CARGO LINER PANEL IS PART OF THE FIRST AIR CLASS C INTERIOR, STC SA22-122 NOT AN OEM COMPONENT. THE WIRING WAS REPAIRED AND CLEARANCE ADJUSTED TO PRECLUDE FURTHER ISSUE. THE COMPANY HAS INITIATED A FLEET CAMPAIGN TO INSPECT FOR SIMILAR ANOMALIES. (TC NR 20080222003)                                                                                                                                                                                                                                                2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20080521     NM  2008       5          21         CA080222004      120080215G2497284T3501315     ELECTRICAL BOX                          BOEING767   767333      1385301NM  GE    CF6   CF680C2B6F  30025NE                              CARGO HANDLING  BURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) WIRING DAMAGE FOUND IN FWD CARGO HANDLING ACCESS PANEL P35 DURING THE (XM) VISIT.  57 WIRES BURN, 3 WIRES MAJOR DAMAGED, 1 FOUND CUT, FOUND LUG DAMAGE ON TERMINAL A1,B1,C1 OF RELAY K245 (P35).  FOUND WIRES DAMAGE ON CONNECTOR D5886P.  AFTER AN INVESTIGATION , FOUND CARGO PDU P/N 43104-14 AT POSITION 7R FAULTY (FOUND INTERNAL WIRES BURNED) ROOT CAUSE , THE FAULTY PDU CAUSED A SHORT IN THE P35 PANEL DAMAGING WIRES AND RELAY (TC NR 20080222004)                                                                                                                                                                                                                                                                             2L72 4F4  FRTA1NM    E13NE                
             20080521     EA  2008       5          21         CA080222005      120080222G32343620377         O-RING                                  CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 R2800CA3    52026NE  HAMSTD43E   43E60       NE  MLG             DETERIORATED    W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) O-RING LOCATED BEHIND INDICATED SCREW IN DIAGRAM, DETERIORATED CAUSING A HYDRAULIC LEAK. THERE ARE (6) LOCATIONS ON THE AC THAT INCORPORATES THIS VALVE. THIS LEAK WAS DISCOVERED ON THE NLG SELECTOR VALVE LOCATED UNDER CO-PILOTS SIDE.  (TC NR 20080222005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4R4  RRTA14EA   5E8     6  CP871     
             20080530     EA  2008       5          30         CA080222006      120080219G2910                LINE                                    DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA                              HYD SYSTEM      PUNCTURED       W      EF  ENGINE SHUTDOWN         ACTIVATE FIRE EXT.                                                      KA FLUID LOSS                FLAME/FIRE                                          TXTAXI/GRND HDL  1                      CA       17426                                                          HYDRAULIC PUMP SUPPLY LINE IN THE COCKPIT DEVELOPED A PIN-HOLE FAILURE IN THE WALL OF THE TUBING.  THE HYDRAULIC FLUID AT A PRESSURE OF 1650 PSI WAS RELEASED INTO THE CABIN, ATOMIZING AS IT DID SO, THE DIRECTION OF THE SPRAY WAS DIRECTLY AT THE PILOT.  THE POWER WIRE FOR THE HYDRAULIC PUMP ARCED AGAINST THE TUBING, IGNITING THE HYDRAULIC MIST AND IGNITING A FLASH FIRE.  THE FIREBALL WAS UNABLE TO SUSTAIN ITSELF AND DID NOT IGNITE THE AIRCRAFT ALTHOUGH THE PILOT WAS SET ON FIRE, SUFFERED 1ST AND 2ND DEGREE BURNS TO HIS FACE AND RIGHT HAND.  THE PASSENGER DID NOT RECEIVE ANY INJURIES AND WAS INSTRUMENTAL IN EXTINGUISHING THE PILOT,  THE SYSTEM HAS BEEN IN THE ACFT SINCE MANUFACTURING, BUT DOES NOT MATCH ROUTING S1H71 3T4  T  A806    E4EA                 
             20080603     EU  2008       6          3          CA080222007      120080215G3211201660001010    BOLT                                    AIRBUSA321  A321211     3930370EU  CFMINTCFM56 CFM565B3P   13006NE                              MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       20789                                                          (CAN) CORRODED FAIL SAFE BOLTS THAT SECURE MAIN LANDING GEAR SIDE STAY ATTACH PINS TO UPPER AND LOWER CARDAN PINS. BOLTS ARE ITEMS 290 AND 296 IN A321 IPC 32-11-18-02E. ITEM 290 IS AN AN6-56A AND ITEM 295 IS AN AN6-62. THE LOWER BOLT ITEM 295 IS HEAVILY CORRODED.  (TC NR 20080222007)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA28NM   E37NE                
             20080603     NM  2008       6          3          CA080222008      120080222G271019004209401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERON         WORN            W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      CA                                                                      (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401, P/N 190-04209-401, RT P/N 190 -05551-401, P/N 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLEAD, LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. MFG WILL COME UP WITH AN SB END OF MARCH (TC NR 20080222008)                                                                                                                                                                                                                                                                    2L72 4F4  FRTA57NM   E00070EN             
             20080530     NM  2008       5          30         CA080222009      120080221G271017005825401     CONTROL CABLE                           EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              AILERON         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P/N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT FAIRLEADS, LOCATED AT LT AND RT WINGS INB OF THE RIB 17.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD.  EMBRAER WILL ISSUE A SB END OF MARCH (TC# 20080222009)                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA56NM   E00063EN             
             20080603     NM  2008       6          3          CA080222010      120080221G5315                FLOORBEAM                               EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 AND ON FLOORBEAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR 14 AT Y = -337.0 AND Z = -490.0 ALSO (3) SILL PLATES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE, AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS MFG INSTRUCTION. THE ROOT CAUSE SEEMS TO BE THE LACK OF FLOOR PROTECTION UNDER THE FWD AND AFT GALLEYS. (TC NR 20080222010)                                                  2L72 4F4  FRTA56NM   E00063EN             
200805141    200805141    NE  2008       5          14         CA080225001      220080212G732178639114        HMU                                     DHAV  DHC8  DHC8*              NM  PWA   PW121 PW121       52124NE                              NR 2 ENGINE     MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          APAPPROACH       1                      CA            1578                                                      (CAN) AFTER CONFIGURING FOR LANDING (FLAP 35, CONDITION LEVERS MAX) CO-PILOT COMMENTED THAT HE HAD NOTICED A SIGNIFICANT POWER LOSS ON THE NR 2 ENG AND POINTED OUT A REDUCTION IN TORQUE. THE NR 2 TORQUE GAUGE WENT TO 0 PERCENT, CREW DECIDED TO SHUTDOWN THE NR 2 ENG. FUNCTIONAL CHECK OF THE ENG WAS CARRIED OUT BY MAINT STAFF. THE ENG WAS ABLE TO BE STARTED WITH VERY SLOW ACCELERATION REPORTED AND LOW IDLE OF 60 PERCENT ONLY ACHIEVED - NP 168, FUEL FLOW 160, ITT 550 DEGREES. FOLLOWING COMMUNICATION OF THIS DATA WITH THE ENG MFG, IT WAS DETERMINED THAT THE MOST LIKELY CAUSE OF THE DEFECT WAS HYDRO MECHANICAL FCU (HMU) FUEL SCHEDULE. THE HMU AND FUEL PUMP ASSY WAS REPLACED IAW THE AC MM 72-01-40 AND SUBSEQUENTLY GR2H72 4T4  TRTA13NM   E20NE                
             20080521     NM  2008       5          21         CA080225002      120080122G326083260024101     ROLLER                                  DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NLG             SEIZED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       8236                                                           (CAN) AFTER RETRACTING LANDING GEAR ON TAKEOFF, NOSE GEAR AMBER DOOR LIGHT REMAINED ILLUMINATED. CONDUCTED CHECKS IAW QRH (LANDING GEAR DOOR MALFUNCTIONS) UNABLE TO RECTIFY PROBLEM, RETURNED TO BASE WITH LANDING GEAR EXTENDED FOR NORMAL APPROACH AND LANDING. INSP OF THE AC BY MAINT AFTER RETURN OF THE AC TO THE TERMINAL DETERMINED THAT THE NLG DOORS WERE CLOSED BUT THE CORRESPONDING INDICATION WAS OF AN UNSAFE CONDITION. FUNCTIONAL CHECK OF THE NLG DOORS AND INDICATING SYS CARRIED OUT. THE ALTERNATE RELEASE ROLLER TRIPPING ARM BRG WAS DISCOVERED TO BE SEIZED AND THE CLEARANCE BETWEEN THE ROLLER AND OB TOGGLE LINK OUT OF ADJUSTMENT. ROLLER PN 83260024-101 WAS REPLACED AND THE ALTERNATE RELEASE CABLE ADJUSTED IAW2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080521     NM  2008       5          21         CA080225003      120080219G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R320  CR3204123F1 GL  NR 2 ENGINE     SEPARATED       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) NR 2 EDP FAILED IN FLIGHT WITH A BANG FOLLOWED SHORTLY AFTER BY NR1 HYD FLUID HOT CAUTION LIGHT ILLUMINATING, FOLLOWED BY THE 1 HYD ISO VALVE TO CLOSING. THE AC MADE A FLAPLESS EMERGENCY LANDING. INITIAL INVESTIGATION BY MAINT FOUND THAT THE NR2 HYD SYS HAD LOST ITS FLUID, THE NR2 EDP PORT CAP HAD SEPARATED FROM THE EDP PUMP BODY, THE PTU WAS INOPERATIVE (OVERSPEED AND EVIDENCE OF OVERHEAT), PTU FLEX HOSES EVIDENCE OF OVERHEAT.  MAINT ACTIONS: REPLACEMENT OF NR1 AND NR2 EDP`S, PTU, PTU SELECTOR VALVE, NR1 AND NR2 HYDR SYS FILTERS, REPLACEMENT OF PTU FLEX HOSES, FLUSHING/BLEEDING OF THE APPLICABLE HYDR LINES. (TC NR 20080225003)                                                                               2H72 4T4  TRTA13NM   E00062EN6  CP5NE     
             20080521     EA  2008       5          21         CA080225005      120080222G2421731579          SHAFT                                   CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343A2     30067NE                              IDG             BROKEN          W      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) 3 MINUTES AFTER TAKEOFF, GENERATOR FAILED, AC RETURNED TO BASE.  GENERATOR REMOVED, FOUND BROKEN SHAFT INSIDE THE IDG (NOT THE MAIN SHAFT).   IT BROKE, MELTED THE COVER AND CAME OUT (TC NR 20080225005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21AE   E15NE                
             20080603     GL  2008       6          3          CA080225006      320080221G6114                HUB             HARTZL      HCE4A3D     PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  PROPELLER       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    CRCRUISE         1                      CA       663                                                            (CAN) PROPELLER REMOVED DUE TO EXCESSIVE GREASE LEAK FROM BLADE CLAMPS. (TC NR 20080225006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080603         2008       6          3          CA080225007      420080221G23306009580001      MONITOR                                 BOEING757   75728A      1384976NM  RROYCERB211 RB211535E43754555NE                              CABIN           MALFUNCTIONED   W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      (CAN) CREW REPORTED A BURNING SMELL IN THE CABIN JUST BEFORE LANDING. IN-FLIGHT ENTERTAINMENT WAS SELECTED OFF AND SMELL DISSIPATED. MAINTENANCE DETERMINED THAT THE SMELL WAS COMING FROM THE NR 7 MONITOR. (TC NR 20080225007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA2NM    E12EU                
             20081230     CE  2008       12         30         CA080225009      120080221G27300510105125      CONTROL CABLE                           CESSNA180   180K        2072624CE  CONT  O470  O470*       17026SO  MCAULY2A34C C2A34C204   GL  ELEVATOR        FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140, WHERE CABLE RIDES ON THE PHENOLIC BLOCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  5A6     E273    5  CP3EA     
             20081230     CE  2008       12         30         CA080225010      120080204G27300510105125      CONTROL CABLE                           CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  ELEVATOR        FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA140 AT PHENOLIC BLOCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A24    E5CE    5  CP3EA     
             20081230     CE  2008       12         30         CA080225011      120080211G27300510105125      CONTROL CABLE                           CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C401   GL  ELEVATOR        FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140 AT THE PHENOLIC BLOCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  3A24    E5CE    5  CP47GL    
             20080530     EA  2008       5          30         CA080225012      120080222G534319064104        FITTING                                 CNDAIRCL604 CL604       1900301EA                                                               MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4481                                                           DURING LANDING GEAR 96 MONTH DETAIL INSPECTION HEAVY PITTING CAUSED BY CORROSION.  FOUND ON MAIN LANDING GEAR MAIN FITTING TRAILING ARM ATTACHMENT INBOARD LUG BUSHING AREA AND BORE, RESULTING CONSIDEABLE AMOUNT OF MATERIAL FROM AFFECTED LOCATION, LEADING MAIN FITTINGTO REDUCED LOAD CARRYING CAPACITY                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA21EA                        
             20090102     CE  2009       1          2          CA080225013      120080220G323026410148        SPRING                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  MLG             WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3808 3808                                                      (CAN) ON JACKING THE ACFT, THE RT MAIN SPRING WAS FOUND TO BE LOOSE IN THE CTR SPRING TO SUCH AN EXTENT THAT MAINWHEEL COULD BE MOVED BACK AND FORTH .1250 ON AN INCH BEFORE THE REMOVAL BEGAN. UPON DISASSEMBLY THE MAIN SPRING WAS REMOVED BY HAND FROM THE CTR SPRING WITHOUT ANY PULLERS BEING USED. AMOUNT OF PLAY WHILE THE MAIN SPRING WAS STILL ASSEMBLED TO THE CTR SPRING SEEMED TO BE EXCESSIVE AND WAS NOT SOMETHING THAT WE HAD EXPERIENCED IN THE PAST.  AFTER REMOVAL OF THE MAIN SPRING THE CTR SPRING WAS FOUND TO BE WITHIN LIMITS ON THE LT SIDE BUT OUT OF LIMITS ON THE RT SIDE. MAXIMUM DIAMETER MEASURED AT THE RT CENTER SPRING WAS 2.807 INCH, THE LIMIT IN THE MM IS 2.794 INCH. DURING A SEARCH OF THE ACFT RECORDS N1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20080530     NM  2008       5          30         CA080225014      120080222G2750                CLUTCH                                  BOEING737   737200      1384453NM  PWA   JT8   JT8D17A     52049NE                              TE FLAP         DISENGAGED      W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      DEPARTING YOW THE AIRCRAFT EXHIBITED AN UNCOMMANDED ROLL TO THE LEFT REQUIRING 2-3 UNITS OF RUDDER TRIM TO CORRECT.  THE CREW OBSERVED NO ASSYMMETRY INDICATION IN THE FLIGHT DECK BUT IT WAS VISUALLY CONFIRMED THAT THE RIGHT INBOARD AFT FLAP WAS PARTIALLY EXTENDED.  MAINTENANCE FOUND THE INBOARD TRAILING EDGE FLAP CLUTCH DISENGAGED.  THE MECHANISM WAS INSPECTED, THE CLUTCH BELLCRANK RESET AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC# 20080225014)                                                                                                                                                                                                                                                                           2L72 4F4  F  A16WE   E2EA                 
200805141    200805141        2008       5          14         CA080225015      220080225G7414                BEARING                     106006169                                                                                                   MAGNETO         EXCESS PLAY     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       930                                                            (CAN) MAG WAS RECEIVED FOR A 500 HR INSP.  BEFORE THE MAG WAS DISASSEMBLED THE ROTATING MAGNET (ROTOR) WAS SPUN TO CHECK FOR BRG ROUGHNESS OR END PLAY. SOME SIDE PLAY WAS NOTICED (MFG DOES NOT ALLOW ANY) AND THE END PLAY WAS MEASURED AT .003 INCH. THE BRGS WERE INSPECTED, SHIMS WERE ADDED, THE REST OF THE 500 HOUR INSP WAS CARRIED OUT, AND THE MAG WAS RETURNED TO SERVICE. THE MAG HAD 473.8 HRS SINCE ITS PREVIOUS 500 HR INSP. (TC NR 20080225015)                                                                                                                                                                                                                                                                                                                          
             20081104     EA  2008       11         4          CA080226001      220080222G7322                THROTTLE BODY                           PIPER PA18  PA18A135    7101822SO  LYC   O320  O320A2B     41508EA  SNSNCH74DM  M74DM       EA  CARBURETOR      LOOSE           W      K   NONE                                                                                            RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  ININSP/MAINT     1                      CA            279                                                       (CAN) DURING GROUND RUN UP PRIOR TO ANNUAL INSPECTION, ENGINE OBTAINED A MAXIMUM RPM OF 1900. INSPECTION FOUND CARBURETOR THROTTLE BODY SCREWS LOOSE AND FUEL STAINS ON BOWL. CARBURETOR REMOVED AND FORWARDED TO REPAIR FACILITY. (TC N 20080226001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  1A2     E274    5  NP88614   
             20090102     CE  2009       1          2          CA080226002      120080219G32450923150         TUBE                                    CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE  MCAULY4HFR344HFR34C762  NE  NLG TIRE        DESTROYED       W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      CA                                                                      (CAN) NOSE WHEEL BLEW OUT ON LANDING. TIRE AND RIM WERE INSPECTED FOR ANOMALIES WHICH WOULD CAUSE A BLOW OUT. NONE FOUND. THE TUBE IS SUSPECTED TO BE THE CAUSE OF CONCERN. ALSO UPON LANDING WITH A FLAT THE FENDER WAS DESTROYED AND THE TAXI LIGHT NEEDED TO BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T3  TRTA7CE    E4EA    6  C3PNE     
             20081104     EU  2008       11         4          CA080226003      120080224G3110                ANNUNCIATOR                             SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         NRNOT REPORTED   1                      CA       1403                                                           (CAN) ON A ROUTINE CHECK FOLLOWING START, THE ANNUNCIATOR LIGHT FOR GOV FAILURE (RED) FAILED TO ILLUMINATE WHEN THE ENGINE GOV SWITCH WAS MOVED FROM AUTO TO MANUAL. OTHER FUNCTIONS ASSOCIATED WITH MOVING TO MANUAL (SOLENOID, VEMD FAILURE CODES) OPERATED NORMALLY. THE WARNING LIGHT ILLUMINATED DURING THE ANNUNCIATOR (ALL LIGHTS) PUSH TO TEST. THE ANNUNCIATOR PANEL WAS REPLACED WITH THE REPLACMENT UNIT OPERATING NORMALLY. (TC NR 20080226003)                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E00054EN             
             20080521     SW  2008       5          21         CA080226004      120080222G2420ALX8403         ALTERNATOR                              GULSTM112   112         0144701SW  LYC   O360  IO360C1D6   41514EA  HARTZLHCE2Y HCE2YR1BF   GL  ELECTRICAL      UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) ALTERNATOR FAILED, CAUSING MAIN BATTERY TO DRAIN RESULTING IN COMMUNICATION DIFFICULTIES WHICH CAUSED PILOT TO CONTACT TOWER BY CELL PHONE FOR CLEARANCE TO LAND. NEW UPGRADED ALTERNATOR INSTALLED PN ALX8521R (TC NR 20080226004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  A12SO   1E10    5  CP9EA     
             20080521     EU  2008       5          21         CA080227001      120080131G2121                BEARING                                 SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F26 NE  BLOWER MOTOR    FAILED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA            74                                                        (CAN) CABIN CREW NOTED AN ABNORMAL ODOR IN THE CABIN AND ADVISED THE COCKPIT CREW. IT WAS DECIDED TO LAND AT THE CLOSEST AIRPORT AS A PRECAUTION. PRIOR TO LANDING THERE WERE SEVERAL WISPS OF SMOKE OBSERVED IN THE FLOOR/SIDEWALL AREA. THE AC LANDED UNEVENTFUL. MAINT DETERMINED THAT THE SMELL WAS CAUSED BY A FAILED RECIRCULATION BLOWER MOTOR. IT IS BELIEVED THAT A FAILED BEARING IN THE ASSEMBLY IS THE CAUSE OF THE FAULT. (TC NR 20080227001)                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20080521     CE  2008       5          21         CA080227002      120080226G5210SL51043         SPINDLE                                 CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              MAIN CABIN DOOR WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1583                                                           (CAN) CREW SNAGGED MAIN CABIN DOOR OUTER HANDLE AS BEING SLOPPY. DISASSEMBLED DOOR HANDLE AND FOUND OUTER DOOR HANDLE SPINDLE TO BE EXESSIVELY WORN WHERE PIN FOR ATTACHING OUTER HANDLE FITS. MEASURED REMAINING MATERIAL AND FOUND TO BE 0.028 INCH ON ONE SIDE AND 0.031 INCH ON THE OTHER. REMOVED AND REPLACED SPINDLE WITH NEW AS IT WAS FELT THAT THIS PIECE WOULD FAIL SOON AND ALLOW THE HANDLE (OUTER) TO COME OFF AND POSSIBLY BE INGESTED BY THE LT ENGINE. (TC NR 20080227002)                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E00059EN             
             20080521     EA  2008       5          21         CA080227003      120080219G7931                OIL SYSTEM                              CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              ENGINE          LOW PRESSURE    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) LOW OIL PRESS WARNING ON NR 2 ENGINE APPROX 3 MINS AFTER TAKEOFF AT 6000FT MSL ON DEPARTURE CLIMBOUT. AFTER IDENTIFICATION OF FAULT AND CONFIRMATION THAT THE FAULT WAS NOT AN INDICATION PROBLEM NR 2 ENGINE WAS SHUTDOWN AND SECURED. RETURNED SAFELY.  THE CAUSE HAS YET TO BE DETERMINED. (TC NR 20080227003)                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20081104     SW  2008       11         4          CA080227004      120080201G531120631308015S    FRAME                                   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE UPPER RT ATTACH POINT ON THE AIRFRAME SIDE CRACKED ON THE FRAME RING ONLY.  PART REPLACED WITH NEW FROM MFG. (TC NR 20080227004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
             20080521     SW  2008       5          21         CA080227005      120080131G5320206031322003    STIFFENER                               BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT STIFFENER UNDER THE OIL COOLER HANGER BEARING CRACKED FROM FWD ANCHOR NUT WHOLE. REPLACED WITH NEW PART. (TC NR 20080227005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
             20080521     NE  2008       5          21         CA080227006      220080122G741410885435        CAM                                     ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            320                                                       (CAN) DURING A 500 HR MAG INSPECTION IT WAS NOTED THE CAM WAS TIGHT TO SHAFT, COULD NOT BE REMOVED BY HAND. CAM WAS TAPPED OFF SHAFT WITH BRASS PUNCH AND HAMMER. WHEN CAM CAME OFF SHAFT IT BROKE INTO 4 PIECES. (TC NR 20080227006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20080530     GL  2008       5          30         CA080227007      220080227G72306898607         BEARING RACE                            BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              COMPRESSOR      SPALLED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1399                                                           DURING FLIGHT THE PILOT HAD A CHIP LIGHT INDICATION.  UPON INSPECTION, THE CHIP PLUG HAD LITTLE DEBRIS AND SMUDGE.  THE CHIP WAS CLEANED, REINSTALLED AND FURTHER GROUND RUNS WHERE CARRIED OUT PRIOR TO FLIGHT.  NO FURTHER ISSUES WERE NOTED AND THE FLIGHT CONTINUED.  A FEW HOURS LATER ANOTHER CHIP LIGHT HAD ILLUMINATED.  THE AIRCRAFT WAS RETURNED TO THE BASE VIA TRUCK AND TRAILER.  FURTHER INVESTIGATION REVEALED FWD CHIP PLUG HAD METAL EVIDENT ON THE PLUG.  THE COMPRESSOR WAS REMOVED AND THE NR 1 BEARING INNER RACE SHOWED EVIDENCE OF SPALLING.  THE GEARBOX ALSO HAD AN ISSUE ADDRESSED BY ANOTHER SDR RELATED TO THIS AIRCRAFT.  WILL SUBMIT PICTURES WHEN THEY ARE AVAILABLE. (TC# 20080227007)                          1G71 3U3  U  H2SW    E4CE                 
             20080530     SW  2008       5          30         CA080227008      120080227G632023034787        BEARING RACE                            BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              GEARBOX         SPALLED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       6794                                                           (CAN) METAL WAS FOUND ON ENGINE LOWER CHIP PLUG.  THE 2 1/2 BEARING IN THE GEARBOX WAS REMOVED AND FOUND THE SPALLING ON THE OUTER RACE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E4CE                 
             20080603     NM  2008       6          3          CA080228001      120080119G3230C247300016      UPLOCK                                  AIRBUSA319  A319114     3930350NM  GE    CFM56 CFM565A     13802NE                              NLG             FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       29460                                                          AFTER TAKEOFF, THE CREW COULD NOT RETRACT THE NOSE GEAR.  THE GEAR WAS RECYCLED WITH NO SUCCESS.  THE CREW RETURNED TO LAND AT DEPARTURE AIRPORT.  THE NLG UPLOCK ASSEMBLY WAS REPLACED AND A LANDING GEAR SWING CARRIED OUT.  DESCRIPTION/ROOT CAUSE, THE UNIT WAS SENT FOR REPAIR WITH THE REQUEST FOR A TEARDOWN REPORT.  THE UNIT WAS PRE-TESTED AND FAILED THE LOCKING TEST.  THE LOCK MECHANISM INSIDE THE UNIT FAILED TO LOCK THE HOOK.  THE REPAIR FACILITY CONCLUDED THAT THE DRIED GREASE CAUSED THE LOCKING MECHANISM TO HANG UP AND PREVENTED THE HOOK FROM LOCKING THE NOSE LANDING GEAR.  THE WEAR TO THE UNIT WAS NORMAL AND NO OTHER MECHANICAL DIFFICULTIES WERE OBSERVED.  AT TIME OF THIS REPORT THE REPAIR ORGANIZATION WAS 2L72 4F4  FRTA28NM   E29NE                
200805141    200805141    NM  2008       5          14         CA080228002      120080222G531517003264001     FLOORBEAM                               EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 . ALSO (3) SILL PLATES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FR 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE FRAME 87, 89, 90 NR FLOORBEAM FRAME 18 POSSIBLE ROOT CAUSE: FLOOR PROTECTION UNDERNEATH THE GALLEY NOT ADEQUATE. (TC NR 20080228002)                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA56NM   E00063EN             
             20080521     NM  2008       5          21         CA080228003      120080215G215018279018        ACM                                     DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE                  FAILED          W      GA  O2 MASK DEPLOYED        UNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA       12421                                                          (CAN) DURING CLIMB, CREW NOTICED A SMELL OF SMOKE IN THE FLIGHT DECK. CREW DONNED OXYGEN MASKS AND COMPLETED THE (OXYGEN DRILL). UNSCHEDULED LANDING COMPLETED. ENGINEERING ONSITE INVESTIGATION CONFIRMED FAILURE OF THE AFT AIR CYCLE MACHINE (ACM). THE AFT ACM WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. ACM HAS BEEN DISPATCHED TO THE MFG FOR REPAIR/OVERHAUL WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20080228003)                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080521     NM  2008       5          21         CA080228004      120080219G3230483025          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R320  CR3204123F1 GL  NLG             FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA       93                                                             (CAN) AN OPERATOR COMPLETED AN EMERGENCY LANDING DUE TO NLG DOOR OPEN INDICATION AFTER SELECTING GEAR UP. UNSCHEDULED LANDING, CREW FOLLOWED THEIR QRH, PERFORMED ALTERNATE GEAR EXTENSION. NLG SOLENOID SEQUENCE VALVE REPLACED. (TC NT 20080228004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E00062EN6  CP5NE     
             20081104     SW  2008       11         4          CA080228007      120080124G3246206050297105    SKID                                    BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8330                                                           (CAN) UPON INSTALLATION OF GROUND HANDLING WHEELS IT WAS DISCOVERED THAT THE MOUNTING LUGS ON THE FWD LT SIDE WAS DETACHED AND LOOSE DUE TO LARGE PERFORATION (HOLE) IN THE ATTACHMENT AREA. FURTHER VISUAL INSPECTION REVEALED CIRCUMFERENTIAL CRACK APPROXIMATELY (3) QUARTERS AROUND THE SKID TUBE, SLIGHTLY FWD OF THE SADDLE LOCATION AND RUNNING AROUND THE BOTTOM PORTION OF THE TUBE. EXTENSIVE CORROSION ALSO DETECTED IN AND AROUND AFFECTED AREA. SKID TUBE REPLACED WITH NEW UNIT. (TC NR 20080228007)                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E4CE                 
             20080521     NM  2008       5          21         CA080228009      120080225G3260                SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R320  CR3204123F1 GL  MLG DOWNLOCK    FAULTED         W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      (CAN) AFTER DEPARTURE, AN ABNORMAL GEAR INDICATION WAS OBSERVED. DECISION TO CONTINUE TO NEXT BASE IAW MCC AND OCM. ON ARRIVAL, ALTERNATE GEAR EXTENSION, ACCORDING PROCEDURE PERFORMED. NORMAL INDICATION (3 GREEN) ON MAIN AND ALTERNATE SYS. DURING FINAL: GEAR UNSAFE-INDICATION ON MAIN INDICATION AGAIN, NORMAL INDICATION ON ALTERNATE SYS. UNEVENTFUL LANDING AND NORMAL DISEMBARKATION ON THE RUNWAY FOLLOWED. PSEU FAULT CODES AS FOLLOWS: LEG 00: LGDLK 1 PROX SENSOR OPEN, LGDLK 1 PROX SENSOR SHORT, PSEU CHANNEL D FAIL CHANNEL INOP, LGDLK1 UNREASONABLE NEAR, NLGLK2 UNREASONABLE NEAR, NLGLK1 UNREASONABLE NEAR, NGDRCL UNREASONABLE NEAR, NGWOFW2 UNREASONABLE NEAR NGWOFW1 UNREASONABLE NEAR, NGDN2 UNREASONABLE FAR, NGDN1 U2H72 4T4  TRTA13NM   E00062EN6  CP5NE     
             20080521     NM  2008       5          21         CA080228010      120080225G2750734386B         TORQUE TUBE                             DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  TE FLAPS        SHEARED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) A/C WAS ON APPROACH INTO AIRPORT, THE FLAPS WERE LOWERED TO 15 DEG WHEN THE (FLAP DRIVE CAUTION LIGHT) CAME ON. THE A/C LANDED WITHOUT INCIDENT. MAINT INSP REVEALED THAT THE LT OB TORQUE TUBE WAS SHEARED OFF. AFTER FURTHER INSP, IT WAS DETERMINED THAT THE TORQUE TUBE WAS SHEARED OFF BY CLAMP INSTALLED ON A DRAIN LINE THAT HAD BEEN CHAFING. THE TORQUE TUBE WAS REPLACED, THE TORQUE SENSOR RIGGED AND THE FLAPS WERE FUNCTION CHECKED SERVICEABLE. (TC NR 20080228010)                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080602     SW  2008       6          2          CA080228011      120080227G32302752003042      BELLCRANK                               SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE3311     01514WP  MCAULY4HFR344HFR34C652  NE  NLG             MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING MAINTENANCE GEAR RETRACTION A "CLICKING" NOISE WAS HEARD FROM THE NOSE GEAR WHEELWELL.  THE ROLLER BEARING ON THE RT NOSE GEAR BELLCRANK WAS BROKEN AND ONLY THE INNER RACE REMAINED ON THE BOLT. THE BELLCRANK WAS REPLACED, GEARSWINGS CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE (TC NR 20080228011)                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T3  TRTA8SW    E3WE    6  C3PNE     
             20080602     SW  2008       6          2          CA080228012      120080220G3222MS171536        PIN             FRCHLD                  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE3311     01514WP  MCAULY4HFR344HFR34C652  NE  RH TORQUE KNEE  DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      PIVOT PIN FOR RT MAIN GEAR TORQUE KNEE WAS PROTRUDING FROM THE TORQUE KNEE.  SPRING PIN REMOVED AND INSPECTED.  NO DAMAGE FOUND.  NEW SPRING PIN INSTALLED.  NO FURTHER PROBLEMS SINCE REPLACEMENT OF SPRING PIN (TC NR 20080228012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T3  TRTA8SW    E3WE    6  C3PNE     
             20080602     EA  2008       6          2          CA080229001      120080218G5610NP1393222       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       10959                                                          FLT NR 6671 - FIRST OFFICER SIDE WINDOW CRACKED ON DESCENT INTO PSP.  WINDOW REPLACED (TC NR 20080229001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
             20080602     NE  2008       6          2          CA080229002      220080221G72004129T17G04      ACTUATOR                                CNDAIRCL600 CL6002D24   1390016EA  GE    CF34  CF348C1     30049NE                              LT ENGINE       CRACKED         W      O   OTHER                                                                                           YJ ENGINE STOPPAGE           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      "925 PWM, LT ENG FAILURE ON SHORT FINAL. ON SHORT FINAL (APPROX 1500 FT) CAPT REPORTED LT ENGINE FAILURE.  N1 WENT TO 32 PERCENT AND EICAS DISPLAYED LT FADEC AND LT BLEED CAUTION ME PERCENT.  CAPT SAW NO OTHER ENGINE RELATED ANOMALIES, IE NO PROBLEMS WITH FUEL FLOW, ITT, OIL PRESSURE OR WARNINGS.  CVR AND FDR CIRCUIT BREAKERS HAVE BEEN PULLED.  AIRCRAFT VERIFIED NOT IMPOUNDED BY THE NTSB.  CONTRACT MX INTERROGATE MDC.  MDC REVEALED LH PS3 SENSE LINE, L FMU FAILED AND VG CMD\POSN DISAGREE.  MX INSPECT INLET FOR POSSIBLE INGESTION, NO FINDINGS.  EXHAUST AREA LOOKED GOOD AS WELL.  OPENED COWLING AND INSPECTED VG ACTUATORS AND AREA.  MX THOROUGHLY INSPECTING AREA.  WE HAVE SENT MM/IPC REFERENCES OF AREAS TO INSPECT2L72 4F4  FRTA21EA   E00063EN             
200805141    200805141    NM  2008       5          14         CA080229003      120080221G3260864202          PROXIMITY SENSOR                        DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NLG             INTERMITTENT    W      D   RETURN TO BLOCK                                                                                 N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA                                                                      (CAN) GEAR UNSAFE (NOSE GEAR) ILLUMINATED DURING TAXI-IN WITH ASSOCIATED GEAR WARNING HORN. AC WAS STOPPED AND SHUTDOWN, EMERGENCY SERVICES REQUESTED FROM TOWER. F/O INSERTED NOSE GEAR LOCK IMMEDIATELY AFTER SHUTDOWN. ENGINEERING INSPECTED THE AC AND TOWED IT TO BAY. MAINT CARRIED OUT INDUCTANCE, CONTINUITY AND MEGGER CHECK OF THE NLG DOWNLOCK SENSOR AND NLG DRAG STRUT SENSOR. THE NLG DRAG STRUT SENSOR 3261-S10 (WDM REF NR) WAS FOUND TO HAVE VARIABLE INSULATION OF 100 MEGA OHMS. THE NLG DRAG STRUT SENSOR WAS REPLACED IAW THE AC MM 32-20-11. NLG RETRACTION AND EXTENSION CHECKS/ TESTS CARRIED OUT IAW AC MM 32-30-00, ALL INDICATIONS CHECKED SERVICEABLE. AC RETURNED TO SERVICE. (TC NR 20080229003)                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080521     CE  2008       5          21         CA080229004      120080228G2420                PULLEY                                  CESSNA210   210R        2073458CE  CONT  O520  IO520L      17032SO  MCAULYD3A34 D3A34C404   GL  ALTERNATOR      SEPARATED       W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA            51                                                        (CAN) WHILE IN FLIGHT, NR1 ALTERNATOR FAILED,  NR1 ALT AMBER LIGHT CAME ON, ON THE GROUND, INSP REVEALED THAT THE DRIVE PULLEY HAD SEPARATED FROM ALTERNATOR, PULLEY FOUND DAMAGED WITH OTHER BROKEN PULLEY PIECES ON THE BUTTOM OF COWLING.  RETAINING NUT HAD GONE AWAY. END SHAFT (ARMATURE) WAS NOT SEIZED.  SUSPECT A QC PROBLEM IN THIS CASE. ALTERNATOR REPLACED WITH O/H UNIT. (TC NR 20080229004)                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ORT3A21    E5CE    5  CP47GL    
             20080521     CE  2008       5          21         CA080229005      120080229G57530512128         BRACKET                                 CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  TE FLAPS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7402                                                           (CAN) ON PREFLIGHT INSPECTION, PILOT FOUND WHEN FLAPS EXTENDED, LT FLAP HAD NO TENSION, AND COULD BE LIFTED TO THE RETRACT POSITION, POTENTIALLY CAUSING DISIMILAR LIFT WHEN ACTIVATED IN FLIGHT.  INSPECTED AREA, AND FOUND LT BRACKET BROKEN AT F.S. 65.33, IB MOUNTING TABS BROKEN. SIMILAR OCCURANCE  INSPECTED AREA EACH 100 HRS SINCE, NO INDICATION OF CRACKS PREVIOUSLY DETECTED.  SUSPECT THAT FAILURE IS IMMEDIATE AS BREAKS LOOK NEW. POORLY DESIGNED PART FOR LOADS THAT ARE IMPOSED. (TC NR 20080229005)                                                                                                                                                                                                                           1H71 3O3  O  3A24    E5CE    5  CP3EA     
             20080521         2008       5          21         CA080229007      420080220G2565416T28243       LEVER                                   BOEING767   76735H      1385208NM  GE    CF6   CF680C2B6F  30025NE                              OVERWING SLIDE  MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) OVER-WING SLIDE COMPARTMENT DOOR OPENING ACTUATING MECHASIM - LEVER DESCRIPTION: A LEVER THAT JOINS THE FIRING PIN CLEVIS OF THE OFF-WING ESCAPE SLIDE COMPARTMENT DOOR OPENING ACTUATOR TO THE ACTUATING ROD IS BEING INSTALLED UPSIDE-DOWN. THIS APPEARS TO CAUSE THE LEVER TO BIND WITH THE FIRING PIN CLEVIS AND COULD PREVENT NORMAL DOOR OPENING ACTUATION IN A REAL SITUATION.  IT SEEMS THAT NO SDR WAS RAISED FOR THE PREVIOUS FINDING. LEVER ORIENTATION CORRECTED IAW DIAGRAMS SUPPLIED IN THE IPC AS WELL AS THOSE DIAGRAMS INCLUDED WITH THE RIGGING INSTRUCTIONS IN THE AMM. ENGINEERING APPROACHED TO ADDRESS A POSSIBLE AMENDMENT TO THE AMM. (TC NR 20080229007)                                                         2L72 4F4  FRTA1NM    E13NE                
             20080521     GL  2008       5          21         CA080229008      220080206G7200                ENGINE                                  BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                                              VIBRATION       W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA                                                                      (CAN) EXCESSIVE ENGINE NOISE AND HIGH VIBRATION FELT BY PILOT AT GROUND IDLE. VERFIED BY ENGINEER. COMPLETE ENGINE REMOVED AND SENT FOR INVESTIGATION. WILL FWD REPORT WHEN AVAILABLE. (TC NR 20080229008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UO H2SW    E1GL                 
             20080521     GL  2008       5          21         CA080229010      220080227G7230                SCROLL          ALLSN                   BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              COMPRESSOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COMPRESSOR 390.6 SINCE 2000 HOUR INSP.  CRACK LOCATED BY ENGINEER DURING GROUND RUN UP FOLLOWING SCHEDULED INSP. LOCATED BY AIR LEAK FOUND BY BARE HAND CHECK. CRACK LOCATED SLIGHTLY BELOW SCROLL ARMPIT REINFORCEMENT PATCH AREA, NOT IN NORMAL CRACK LOCATION. A SMALL PIECE OF PATCH MATERIAL ALSO FOUND MISSING. COMPRESSOR REMOVED AND SENT FOR REPAIR. (TC NR 20080229010)                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  UO H2SW    E1GL                 
             20080521     SO  2008       5          21         CA080229011      120080226G81204091701         SHAFT                                   PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  TURBOCHARGER    SHEARED         W      A   UNSCHED LANDING                                                                                 BR SMOKE/FUMES/ODORS/SPARKS  PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA            3                                                         (CAN) SHORTLY AFTER TAKEOFF, WHEN SETTING CRUISE POWER, THE LT ENGINE WOULD NOT STAY AT CRUISE POWER.  AFTER A COUPLE OF ADJUSTMENTS THE POWER DROPPED FROM 31IN TO AS LOW AS 12IN OF MANIFOLD PRESSURE. THE AIRCRAFT RETURNED FOR LANDING. MAINT FOUND THE SHAFT THAT CONNECTS THE EXHAUST AND INTAKE TURBINE WHEELS ON THE TURBOCHARGER WAS BROKEN AT THE EXHAUST TURBINE WHEEL. NO REASON COULD BE FOUND FOR THE FAILURE. THE TURBOCHARGER HAD 2.7 HOURS SINCE OVERHAUL. (TC NR 20080229011)                                                                                                                                                                                                                                                 1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20080521     EA  2008       5          21         CA080229012      220080229G8530LW12966         CYLINDER                                PIPER PA28  PA28140     7102802SO  LYC   O540  TIO540J2BD  41532EA                              ENGINE          UNSERVICEABLE   W      BA  EMER. DESCENT           UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA       150                                                            (CAN) PILOT HEARD A BANG WHILE IN CRUISE AND NOTICED A LOSS OF POWER. TURNED BACK TO THE NEAREST AIRPORT TO LAND. UPON INSPECTION THE AME FOUND THAT THE NR1 INTAKE VALVE WAS MISSING. THE ENGINE WAS REMOVED. WHEN WE REMOVED THE NR1 CYLINDER, WE FOUND THAT THE INTAKE VALVE HAD BROKEN OFF AT THE KEEPERS AND A PIECE HAD SHOT OUT THE SIDE OF THE PORT AND LODGED ITSELF IN THE FINS OF THE NR3 CYLINDER. THERE WAS CONSIDERABLE DAMAGE TO BOTH CYLINDERS. THE REST OF THE VALVE HAS YET TO BE SEEN BUT IT IS EXPECTED TO BE FOUND ONCE WE REMOVE THE INDUCTION COVER. (TC NR 20080229012)                                                                                                                                                 1L71 3O3  O  2A13    E14EA                
             20080521     NM  2008       5          21         CA080303001      120080228G5315                FLOORBEAM                               EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3948                                                           (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18, 19 AND ON FLOORBEAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR12 AND 14 , 14 AT Y = -337.0 AND Z = -490.0 ALSO THREE SILL PLATES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS IAW MFG INSTRUCTION.  (TC NR 20080303001)                                                                                                                 2L72 4F4  FRTA56NM   E00063EN             
             20080602     NM  2008       6          2          CA080303002      120080228G271017005825401     CONTROL CABLE                           EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              AILERONS        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3948                                                           DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401) WORN AND WITH WIRES BROKEN AT FAIRLEADS, LOCATED AT LT WINGS INB OF THE RIB 17.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD.  EMBRAER HAVE BEEN ADVISED (TC NR 20080303002)                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA56NM   E00063EN             
             20080603     SO  2008       6          3          CA080303003      120080229G2421                BEARING                                 PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2     GL  ALTERNATOR      FAILED          W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA            1093                                                      IN CRUISE, THE PILOT NOTICED THE RT ALTERNATOR WARNING LIGHT CAME ON.  CHECKED THE BREAKER BUT IT HAD NOT BLOWN.  PULLED BREAKER AND LANDED UNEVENTFULLY.  MAINTENANCE INSPECTED THE RT ALTERNATOR AND DISCOVERED THAT THE ALTERNATOR BEARING HAD SEIZED AND BROKEN THE BELT. (TC NR 20080303003)                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081104     SW  2008       11         4          CA080303004      120080303G6510327211          DISC PACK                               BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              T/R DRIVE       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2562                                                           (CAN) DISC PAC WAS REMOVED FOR INSPECTION DURING A SCHEDULED 1200 HOUR INSPECTION. CRACKED DISC WAS DISCOVERED DURING DISASSEMBLY. ONE DISC OF TEN IN PAC WAS COMPLETELY CRACKED ON BOTH SIDES ON ATTACHEMENT BOLT HOLE SO THAT A PIECE OF THE DISC WAS BROKEN AWAY. THE REMAINDER OF THE DISCS WERE CORRODED ON BOTH SIDES OF THE DISC IN THE SAME AREA CLOSEST TO THE BOLT HOLE.                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E1GL                 
             20080603     GL  2008       6          3          CA080303005      220080302G732223034702        FUEL CONTROL                            BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2936                                                      AFTER INSTALLING THE FCU, IT WAS NOTED THAT FUEL WAS LEAKING FROM LOWER THROTTLE ARM HOUSING.  FCU WAS REMOVED. (TC NR 20080303005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H2SW    E4CE                 
             20090102     CE  2009       1          2          CA080303006      120080303G3411                STATIC PORT                             BEECH 23    B23         1151240CE  LYC   O360  O360A2G     41514EA  SNSNCH76E   M76EMMS     EA  RT              OBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2312 2312                                                      (CAN) WHILE DOING A PRE-PURCHASE INSP, DISCOVERED A PIECE OF TAPE COVERING THE RT STATIC PORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ORTA1CE    E286    5  NP4EA4    
             20081104     SW  2008       11         4          CA080303008      120080229G6520476400751       GEARBOX                                 BELL  47    47G2        1181008SW  LYC   O435  VO435A1D    41516EA                              TAIL ROTOR      MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3110 948                                                       (CAN) UPON WALK AROUND OIL IN GEARBOX LOOKED DIRTY, OIL WAS DRAINED AND METAL WAS FOUND ON MAGNETIC PLUG, TAIL ROTOR GEARBOX WAS REMOVED FROM SERVICE AND OH ONE INSTALLED AND ACFT WAS RELEASED. MORE INFO WILL BE POSTED AS THE GEARBOX IS DISASSEMBLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H1      E279                 
             20080521     EA  2008       5          21         CA080303009      220080301G855077517           SUMP                                    FOUND FBA   FBA2C1      3640103EA  LYC   O540  IO540L1A5   41532EA  HARTZLHCC3Y HCC3YR      GL  ENGINE OIL SYS  UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1100                                                           (CAN) OIL SUMP WAS REMOVED TO INSPECT SUMP BAFFLE IAW SB. INTERNAL CRACK IN THE SUMP WAS FOUND NEAR ONE OF THE MOUNTING LUGS.  IAW THE SB, THE OIL SUMP BAFFLE HAD A LACK OF CLEARANCE AND HAD BEEN RUBBING THE BOTTOM OF THE SUMP. BAFFLE, AND SUMP HAD SIGNS OF WEAR. BAFFLE WAS LOOSE, AND HAD (2) BROKEN CONTACT POINTS.  ENGINE REMOVED TO FURTHER DETERMINE CONTAMINATION AND SERVICEABILITY. (TC NR 20080303009)                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONCA7EA    1E4     5  CP25EA    
200805141    200805141        2008       5          14         CA080304001      420080204G3418543036B29       COMPUTER                                CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF343A2     30067NE                              STALL WARNING   FAULTY          W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) IT TOOK (3) STALL WARNING COMPUTER BEFORE GETTING ONE THAT WAS SERVICEABLE , THEY ALL FAIL THE TEST IAW TEST PROCEDURE MM PSP601-2 CHAP 27-39-00 P 206 207 NB MFG PRODUCTS (TC NR 20080304001).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20080602     NM  2008       6          2          CA080304003      120080229G2497IN3311B         DIODE                                   BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                                              OPEN            W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         CRCRUISE         1                      CA                                                                      EN ROUTE, AFTER SHUTTING OFF CENTER TANK BOOST PUMPS, LEFT CENTER, LEFT AFT AND RIGHT FORWARD LOW PRESSURE LIGHTS DID NOT ILLUMINATE.  WINDOW HEAT LIGHTS FOR THE LEFT SIDE WINDOW AND RIGHT FORWARD WINDOW WERE NOT ILLUMINATED.  INITIALLY NO MASTER CAUTION, THEN ANTI-ICE MASTER CAUTION.  THERE WAS NO LE DEVICES INDICATION.  ON DOWNWIND FOR LANDING, THE PRESSURIZATION WENT FROM AUTO TO STANDBY AND DUMPED PRESSURE.  UPON LOWERING GEAR, NO GREEN LIGHTS.  THE CREW OVERSHOT AND USED THE GEAR VIEWERS AND A FLY BY TO DETERMINE THE GEAR STATUS.  AFTER SPEAKING WITH DISPATCH, THE LIGHTS WERE CYCLED THROUGH BRIGHT/DIM/TEST AND THE GEAR INDICATION RETURNED.  THE AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT.  MAINTENANCE WAS2L72 4F4  FRTA16WE   E21EU                
             20080602         2008       6          2          CA080304004      420080303G34165035PP41        ENCODER                                                                                                                                 ALTIMETER       DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      WHEN RECEIVED FOUND WITH TIN BETWEEN CASE AND PIN ON CONNECTION RECEPTACLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               
             20080602     EU  2008       6          2          CA080304005      120080227G2910A3248021101100  LINE                                    AIRBUS310   A310304     3930339EU  GE    CF6   CF680C           GL                              HYD SYSTEM      SPLIT           W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      WHILE AIRCRAFT WAS UNDER MAINTENANCE IN THE HANGAR, THE HYDRAULIC RETURN LINE FOR YELLOW SYSTEM ALTERNATE BRAKE FAILED WITH A SPLIT IN THE TUBING APPROX 1.5 INCHES IN LENGTH.  AT THE TIME OF THE FAILURE THERE WAS NO HYDRAULIC PRESSURE OR OPERATION OF THE SYSTEM.  THE LINE WAS REPLACED AND SYSTEM TESTED SERVICEABLE.  LINE WAS SENT TO AIRBUS FOR ANALYSIS. (TC NR 20080304005)                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA35EU   E23EA                
             20080602         2008       6          2          CA080304006      120080304G8011                STARTER                                                                                                                                 ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      AFTER INSTALLATION TEST FOR FUNCTIONAL START, THE ENGINE LIGHT STAY ON IN THE COCKPIT.  FOUND BY OUR TECHNICIAN THAT THE RECEPTACLE PLUG ON THE STARTER PIN B GROUNDED ALL THE TIME. (TC NR 20080304006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20080521     EA  2008       5          21         CA080304007      220080205G8500                ENGINE                                  PIPER PA31  PA31310     7103103SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL                  MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A SCHEDULED INSP, LARGE QUANTITIES OF FERROUS PARTICLES WERE DISCOVERED IN THE PAPER ELEMENT OF THE ENGINE OIL FILTER. LARGER PIECES WERE ALSO DISCOVERED IN THE OIL SUCTION SCREEN FINGER. THE AC IS GROUNDED PENDING REPLACEMENT OF THE AFFECTED ENGINE. ANALYSIS OF THE FILTER ELEMENT REVEALED FINES AND FLAKES OF CARBON STEEL AMS NR 6440 OR 6444 WHICH INDICATES CAMSHAFT AND FOLLOWERS, ALTHOUGH THIS IS NOT AS YET SUBSTANTIATED. THE ENGINE HAS BEEN OPERATED FOR 88.1 HOURS SINCE OVERHAUL FOR AN IDENTICAL FAULT WHERE THE NR 5 CAM LOBE WAS FOUND WORN BEYOND LIMITS. THE ENGINE IS CURRENTLY EN ROUTE FROM INDIA TO THE ORIGINAL ENGINE OVERHAUL SHOP FOR PRECISE FAULT IDENTIFICATION. (TC NR 20080304007)          1L71 3O3  ORTA20SO   E14EA   5  CP33EA    
             20080521     WP  2008       5          21         CA080304009      220080303G73218978017         FUEL CONTROL                            SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3518                                                           (CAN) ENGINE HAD BEEN REMOVED IN RUNNING CONDITION FOR SCHEDULED HOT SECTION/GEARBOX INSP. ENG SENT TO ENGINE SHOP. UPON INITIAL START UP FOR THE TEST CELL RUN, THE ENGINE WOULD NOT START. FUEL CAME OUT THE DRAINS AND THE BACK OF THE ENGINE. THE FUEL PUMP PRESSURE WAS TESTED AND WITHIN LIMITS. THE FUEL CONTROL WAS REMOVED AND THE DRIVE SHAFT TURNED WITH NO RESISTANCE, LIKE SOMETHING HAD FAILED INSIDE. THIS FUEL CONTROL IS POST AD 2006-15-08 COMPLIANT AND THE FIRST FAILURE OF THIS TYPE SEEN BY THE OPERATOR OR THE ENGINE SHOP ON ONE OF THESE PN.  UNIT TBO IS 7000 HOURS NORMALLY. UNIT HAS BEEN SENT FOR REPAIR AND A TEARDOWN REPORT REQUESTED. (TC NR 20080304009)                                                      2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
             20080521     EA  2008       5          21         CA080304010      120080303G3230533407          SELECTOR VALVE                          CNDAIRCL600 CL6002C10   1390015EA  GE    CF700 CF7002D2    30010NE                              MLG             FAILED          W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN)  DISC LANDING GEAR WOULD NOT EXTEND. PERFORMED MANUAL/EMERGENCY EXTENTION. ENG HYDR PUMP PRESSURE WAS NORMAL. REMOVED AND REPLACED  LANDING GEAR SELECTOR VALVE IAW AMM 32-32-10. ADDITIONAL INFORMATION: ATTEMPTED TO EXTEND GEAR 3 TIMES BUT FAILED. DID GET A LG DISAGREE WARNING. HAD TO DO A GO AROUND TO GET GEARDOWN. (TC NR 20080304010)                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E7EA                 
             20080521     CE  2008       5          21         CA080304011      120080118G323399101399        ACTUATOR                                CESSNA441   441         2076020CE  GARRTTTPE331TPE3318     01514WP  HARTZLHCB3T HCB3TN5     GL  NLG             FAILED          W      O   OTHER                                                                                           Z  SIGNIFICANT FAILURE REPORT                                                    LDLANDING        1                      CA                                                                      (CAN) AIRCRAFT INDICATED (3 GREEN) ON APPROACH, UPON LANDING, NOSE GEAR RETRACTED RESULTING IN AC DAMAGE. UPON ARRIVAL, MAINT NOTED GEAR INDICATION REMAINED (3 GREEN) AND AC WAS SITTING ON ITS NOSE. THE AC WAS RAISED AND THE NOSE GEAR WAS PULLED INTO THE DOWN AND LOCKED POSITION. INITIAL INSP OF THE GEAR SYS FOUND ALL TO BE IN WORKING ORDER, GEAR SWINGS PERFORMED NORMALLY. THE ACTUATOR`S INTEGRAL POSITION INDICATION SWITCH MALFUNCTIONED CAUSING THE HYD SYS PRESSURE TO THE NOSE GEAR ACTUATOR TO STOP PREMATURELY BEFORE THE NOSE GEAR WAS FULLY EXTENDED AND IN THE OVER CENTER POSITION. (TC NR 20080304011)                                                                                                                1L72 3T4  TRTA28CE   E4WE    6  CP15EA    
             20081104     WP  2008       11         4          CA080304012      120080302G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       289                                                            (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK.                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
             20081104     WP  2008       11         4          CA080304013      120080228G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14                                                             (CAN) STARTER -COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304013)                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
             20081104     WP  2008       11         4          CA080304014      120080217G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       62                                                             (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304014)                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20080602     GL  2008       6          2          CA080305001      220080303G7261                PRESSURE SWITCH                         AIRBUS310   A310304     3930339EU  GE    CF6   CF680C           GL                              ENGINE OIL      MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA       479931630                                                      DURING CLIMB AT 18000 FEET, NR 1 ENGINE OIL FILTER CLOGGED LIGHT CAME ON.  AS PER QRH, NR 1 ENGINE WAS SHUT DOWN.  AIRCRAFT RETURNED TO STATION WITH NO FURTHER PROBLEM.  THE OIL FILTER WAS REPLACED.  NO SIGNIFICANT CONTAMINATION WAS NOTICED.  THE OIL SYSTEM WAS DRAINED AND SERVICED AS PER MM.  THE OIL DIFFERENTIAL PRESSURE SWITCH WAS REPLACED.  A TEST FLIGHT WAS PERFORMED AND THE ENGINE OIL INDICATION SYSTEM WAS NORMAL.  AIRCRAFT WAS RETURN TO SERVICE.                                                                                                                                                                                                                                                                        2L72 4F4  FRTA35EU   E23EA                
             20080521     CE  2008       5          21         CA080305002      120080303G2121C4140070102     COOLING FAN                             CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  COCKPIT         NOISY           W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) ON CLIMBOUT FLIGHT CREW HEARD A LOUD SQUEALING NOISE FROM THE AVIONICS COOLING FAN. IN COLD TEMPERATURES THIS IS TYPICAL OF THE COOLING FAN AND THE FLIGHT CREW DECIDED TO ALLOW THE FAN TO WARM UP. AFTER A COUPLE MINUTES THE FLIGHT CREW DECIDED TO RETURN. APPROX 5 MINUTES LATER DURING VECTORS BACK THE FLIGHT CREW BEGAN TO SMELL A BURNED SMELL IN THE COCKPIT AND PULLED THE AVIONICS FAN CIRCUIT BREAKER, THE SMELL STOPPED. AT THE TIME, THE FLIGHT CREW ALSO COMMENTED ON SMOKE LIGHT, SMOKE IN THE COCKPIT. THE FLIGHT WAS CONTINUED AND LANDED WITHOUT FURTHER INCIDENT. MAINT REPLACED THE AVIONICS COOLING FAN AND GROUND RUN THE AC WITHOUT ANY ADDITIONAL FAULTS. THE AC WAS RELEASED. (TC NR 20080305002)              1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081104     NE  2008       11         4          CA080305003      220080228G7200                PIN                                     SKRSKYS92   S92A               NE  GE    CT7TS CT78A       30136NE                              ENGINE          FOD             W      O   OTHER                                                                                           CR F.O.D.                    PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA                                                                      (CAN) ON RETURN FLIGHT AN EPAC (POWER CHECK) WAS ATTEMPTED BUT WOULD NOT COMPLETE (A USUAL CASE IN PARTICULAR ACFT) NRS WERE NOTED FOR MAINT STAFF AND ON RETURNING TO BASE ANOTHER EPAC WAS RUN AND COMPLETED. MAINT STAFF WAS NOTIFIED UPON ARRIVAL AT AIRPORT AND DAMAGE IN ENGINE PARTICLE SEPARATOR WAS NOTICED. SMALL HANDLE. PIN FROM HINGE ASSY FOUND TO HAVE BECOME DETACHED FROM ASSY AND ENTERED THE ENGINE INTAKE RESULTING IN FOD DAMAGE TO ENGINE.                                                                                                                                                                                                                                                                                2G72 4U4  U  R00024BOE8NE                 
200805141    200805141    NM  2008       5          14         CA080305004      120080221G381014C3308         COUPLER                                 BOEING737   7378Q8      13844BXNM  CFMINTCFM56 CFM567B26US      NE                              POTABLE WATER   CRACKED         W      BG  EMER. DESCENT           O2 MASK DEPLOYED                                                        ZS SIGNIFICANT FAILURE REPORTAFFECT SYSTEMS                                      CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, CREW NOTED CABIN ALTITUDE WARNING. UNABLE TO CLOSE OUTFLOW VALVE EITHER ELECTRICALLY OR MANUALLY. EMERGENCY DESCENT PERFORMED, OXYGEN MASKS DROPPED. OUTFLOW VALVE WOULD CLOSE TO THE .2500 POSITION ON GAUGE. ATTEMPTED TO CLOSE VALVE MANUALLY AT 10000FT (OAT +13 DEG C), NO RESPONSE. VALVE CLOSED SUCCESSFULLY AFTER 10 MIN. ON INSP FOUND PORTABLE WATER LEAKING AT FITTING AND FITTING PARTLY SEPARATED WITH WIGGENS COUPLING OPEN. UPON INSP OF REMOVED COUPLING FOUND CRACKED. (TC NR 20080305004)                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E00055EN             
             20080521     EU  2008       5          21         CA080305008      120080225G2421ALU8521R        ALTERNATOR                              ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA  MUHBR MTV   MTV9*       EU                  FAILED          W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA       1034                                                           (CAN) PILOT EXPERIENCED A COMPLETE ELECTRICAL FAILURE. SUBSEQUENT INVESTIGATION REVEALED A MELTED INSULATOR ON THE (BATT) TERMINAL OF THE ALTERNATOR. THE (BATT) WIRE TERMINAL END WAS MELTED AND BROKEN WITH THE FREE END CONTACTING THE ALTERNATOR CASE. THE FREE WIRE ENABLED A RAPID DISCHARGE OF THE BATTERY. (TC NR 20080305008)                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O0 A76EU   1E10    5  CP24NE    
             20080521     SO  2008       5          21         CA080305011      120080305G2140CD21252         SWITCH                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2B        NE  HARTZLHCE3Y HCE3YR2A    GL  HEATER          INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       31                                                             (CAN) THE PILOT REPORTED THAT THE HEATER DID NOT WORK. MAINT INVESTIGATED AND DETERMINED THAT THE CYCLING SWITCH WAS DEFECTIVE AND REPLACED THE SWITCH. THE CREW AGAIN REPORTED THAT THE HEATER DID NOT WORK PROPERLY. MAINT DID MORE TROUBLESHOOTING AND DETERMINED THAT THE CYCLING SWITCH FUNCTIONED PROPERLY INSIDE A HEATED HANGAR. HOWEVER WHEN LEFT OUTSIDE AT ABOUT -20 DEGREES CELSIUS THE SECOND SWITCH ALSO FAILED TO FUNCTION PROPERLY. THE HEATER WAS INSTALLED NEW ABOUT 218 HRS AGO AND THE FIRST CYCLING SWITCH FAILED AFTER 188.3 HRS.  (TC NR 20080305011)                                                                                                                                                                    1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20080521     NE  2008       5          21         CA080305012      220080219G7320                EEC                                     CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              ENGINE          MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKEOFF ROLL, THE ENGINE ELECTRONIC CONTROL DROPPED OFF LINE. THE CREW ADVANCED THE THRUST LEVER TO ACHIEVE REQUIRED THRUST, BUT THE POWER LEVEL REMAINED 10 PERCENT LESS THAN THE REQUIRED LEVEL.THE FLIGHT WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. TROUBLESHOOTING IS ONGOING.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305012)                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA22CE   E00059EN             
             20080521     NE  2008       5          21         CA080305013      220080219G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   530   PW530A           NE                                              FLAMED OUT      W      D   RETURN TO BLOCK                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE DEICING THE AC AND PERFORMING SYSTEMS CHECKS, THE ENGINE FLAMED OUT WHEN BROUGHT TO IDLE POWER. THE ENGINE FLAMED OUT (2) ADDITIONAL TIMES UNDER SIMILAR CIRCUMSTANCES DURING TROUBLESHOOTING. ATTENTION IS FOCUSING ON THE FUEL CONTROL AND AIRFRAME RIGGING.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080305013)                                                                                                                                                                                                                                                                                                                                                            1L72 4F4  F  A22CE   E00053EN             
200805141    200805141    NE  2008       5          14         CA080305016      220080301G7200                ENGINE          PWC         PW545B      CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                                              POWER LOSS      W      E   ENGINE SHUTDOWN                                                                                 RFJPARTIAL RPM/PWR LOSS      FLT CONT AFFECTED         WARNING INDICATION        DEDESCENT        1                      CA                                                                      (CAN) DESCENDING THROUGH FL370, THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND ENGINE N2 SPEED REDUCED TO 41 PERCENT ASSOCIATED WITH VIBRATION. THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUT AND THE CREW ELECTED TO SHUTDOWN THE ENGINE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305016)                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00059EN             
             20081104     WP  2008       11         4          CA080305017      120080220G6710369A7304        BRACKET                                 HUGHES369   369A        4470503WP  ALLSN 250C  250C20B     03013GL                              ROTOR CONTROL   UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON REMOVAL OF DUAL CONTROLS, A GENERAL INSPECTION OF THE UNDERSEAT AREA REVEALED A CRACK ON THE BEARING CAP OF THE BRACKET ASSEMBLY WHICH IS USED TRANSFERING CONTROL INPUTS FROM CABIN BACK TO THE ROTORS. THE PART WAS REPLACED WITH NO INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H3WE    E4CE                 
             20080521     EU  2008       5          21         CA080306002      120080304G2910HTE400005       VALVE                                   BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  HYD SYSTEM      FAILED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) THE RT NON RETURN VALVE ASSEMBLY DOWNSTREAM OF THE RT HYDRAULIC PUMP FAILED. NON RETURN VALVE ASSEMBLY IS A UNIT THAT IS SWAGED TOGETHER. THE SWAGE LET GO, ALLOWING HYDRAULIC FLUID TO VENT OVERBOARD. THIS VALVE IS INSTALLED TO PREVENT PRESSURE FROM EITHER ENGINE DRIVEN PUMP GOING TO THE OPPOSITE PUMP IN THE EVENT OF A PUMP FAILURE OR ENGINE SHUTDOWN. TIME AND CYCLES ON PART ARE UNKNOWN BUT IT IS VERY LIKELY ORIGINAL EQUIPMENT. (TC NR 20080306002)                                                                                                                                                                                                                                                                        2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
             20081104         2008       11         4          CA080313002      420080312G3197                CONNECTOR                               SNIAS 350   AS350BA     8680817EU                                                               INSTRUMENT LIGHTBURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) DURING THE FLIGHT THE PILOT SELECTED THE INSTRUMENT LIGHTS ON. FIVE MIN LATER THE LIGHTS BEGAN TO CYCLE ON AND OFF. THE PILOT TOUCHED THE CONNECTOR AND ELECTRICAL FLAME CAME FROM THE CONNECTOR. THERE WAS A BURNING ODOR BUT NO VISIBLE SMOKE. THE PILOT SHUT THE LIGHTS DOWN AND CONTINUED THE FLIGHT. THE PROBLEM COULD NOT BE REPRODUCED ON THE GROUND, BUT THE UNIT IS UNSERVICABLE. (TC NR 20080313002)                                                                                                                                                                                                                                                                                                                            1G71 3U    NCH9EU                         
             20080602     EU  2008       6          2          CA080313004      220080311G7200                ENGINE                                  BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  NR 2            MALFUNCTIONED   W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      DURING APPROACH IN ICING CONDITIONS AND HEAVY PRECIPITATION, WHEN THE PILOT THROTTLED BACK, ENGINE NR 2 FLAMED OUT AND AUTO FEATHERED. THE PILOT DID NOT ATTEMPT TO RE-LIGHT AND LANDED WITH ONE ENGINE OPERATING. MAINTENANCE CHECKED THE OIL SCREEN, FUEL SCREEN AND FUEL TANK SUMPS. NO CONTAMINATION WAS FOUND. MAINTENANCE CONDUCTED HIGH AND LOW POWER ENGINE RUNS AS WELL AS AUTO-FEATHER CHECKS AND FOUND NO PROBLEM WITH THE ENGINE.  ROLLS-ROYCE NOTICE TO OPERATES NO. 1142 IS DIRECTED TO THE FLIGHT CREWS TO "SWITCH ON THE ENGINE IGNITION SWITCHES WHEN MODERATE OR SEVERE ICING IS ENCOUNTERED". THE PILOT DID NOT HAVE THE ENGINE IGNITION SWITCHES SELECTED TO "ON" DURING THIS EVENT.  THE PILOTS HAVE BEEN REMINDED OF THIS 2L72 3T4  T  A24EU   A196    6  CP899     
             20080521     EA  2008       5          21         CA080314001      120080206G5610NP1393225       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7038                                                           (CAN) FLT NR 3874  DISCREPANCY: (CAPT`S SIDE WINDOW FWD UPPER CORNER, MIDDLE PANE CRACKED DURING APPROACH)  REQUESTED THE PN/SN, TSN/CSN INFORMATION. UPDATE 2/6: REPLACED THE WINDOW. (TC NR 20080314001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA21EA                        
200805141    200805141    NE  2008       5          14         CA080314002      220080313G7200CF343B1         ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              NR 2            FIRE            W      AFB UNSCHED LANDING         ACTIVATE FIRE EXT.      EMER. DESCENT                                   BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AC LANDED, AFTER THE PILOT HAD DECLARED AN EMERGENCY FURTHER TO A FIRE ON ENG NR 2. THE AC FLEW IN CRUISE AT FL 220, WHEN THE PILOT GOT A FIRE ALARM ON ENG 2. THE TEMP (ITT) OF ENGINE SHOWED CLEARLY THAT AN ACTUAL FIRE HAD BROKEN OUT. PILOT DECLARED AN EMERGENCY, APPLIED THE FIRE DRILL, ACTIONED THE FIRE PROTECTION SYS (BOTH BOTTLES) AND WENT IN AN EMERGENCY DESCEND TOWARDS AIRPORT. DURING DESCEND, THE TEMP OF ENG NR 2 STAYED AT A HIGHER LEVEL (760 DEGREE C) THAN ENG NR 1 (600 DEGREE C). THE AC LANDED SAFELY, ATC PERSONNEL WITNESSED A SLIGHT BLACK SMOKE COMING FROM THE ENGINE. THE FIRE BRIGADE WENT INTO ACTION AND USED FIRE EXTINGUISHING AGENT, BUT DID NOT REPORT HAVING ACTUALLY SEEN FLAMES. (TC NR 2008032L72 4F4  FRTA21EA   E15NE                
             20080521     NM  2008       5          21         CA080314003      120080307G532019093649001     BRACKET                                 EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              FUSELAGE        CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3018 3018                                                      (CAN) EXCERPT FROM MESSAGE RECEIVED FROM MAINT ON THAT FINDING:  NOTE THE CRACK RUNNING FROM THE HIGHLOCK. FOUND WHILE T/S ON SNAG L4438921. THIS IS THE MAIN SUPPORT FOR THE LOWER END OF THE CONTROL QUADRANT IN THE LT WHEEL WELL THE FLANGE IS SUPPORTING THE BULHEAD THAT CONCERNS FLEXING AND CONTACTING THE LOWER FWD SECTION OF THE CONTROL QUADRANT.  MFG INFORMED OF THE FINDING, REPAIR SUGGESTED TO FLEET ENGINEERING.  MORE INFO TO BE PROVIDED. (TC NR 20080314003)                                                                                                                                                                                                                                                               2L72 4F4  FRTA57NM   E00070EN             
             20081104     SW  2008       11         4          CA080314004      120080306G2510STCSH0631       INERTIA REEL    BELL                    BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              COCKPIT SEAT    BINDING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CO-PILOT SEAT SHOULDER HARNESS INERTIAL REEL CABLE FOUND BINDING AGAINST VERTICAL REFERENCE SEAT KIT - PLATE ASSY P/N AAL-292-031-001. FOUND TO BE COMMON PROBLEM WHEN CHECKED ON OTHER ACFT. WILL CONTACT MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 4U4  U  H4SW    E22EA                
             20080521     EU  2008       5          21         CA080314005      120080311G3244542K694         TIRE                                    AIRBUSA330  A330*              EU  RROYCERB211 RB211*      54555NE                              MLG             FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN)THE AC BLEW THE NR (4) MAIN TIRE ON DEPARTURE. THE FLIGHT CREW ELECTEDTO DIVERT, AND ULTIMATELY LANDED APPROXIMATELY 15000 KGS OVER THE MAXIMUM STRUCTURAL LANDING WEIGHT OF 185000KGS. DURING TAXI, THE NR (3),  RT FWD IB MAIN TIRE DEFLATED AND THE AC WAS SUBSEQUENTLY SERVICED BY MAINT, BEFORE BEING ABLE TO POSITION TO THE GATE. INVESTIGATION IS ONGOING. SDR WILL BE UPDATED ACCORDINGLY. (TC NR 20080314005)                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA46NM   A12EU                
             20080521     NM  2008       5          21         CA080314006      120080312G215078279018        ACM                                     DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE                  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3390523037                                                     (CAN) WHILE CARRYING OUT WORK CARD TO REMOVE COMPONENT IT WAS DISCOVERED THERE WAS A 6 INCH CRACK ON THE INNER SIDE OF THE CHAMBER. (TC NR 20080314006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080603     GL  2008       6          3          CA080314007      220080312G7261                ENGINE                                  EMB   135   EMB135ER    3260203SO  ALLSN AE300 AE3007A          GL                                              LEAKING         W      A   UNSCHED LANDING                                                                                 KMYFLUID LOSS                OVER TEMP                 ENGINE STOPPAGE           CRCRUISE         1                      CA                                                                      OIL IMPENDING BYPASS INDICATION ILLUMINATED ALONG WITH OIL TEMPERATURE RISING TO 141 DEGREES.  THE PILOT COMMANDED THE SHUT DOWN OF THE ENGINE DUE TO OIL TEMPERATURE AND QUANTITY INDICATING THREE QUARTS.  AIRCRAFT RETURNED TO CMH WITHOUT INCIDENT.  MAGNETIC INDICATING PLUGS WERE FOUND CLEAN.  A SMALL PUDDLE OF OIL IN FAN SECTION AND A LOT OF OIL IN THE EXHAUST WAS REPORTED.  THE OIL FILTER WAS FILLED WITH CARBON DEBRIS.  ENGINE HAS ACCUMULATED 0.8 HOURS SINCE LAST REPAIR AND THIS WAS THE 1ST FLIGHT SINCE REPAIRS.  ENGINE UNDER INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED AFTER ENGINE TEARDOWN. (TC NR 20080314007)                                                                                                 2L72 4F4  FRTT00011ATTE6CH                
             20080603     NE  2008       6          3          CA080314008      220080313G7200                ENGINE                                  AIRBUSA319  A319114     3930350NM  GE    CFM56 CFM565A     13802NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CLCLIMB          1                      CA       3080414183                                                     DURING CLIMB A LOUD BANG AND VIBRATION WAS FELT, FOLLOWED BY ENG 2 FAIL ON ECAM AT 8300 FT AND CLIMBING.  LANDED SAFELY WITH NO ISSUE WITH LANDING.  AFTER LANDING DEBRIS WAS FOUND IN ENGINE EXHAUST AND AFT CENTER BODY WAS DAMAGED.  INVESTIGATION INTO CAUSE OF ENGINE FAILURE IS ON GOING AND SDR WILL UPDATED ACCORDINGLY.  ENGINE HAS BEEN CHANGED. (TC NR 20080314008)                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA28NM   E29NE                
             20080603     GL  2008       6          3          CA080314009      220080310G7230                BEARING                                 EMB   145   EMB145LR    3260212SO  ALLSN AE300 AE3007A          GL                              NR 4            FAILED          W      K   NONE                                                                                            BM SMOKE/FUMES/ODORS/SPARKS  OVER TEMP                                           ININSP/MAINT     1                      CA                                                                      ENGINE REMOVED FOR ITT EXCEEDANCE, AUTO IFSD, SMOKE IN COCKPIT/CABIN, OIL DEBRIS ON ALL CHIP DETECTORS.  TEARDOWN OF ENGINE REVEAL NR 4 BEARING FAILURE AND ALSO NR 3 BEARING FAILURE.  EXCESSIVE DAMAGE IN COMPRESSOR AREA DUE TO BOTH SUPPORTING BEARING FAILURE.  FAILED COMPONENTS WILL BE SENT TO THE OEM FOR INVESTIGATION. (TC NR 20080314009)                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  FRTT00011ATTE6CH                
             20081219     CE  2008       12         19         CA080314010      120080306G3245G195X6758       TUBE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  TIRE            FLAT            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) TIRE WENT FLAT SITTING IN HANGAR.  CRACK FOUND IN TUBE AT BASE OF VALVE STEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20080603     CE  2008       6          3          CA080314011      120080306G8011200SGL119Q2     BRUSHES                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  STARTER         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1181                                                           SLOW SPOOLING OVER ENGINE, ENGINE STARTER BRUSHES WORN OUT (TC NR 20080314011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081104     NE  2008       11         4          CA080314012      120080310G792184300207        THERMOSTAT                              SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              OIL COOLER      STUCK           W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMPERATURE INCREASED TO RED LINE. (TC NR 20080314012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G72 3U3  U  H1NE    E1GL                 
             20080521     SO  2008       5          21         CA080314013      220080307G8500TSIO520EB       ENGINE                                  CESSNA401   401         207590CCE  CONT  O520  TSIO520E    17040SO  MCAULY3AF32C3AF32C*     GL                  MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         APAPPROACH       1                      CA            714                                                       (CAN) ON FINAL APPROACH INTO AIRPORT THE RT ENGINE MANIFOLD PRESSURE STARTED CHANGING. THE PILOT THEN NOTICED THAT THE RT OIL PRESSURE HAD DROPPED TO THE RED LINE. THE RT PROP WAS FEATHERED AND THE ENGINE WAS SHUTDOWN. SMALL BITS OF METAL WERE FOUND UNDER THE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS REMOVED AND SENT FOR WARRANTY. (TC NR 20080314013)                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20081105     SW  2008       11         5          CA080314014      120080307G3246205050400063    CROSSTUBE                               BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              MLG             BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) HELICOPTER WORKING HELI-SKIING. THE PASSENGERS WERE LOADING INTO THE HELICOPTER. ALMOST ALL THE SEATS WERE OCCUPIED WHEN A SUDDEN SETTLING WITH A METALLIC NOISE ON THE REAR OF THE MACHINE OCCURRED. IT WAS NOTED THAT THE REAR CROSS TUBE WAS CRACKED ALL THE WAY AROUND OR BROKEN UNDERNEATH THE RIGHT HAND CROSS TUBE SADDLE. (ABOUT 1" INSIDE THE SADDLE AREA)                                                                                                                                                                                                                                                                                                                                                                       1G71 4U4  U  H4SW    E22EA                
             20081104     WP  2008       11         4          CA080314015      120080313G6320369D2512311     GEAR                                    HUGHES369   369         4470702WP  ALLSN 250C  250C20      03013GL                              M/R TRANSMISSIONBROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       616                                                            (CAN) ACFT WAS BROUGHT IN WITH XMSN NOISE AND CHIP LIGHT. XMSN WAS OPENED AND A PIECE OF GEAR TOOTH 7/8 OF AN INCH LONG WAS FOUND MISSING. THIS IS THE SECOND OCCURENCE OF THIS TYPE THAT WE HAVE ENCOUNTERED. THE LAST SDR WAS APRIL OF 2005. (TC NR 20080314015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
200805141    200805141    EU  2008       5          14         CA080314016      120080309G2751A275704050400   SWITCH                                  AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              KRUEGER FLAP    CONTAMINATED    W      D   RETURN TO BLOCK                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, ECAM WARNING "FLAP KRUEGER NOT RETRACTED LIGHT" CAME ON. FLIGHT RETURNED TO THE STATION. SFCC INDICATED FAULT COMING FROM THE LT KRUEGER RETRACT SWITCH. MAINT FOUND THE SWITCH BACK SHELL CONTAMINATED WITH WATER.  CONNECTOR AND SWITCH CLEANED OUT AND SYS TESTED SERVICEABLE.  AC DEPARTED AND SAME SNAG REOCCURRED DURING CLIMB. THE AC RETURNED TO THE STATION AND WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING. DURING INSP, FOUND SLIGHT DAMAGE ON WIRE, 2 INCHES FROM CONNECTOR. WIRE PROTECTION CARRIED OUT IAW ESPM 20-53-00 AND SWITCH ASSY REPLACED. SYS TESTED SERVICEABLE. AC WAS RETURN TO SERVICE WITH NO REOCCURRENCE. (TC NR 20080314016)                                                                2L72 4F4  FRTA35EU   E23EA                
             20080521     EA  2008       5          21         CA080314017      120080306G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) FLAP FAIL MESSAGE SHORT FINAL WHEN CREW WERE SELECTING FROM FLAP 8 TO FLAP 20 POSITION, FLAPS REMAINED AT 8 DEGREES AND LANDED NORMAL. MAINT REPORTED THAT THE LIST OF FAULTS IN MDC ARE :  1- JAM 2- FECU 3- L MOTOR BRAKE  THE FAULT CODES WERE RETRIEVED FROM THE FECU AND POINT TOWARDS POWER LOSS DUE TO THE SDS LT SKEW DETECTOR FLAGGED. MAINT RESET THE SDU AND FECU. RAN THE FLAPS UP AND DOWN 2 TIMES. THEN THE SDU FLAGGED THE LT SKEW DETECTOR AGAIN. DUMMY BOX INSTALLED, SYSTEM TESTED AND IT WAS CONFIRMED THE SKEW DETECTION IS AT FAULT. MAINT HAS CONFIRMED THAT THE SDU FECU POWER 1 AND 2 LIGHTS FLAGGED, AND THE LT OB PANEL SKEW L4 AND L3 LIGHTS FLAGGED. SKEW DETECT SYS BOUND AT FAULT. SKEW DETECT SYS DEACTIVAT2L72 4F4  FRTA21EA   E15NE                
             20080521     EU  2008       5          21         CA080314018      120080307G32505325012004      BEARING                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NLG STEERING    UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8888                                                           (CAN) FORK BEARING ON NOSE LANDING GEAR STEERING FOUND TWISTED. THIS DEFECT WAS FOUND ON NOSE LANDING GEAR SHOCK ABSORBER REPAIR AND SERVICE. (TC NR 20080314018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080521     GL  2008       5          21         CA080314019      220080304G72506871505         BEARING                                 HILLERUH12  UH12E       4360122WP  ALLSN 250C  250C20      03013GL                              NR 5            FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       169                                                            (CAN) CHIP LIGHTS METAL CONTAMINATION ENGINE SHOP DETERMINED NR 5 BEARING FAILURE.  (TC NR 20080314019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  U  4H11    E4CE                 
             20080603     NE  2008       6          3          CA080314021      220080209G7200                ENGINE                                  SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                                              MAKING METAL    W      O   OTHER                                                                                           EJ VIBRATION/BUFFET          WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       4581 1456                                                      ON THE FIRST GROUND RUN OF THE DAY DURING GROUND WARM UP, A NOISE WAS EMITTED FROM THE ENGINE AND IMMEDIATLEY AFTER NOISE WAS HEARD THE ENGINE CHIP LIGHT ILLUMINATED.  PILOT SHUT ENGINE DOWN.  METAL PARTICLES WERE FOUND ON MOS CHIP PLUG AND SOME ON THE ELECTRIC CHIP PLUG.  ENGINE WAS REMOVED AND SENT TO TURBOMECA MONTREAL FOR INSPECTION AND REPAIR. WE WERE LUCKY THIS DID NOT HAPPEN IN THE AIR AS WE WOULD BE LOOKING AT A TOTAL ENGINE FAILURE. (TC NR 20080314021)                                                                                                                                                                                                                                                               1G71 3U3  U  H9EU    E00054EN             
             20080521     SO  2008       5          21         CA080314022      120080309G2400W23X1A1G40      CIRCUIT BREAKER                         PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  COCKPIT         OPEN            W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) CIRCUIT BREAKER FOUND IN OPEN CIRCUIT AND ALSO FOUND ONE FAULTY WIRE WHICH WAS REPLACED. (TC NR 20080314022)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A20SO   E14EA   5  CP33EA    
200805141    200805141    EU  2008       5          14         CA080317003      120080311G2435                COOLING FAN                 160SG140Q   UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              STARTER GEN     SEPARATED       W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       128                                                            (CAN) DURING THE ENGINE START SEQUENCE, AN UNUSUAL NOISE WAS HEARD BY THE PIC. THE NOISE WAS MOMENTARY AND OCCURRED SEVERAL SECONDS AFTER STARTER GENERATOR ENGAGEMENT AND JUST PRIOR TO ENGINE LIGHT OFF. ENGINE PARAMETERS REMAINED NORMAL SO THE START SEQUENCE WAS COMPLETED.  AFTER ENGINE STABILIZATION THE ENGINE WAS SHUTDOWN FOR INVESTIGATION AND THE FLIGHT WAS CANCELLED.  MAINT WERE ABLE TO DUPLICATE THE NOISE BY ENGAGING THE STARTER FOR SEVERAL SECONDS. THE STARTER GENERATOR WAS REMOVED TO THE BENCH AND THE COVER WAS REMOVED. IT WAS NOTED IMMEDIATELY THAT THE COOLING FAN HAD BECOME SEPARATED FROM THE ARMATURE SHAFT AND WAS ABLE TO SPIN FREELY. BY QUICKLY SPINNING THE FAN AROUND THE SHAFT, THE NOISE HEARD DURIN1G72 3U3  UNCR0001RD E34NE                
             20080521         2008       5          21         CA080317004      420080214G8300                GEAR                                    PIPER PA34  PA34200T    7103406SO  CONT  O360  TSIO360EB   17025SO  HARTZLHCC2Y BHCC2YF2    GL  ACCESSORY G/B   FAILED          W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) LOW OIL PRESSURE LIGHT CAME ON IMMEDIATELY AFTER TAKEOFF.  PWR WAS BROUGHT BACK AND AC RETURNED FOR SAFE LANDING. ENGINE WAS SHUTDOWN OFF RUNWAY, PROP FEATHERED AUTOMATICALLY. BOTH SUCTION SCREEN AS WELL AS OIL FILTER INSPECTED, NO METAL CONTAMINANTS FOUND. PROP DID NOT TURN FREELY. ALTERNATOR PULLED OFF ON THE BACK OF THE ENGINE. GEAR FOUND LYING LOOSE IN ACCESSORY CASE WITH MULTIPLE BROKEN TEETH ON OTHER GEARS. (TC NR 20080317004)                                                                                                                                                                                                                                                                                      1L72 3O3  O  A7SO    E9CE    5  CP920     
             20080521     EA  2008       5          21         CA080317005      220080304G8520                PISTON PIN                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  NR 1 CYLINDER   WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HOUR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOUND WORN ON NR 1 CYLINDER. (TC NR 20080317005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081222     EA  2008       12         22         CA080317006      220080222G8530                CYLINDER                                CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  ENGINE          WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOUND WORN ON NR 1 CYLINDER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081222     CE  2008       12         22         CA080317009      120080302G272004115261        RUDDER BAR                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       11625                                                          (CAN) PILOT NOTED LT PILOTS RUDDER PEDAL WAS NOT IN IT`S CORRECT POSITION. THE RUDDER BAR WHICH IS A WELDMENT WAS FOUND TO BE CRACKED AT THE ATTACHMENT POST FOR THE LT RUDDER PEDAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081230     CE  2008       12         30         CA080318001      120080306G7160                BRACKET                                 CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              CARB HEAT       DETACHED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING ROUTINE INSP TECH NOTICED NO CARB HEAT DROP ON IN-COMING RUN-UP. TECH DISCOVERED THAT ONE OF THE 2 CARB AIR BOX BUTTERFLY VALVE BRACKETS HAD BECOME DETACHED FROM SHAFT AND VALVE WAS NOT OPENING OR CLOSING PROPERLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E274                 
             20080603     EA  2008       6          3          CA080318002      220080226G8530                STUD                                    CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  SNSNCH72C   72CK        EA  CYLINDER        BROKEN          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA            3495                                                      DURING WALK AROUND, PILOT NOTICED ENGINE OIL COVERING LT SIDE OF FUSELAGE AND EMPENNAGE.  MAINTENANCE INSPECTED ENGINE AND FOUND ON NR 2 CYLINDER, ONE BROKEN THROUGH STUD.  OIL WAS RUNNING DOWN THROUGH STUD AND EXITING CYLINDER BASE WHERE ATTACH NUT USED TO BE.  OIL LEAK WAS NOT DISCOVERED DURING OR AFTER PREVIOUS NIGHT FLIGHT. (TC NR 20080318002)                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A19    E223    5  NP9045    
             20080521     EA  2008       5          21         CA080318008      220080317G7310252429710       SERVO                                   PIPER PA28  PA28R180    7102809SO  LYC   O360  IO360B1E    41514EA  HARTZLHCC2Y HCC2YK1     GL  FUEL SYSTEM     MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            193                                                       (CAN) CHECKED IAW EMERGENCY AWD 2008-06-51. FOUND, DID NOT APPLY BY DATE BUT WHEN VISUALLY INSPECTED FOUND SAME PROBLEM AS REPORTED IN AWD. O/H DATE WAS JANUARY 28, 2005. AWD STATED AUGUST 22, 2006. ALL SERVOS MAY NEED TO BE CHECKED. (TC NR 20080318008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  2A13    1E10    5  CP920     
             20080602     WP  2008       6          2          CA080319003      220080311G731331038294        NOZZLE                                                                     GARRTTTPE331TPE33111U   01514WP                              FUEL            DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1791                                                      THE A/C CAME INTO THE HANGER FOR A ROUTINE FUEL NOZZLE AND BOROSCOPE INSPECTION.  DURING THE BOROSCOPE INSPECTION OUR NIGHT MAINTENANCE FOUND SOME DISCREPANCIES IN THE ENGINE.  FURTHER INSPECTION FROM THE TURBINE SHOP IT WAS NOTED THAT THE NOZZLE SEGMENTS THAT MAKE UP THE NR 1 STATOR ASSEMBLY HAD SOME DAMAGE TO THEM.  THE NOZZLE SEGMENTS WERE OVERHAULED FROM SOUTHWEST TURBINE.  THE ENGINE WAS REPLACED AND FORWARDED TO THE ENGINE SHOP FOR FURTHER REPAIR. (TC NR 20080319003)                                                                                                                                                                                                                                                          4  T          E4WE                 
             20080603     NM  2008       6          3          CA080319004      120080307G531019093649001     SUPPORT                                 EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              MLG WW          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3018 3018                                                      ON AIRCRAFT A CRACK WAS FOUND TO MLG WELL BULKHEAD SUPPORT.  THE CRACK STARTS AROUND ONE OF THE ATTACHMENT HOLES AND GOES UP TO THE MIDDLE OF DISTANCE BETWEEN THE TWO ATTACHMENT HOLES.  THE BULKHEAD IS ALSO FLEXING AND CONTACTING THE LOWER SECTOR OF THE AILERON CONTROL QUADRANT.  PROBLEM ALSO FOUND ON THE FOLLOWING A/C FIN NUMBER: 307, 309, 311, 313, 315, 317, 318, 319, 320, 322, 323, 324, 326, 332 (TC NR 20080319004)                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA57NM   E00070EN             
             20080602         2008       6          2          CA080319005      120080319G8011EBB131A         DRIVE SYSTEM                                                                                                                            STARTER         SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            97                                                        STARTER RECEIVED DUE TO DRIVE ASSEMBLY FAILURE.  ENGINE COULD NOT BE STARTED BECAUSE DRIVE WOULD NOT ENGAGE.  WHEN INSPECTED THE DRIVE COULD NOT BE TURNED OUT OR SPUN BY HAND TO EXTEND THE GEAR SECTION OF THE DRIVE.  STARTER WAS RETURNED TO KELLY AEROSPACE FOR WARRANTY REPLACEMENT. (TC NR 20080319005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
             20080602     SW  2008       6          2          CA080319007      120080306G3260EN516           SWITCH                                  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE331*     01514WP  MCAULY4HFR344HFR34C652  NE  LT MLG          INTERMITTENT    W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      ON APPROACH, THE CREW NOTICED THAT THE LT GEAR HAD NO "GREEN" SAFE LIGHT.  FLY BY WAS CARRIED OUT CONFIRMED GEAR DOWN.  AIRCRAFT LANDED WITHOUT INCIDENT.  SWITCH WAS FOUND STICKY.  SWITCH REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20080319007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T3  TRTA8SW    E2WE    6  C3PNE     
             20080602     NE  2008       6          2          CA080319008      220080306G7200                ENGINE                                  PAC   CRESCOCRESCO             CE  PWA   PT6   PT6A34AG    52053NE                                              POWER LOSS      W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      DURING TAKEOFF ROLL, A NOISE WAS HEARD ACCOMPANIED BY LOSS OF ENGINE POWER.  THE TAKEOFF WAS ABORTED.  INITIAL INSPECTION REVEALED FRAGMENTS SIMILAR TO COMPRESSOR BLADE MATERIAL DISTRIBUTED THROUGHOUT THE INLET.  TEARS IN THE INLET SCREEN WERE NOTED.  THE ENGINE HAS BEEN REMOVED AND WILL BE INVESTIGATE ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                    1L71 4T4  TNTEXPA1L71E4EA                 
             20080602     EA  2008       6          2          CA080320002      120080318G2797MS27473T20B4    CONNECTOR                               CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              FLUTTER DAMPER  DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       19157                                                          TASK NR 27-34-05-710-801 WAS BEING PERFORMED ON THE ELEVATOR FLUTTER DAMPERS.  IT FAILED THIS TASK FOR LOW FLUID LEVEL TRANSMITTER SWITCHES.  THIS TASK WAS CALLED UP DURING THE AIRCRAFT`S PLANNED HEAVY INSPECTION. T HERE WERE NO REPORTED FAILURES WHILE THE AIRCRAFT WAS IN-SERVICE PRIOR TO THIS HEAVY MAINTENANCE VISIT.  DURING THE COURSE OF TROUBLE SHOOTING, THE AME FOUND THE CONNECTORS P300 AND J300 CORRODED TO THE EXTENT THAT THE PINS M AND N BROKE OFF WHEN THEY WERE DISCONNECTED.  SEVERAL OTHER PINS WERE ALSO FOUND DISCOLORED.  CONNECTOR P/N MS27497T20B41S, BACKSHELL P/N HEX41-AB90-21A9-1, CONNECTOR P/N MS27473T20B41P AND BACKSHELL P/N HEX41-AB00-21A9-1 WERE REPLACED AND SYSTEM FUNCTION CHECKED "SERVICEABLE".2L72 4F4  FRTA21EA   E15NE                
             20080602     SW  2008       6          2          CA080320003      120080312G52302724050083      FRAME                                   SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              CARGO DOOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       43129                                                          DURING AN AGING AIRCRAFT INSPECTION A CRACK WAS DETECTED VISUALLY EXTENDING FROM THE LOWER AFT LATCH (POSITION 8).  WHEN THE DOOR WAS REMOVED FOR REPAIR FURTHER CRACKS WERE DISCOVERED TO THE ATTACHING STRUCTURE FOR BOTH LOWER LATCHES (POSITIONS 7 AND 8).  THIS FAILURE IS BELIEVED TO BE THE RESULT OF FATIGUE, AND IF REMAINED UNDETECTED COULD EVENTUALLY RESULT IN FAILURE OF THE CARGO DOOR.  IT SHOULD ALSO BE NOTED THAT AD 98-06-25 REQUIRES AN INSPECTION OF THE LATCHING SYSTEM. (TC NR 20080320003)                                                                                                                                                                                                                             2L72 4T4  TRTA8SW    E4WE                 
             20080602     CE  2008       6          2          CA080320004      120080314G5320365533          GASKET                                  CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              SERVO PLUG      LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1861                                                           SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF JULY 14, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE.  HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320004)                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10                 
             20080602     EA  2008       6          2          CA080320005      220080314G7321365533          GASKET          PRECISIONWND            CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              FCU             LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1745                                                           AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.ENGINE REMANUFACTURE DATE OF SEPT. 8, 2005 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. RIGHT MAGNETO P-LEAD WIRE BROKEN. (TC NR 20080320005)                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    1E10                 
             20080602     EA  2008       6          2          CA080320006      220080314G7321365533          GASKET          PRECISIONWND            CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              FCU             LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1367                                                           SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF AUG 18, 2005 AND THE FUEL SERVO WAS REPAIRED JULY 28, 2006 AND BOTH DO NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320006)                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
             20080602     EA  2008       6          2          CA080320007      220080314G7321365533          GASKET          PRECISIONWND            CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA  MCAULY3D36C B3D36C431   GL  FCU             LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       293                                                            AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF SEPT 8, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE.  HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320007)                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A13    1E4     5  C         
             20080602     CE  2008       6          2          CA080320010      120080307G2750S16612          SWITCH                                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              TE FLAPS        BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      INTERNAL RETURN SPRING OF SWITCH BROKEN.  TOGGLE NOT RETURNING TO NEUTRAL POSITION.  SWITCH REPLACED WITH NEW. (TC NR 20080320010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E274                 
             20081105     EU  2008       11         5          CA080320011      120080320G6230350A37118322    LOCK                                    SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  CRACKED MAIN ROTOR MAST LOCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  UNCH9EU    E19EU                
             20081105     WP  2008       11         5          CA080320012      120080312G6310C1883           CROSS TIE                               ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              SPRAG CLUTCH    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       911                                                            (CAN) DURING A IN-HOUSE 1000 HR CLUTCH INSPECTION THE SPRAG CLUTCH CAGE CROSSBAR WAS FOUND CRACKED. NEW PARTS WERE INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
             20080602     CE  2008       6          2          CA080320013      120080319G3245891250          TUBE                                    CESSNA208   208         2073702CE  PWA   PT6   PT6A114A    52043NE                              TIRE            FAILED          W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       626                                                            ON TAXI PILOT FELT AIRCRAFT PULLING TO ONE SIDE AND DISCOVERED FLAT TIRE.  TIRE WAS CHANGED AND FLOWN BACK TO BASE.  TIRE ASSY WAS DISASSEMBLED AND TUBE WAS FOUND BLOWN WITH ABOUT A FOUR INCH SPLIT IN IT.  THE TUBE WAS ALSO FUSED TO THE INSIDE OF THE TIRE IN THE AREA OF THE BALANCE PATCH.  THIS WAS THE ORIGINAL TIRE INSTALLED AT CESSNA FACTORY WHEN AIRCRAFT WAS DELIVERED.  I AM REPORTING THIS DUE TO AN ABNORMAL NUMBER OF TUBES THAT WE HAVE HAD LET GO IN THE LAST MONTH.  TALKING TO OTHER OPERATORS HAS INDICATED THAT OTHERS ARE HAVING THE SAME PROBLEM.  I HAVE BEEN TOLD BY A TIRE COMPANY THAT THE BUTYL RUBBER TUBES ARE NOT WORKING WELL IN OUR COLDER CLIMATE. (TC NR 20080320013)                                    1H71 3T3  TNTA37CE   E4EA                 
             20080521         2008       5          21         CA080324001      120080324G3245600X6           TUBE                                                                                                                                    TIRE            DEFECTIVE       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BELIEVE TO HAVE ENCOUNTERED A DEFECTIVE TIRE TUBE BATCH. THE TUBES IN QUESTION ARE MFG 6.00 X 6, SOLD UNDER BATCH NR 032358. WE HAVE HAD 5 INSTANCES OF TIRE TUBE FAILURE OUT OF 6, WITH THE CONCERNED TUBE BATCH. (TC NR 20080324001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
             20080521     CE  2008       5          21         CA080325006      120080312G531212127071        BULKHEAD                                CESSNA206   U206E       2073350CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y HCC3YF1     GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BULKHEAD CRACK 1.25 IN LONG AT RT SIDE FROM LIGHTNING HOLE.  NEAR STAB ATTACH POINT. (TC NR 20080325006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A4CE    E5CE    5  CP25EA    
             20080521     NM  2008       5          21         CA080325008      120080325G5315654681163       FLOORBEAM                               BOEING737   737490      1384715NM                                                               BS 986 RBL43    CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOORBEAM FOUND CORRODED DURING VISUAL INSP AND REPAIRED WITH REPAIR PART IAW EA AND SRM. (TC NR 20080325008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080325009      120080325G5315654681179       FLOORBEAM                               BOEING737   737490      1384715NM                                                               BS 986 RBL 35-40CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOORBEAM CAP AT BS 986.5, RBL 35 AND 40 FOUND CORRODED DURING VISUAL INSPECTION AND REPAIRED WITH REPAIR PART IAW CUSTOMER EA AND SRM. (TC NR 20080325009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
             20080521     NM  2008       5          21         CA080325010      120080325G5315654681179       FLOORBEAM                               BOEING737   737490      1384715NM                                                               BS 986 RBL 27   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOORBEAM AT BS 98605, RBL 27, WL 207.5 CORRODED UNDERSIDE UNDER CLIP NUT. REPAIRED WITH REPAIR PART IAW CUSTOMER EA AND SRM. (TC NR 20080325010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA16WE                        
             20080521         2008       5          21         CA080325011      120080325G2410ALV9510R        ROTOR                                                                                                                                   ALTERNATOR      MISMANUFACTURED W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN INSTALLING DRIVE HUB, THE CUSTOMER NOTICED COTTER PIN COULD NOT BE INSERTED WITH NUT TORQUED AND NUT ALIGNED WITH COTTER PIN HOLE LOCATION. WHEN INSPECTED IN-HOUSE THE COTTER PIN HOLES WERE FOUND DRILLED TOO FAR DOWN THE SHAFT. ALSO THE O-RING BETWEEN THE SPACER AND WASHER UNDER THE DRIVE HUB WAS FOUND TO BE TOO BIG TO ALLOW THE WASHER TO SEAT AGAINST THE SPACER.  HAS INFORMED US THAT THEY HAD SOME ROTORS LEAVE THEIR FACILITY WITH THIS ISSUE AND THE ALTERNATOR WAS RETURNED TO THEM FOR WARRANTY PURPOSES. (TC NR 20080325011)                                                                                                                                                                                                                               
             20080521     GL  2008       5          21         CA080325013      220080320G725023038136        SHAFT                                                                      ALLSN 250C  250C47B          GL                              TURBINE         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3823                                                           (CAN) ENGINE NOISE WAS NOTED AT GROUND IDLE. THE NOISE WAS REDUCED WHEN IN HOVER BUT CONSISTENTLY APPEARED DURING SPOOL DOWN TO GROUND IDLE. THE ENGINE WAS REMOVED AND RETURNED TO THE OVERHAULER FOR REPAIR. THE NOISE WAS CONFIRMED DURING AN ENGINE TEST WITH VIBRATION MEASUREMENTS. ENGINE DISMANTLE AND INSP ON THE 26TH OF FEBRUARY 2008 REVEALED A CRACKED POWER TURBINE SHAFT. THE CRACK LOOSENED THE FIT AT THE TURBINE 4TH WHEEL CURVIC COUPLING AND CAUSED FRETTING AND THE LOSS OF A COUPLING TOOTH.   PT OUTER SHAFT P/N 23038136, S/N KU95766 AND 4TH TURBINE WHEEL RETURNED TO MFG FOR INVESTIGATION. (TC NR 20080325013)                                                                                                             3  U          E1GL                 
             20081105     WP  2008       11         5          CA080325015      120080304G5100                UNKNOWN                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              UNKNOWN         W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) UPON TAKE OFF AND AT A SPEED OF 30 KTS AND 10-15FT ALTITUDE (AGL), ACFT YAWED RT WITH ENGINE BACKFIRE AND DECELERATION AND IMMEDIATE LOW ROTOR HORN. THE PILOT DROPPED THE COLLECTIVE & CONDUCTED EMERGENCY RUN-ON LANDING IN A FIELD SOUTH OF THE HANGAR. UPON SAFE LANDING, THE ENGINE WAS STILL RUNNING AND ACCELERATING AND ROTOR RPM WAS AT 90% AND RISING. AFTER MATCHING THE ENGINE AND ROTOR RPM NEEDLES, THE ACFT WAS LIFTED IN A HOVER AND HOVER TAXIED BACK TO THE HANGAR.  NO MECHANICAL PROBLEMS WERE FOUND. THE ACFT WAS GROUND RUN AND HOVERED FOR 30 MINS AT VARIOUS POWER SETTINGS WITH NO FURTHER INCIDENT. AT THE TIME OF THIS INCIDENT, THIS ACFT HAD THE DART COLD WEATHER BAFFLES INSTALLED.  WE HAVE IMPLEMENTED A 1G71 3O3  O  H11NM   1E4                  
             20081105     SW  2008       11         5          CA080326001      120080325G8097                WIRE                                    BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              STARTER         CHAFED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START.  IT WAS FOUND THAT THERE WERE 2 WIRES LABELED K2D20 AND K3C20 CHAFFED INSIDE THE CO-PILOTS COLLECTIVE. K3C20 HAD BEEN SOLDER SPLICED AND CHAFED AT THE SPLICE AND K2D20 WAS CHAFFED THROUGH THE WIRE.                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H1SW    E17EA                
             20080521     SW  2008       5          21         CA080326002      120080324G78103101582         EXHAUST DUCT                            SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN THE ENG WAS UNDERGOING A PHASE 6 INSP, A CRACK APPROX 3 INCH LONG WAS DISCOVERED IN THE ENGINE EXHAUST DUCT NEAR THE EGT PROBE BOSSES.  IT APPEARED TO BE ON A PREVIOUS WELD.  REMOVED AND REPLACED THE DUCT. (TC NR 20080326002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
             20080521     CE  2008       5          21         CA080326003      120080324G2161                COUPLING                                CESSNA650   650         2076802CE  GARRTTTPE731TFE7313C         WP                              TEMP CONTROL    MISINSTALLED    W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) CREW WROTE UP, CABIN PAC STUCK ON FULL COLD. TROUBLESHOOTING CARRIED OUT AND FOUND THAT THE COUPLING FOR CABIN TEMP CONTROL HAD DISCONNECTED FROM THE ENVIROMENTAL CONTROL UNIT. BOTH CLAMPS AND THE COUPLING WERE INTACT HOWEVER THE COUPLING HAD BEEN INSTALLED INCORRECTLY. COUPLING WAS REINSTALLED AND LEAK CHECKED SERVICEABLE. (TC NR 20080326003)                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  F  A9NM    E6WE                 
             20081105     WP  2008       11         5          CA080326004      120080304G2435                ARMATURE                                ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER GEN     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            543                                                       (CAN) HOLES MELTED THROUGH ARMATURE CASE IN STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081105     WP  2008       11         5          CA080327005      120080317G2435                GEAR                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER GEN     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       27                                                             (CAN) STARTER AND RING GEAR TEETH FOUND DAMAGED DURING A DI                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081105     WP  2008       11         5          CA080327006      120080304G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       203                                                            (CAN) STARTER INTERMITTENT                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
             20081105     WP  2008       11         5          CA080327007      120080307G6520C0211           GEARBOX                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              TAIL ROTOR      LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            4                                                         (CAN) TAILROTOR GEARBOX FOUND LEAKING FROM THE INPUT SEAL DURING DI                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20080521     NE  2008       5          21         CA080328001      220080320G7250310703301       BEARING RACE                                                               PWA   PW120 PW123            NE                              NR 15           MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            11000                                                     (CAN) EIR PW100 2008-025, METAL CONTAMINATION OF THE RGB OIL SYS. (TC NR 20080328001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  4  T          E20NE                
             20080603     NE  2008       6          3          CA080328002      220080309G8530399353          CYLINDER HEAD                           DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              NR 2            SEPARATED       W      A   UNSCHED LANDING                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA            5                                                         HEAD SEPERATED FROM NR 2 CYLINDER AFTER 4.9 HRS AIRTIME.  CYLINDER HEAD SEPARATION OCCURRED DURING CRUISE FLIGHT.  UNEVENTFUL LANDING CARRIED OUT.  REPLACEMENT CYLINDER HEAD INSTALLED AND AIRCRAFT COMPLETED ITS MISSION. (TC NR 20080328002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1                  
             20080603     CE  2008       6          3          CA080328003      120080319G551412326231        BRACKET                                 CESSNA210   210J        2073439CE  CONT  O520  IO520J      17032SO                              HORIZONTAL STAB CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3218                                                           DURING THE ANNUAL INSPECTION REINFORCEMENT BRACKET (P/N 12 32623-1) WAS FOUND TO HAVE A CRACK RUNNING FROM THE BOTTOM BOLT HOLE TO THE EDGE OF THE BRACKET.  THE BRACKET IS ATTACHED TO THE REAR SPAR OF THE LT HORIZ STABILIZER.  AFFECTED PART REPLACED. (TC NR 20080328003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  3A21    E5CE                 
             20080603     CE  2008       6          3          CA080328004      120080319G531212120031        DOUBLER                                 CESSNA210   210J        2073439CE  CONT  O520  IO520J      17032SO                              BULKHEAD        CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3218                                                           DURING THE ANNUAL INSPECTION A CRACK WAS DETECTED RUNNING FROM THE ANCHOR NUT RIVET HOLE TO THE EDGE OF THE DOUBLER PLATE, THIS BRACKET IS ATTACHED TO THE REAR FRAME AT STN 209, P/N 12120402-3.  AFFECTED PART REPLACED.  (TC NR 20080328004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  O  3A21    E5CE                 
             20080603         2008       6          3          CA080328005      220080328G741410357586        DISTRIBUTOR GEAR                                                                                                                        MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2000                                                           MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL.  WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH.  THIS CONDITION HAS BEEN NOTICED IN MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE.  THE WASHER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED.  THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`.  THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328005)                                                             
             20080603         2008       6          3          CA080328006      220080328G741410357586        DISTRIBUTOR GEAR                                                                                                                        MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2000                                                           MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL.  WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH.  THIS CONDITION HAS BEEN NOTICED ON MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE.  THE WASHER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED.  THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`.  THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328006)                                                             
             20080603     CE  2008       6          3          CA080328007      120080327G5280150450018       ARM                                     CESSNA401   401B        207590ECE  CONT  O520  TSIO520EB   17040SO                              MLG DOOR        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING PILOT WALKAROUND THE RT MAIN GEAR DOOR WAS HANGING SLIGHTLY DOWN FROM RETRACTED POSITION.  MAINTENANCE TO REPLACE PART. (TC NR 20080328007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A7CE    E8CE                 
             20081105     WP  2008       11         5          CA080328008      120080308G2410                BRUSHES         KELLY                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ALTERNATOR      WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       847                                                            (CAN) DURING A POST FLIGHT DI THE ALTERNATOR BELT WAS FOUND DAMAGED. CARRIED OUT AN INSPECTION OF THE ALTERNATOR AND FOUND THE BRUSHES AND SLIP RINGS WORN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20080521     EA  2008       5          21         CA080328010      120080327G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAP         FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       2931729317                                                     (CAN) ON APPROACH WHEN MAKING INITIAL FLAP SELECTION CREW RECEIVED FLAP FAULT MESSAGE, FLAPS FAILED TO OPERATE. CREW PERFORMED FLAP (0) LANDING. CREW ADVISE OAT WAS -57 TO -59 FOR ABOUT AN HOUR AT FLIGHT LEVEL 260 PRIOR TO COMMENCING DESCENT. ON GROUND FLAPS POSITIONED TO 8 DEG AND AC FERRIED WITH FLAPS AT 8 DEG TO MAINT BASE FOR CORRECTIVE ACTION. FLAP FAULT CODE INDICATED FLAP JAM.  MAINT FOLLOWING COMPANY POLICY IS REPLACING ALL FLAP ACTUATORS, CLEANING AND LUBRICATING ALL FLAP DRIVES, NO OBVIOUS ABNORMALITIES NOTED.  (TIMES PROVIDED ARE AC TT AS NO SPECIFIC COMPONENT IDENTIFIED AS TO CAUSE) (TC NR 20080328010)                                                                                                   2L72 4F4  FRTA21EA   E15NE                
             20080521     NM  2008       5          21         CA080328011      120080328G7500                DUCT                                    BOEING727   727200      138407ENM  PWA   JT8   JT8D9A      52048NE                              BLEED AIR       LEAKING         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF OUT, NR 2 ENGINE FIRE WARNING CAME ON. THE THROTTLES WERE RETARDED AND THE WARNING EXTINGUISHED. THE AC RETURNED TO AIRPORT.  AFTER INVESTIGATION, MAINTENANCE FOUND THE DUCT FOR THE FUEL HEAT VALVE HAD COME OUT OF ITS SLEEVE CAUSING A DUCT LEAK. THE DUCT WAS REPAIRED AND LEAK CHECKED SERVICEABLE. (TC NR 20080328011)                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  FRTA3WE    E2EA                 
             20080521     EA  2008       5          21         CA080331001      120080317G571121531062212     FRAME                                   CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  FS 434.80       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2531 2531                                                      (CAN) WHILE PERFORMING AD CF-1997-07R2, NDT INSP OF FRONT AND REAR SPAR WING TO FUSELAGE FRAME ANGLES A CRACK WAS DETECTED ON THE REAR LT OB ANGLE. THE CRACK ORIGINATED AT THE TOP HI-LOK AND WAS HEADED UP ABOUT .1250 TH OF AN INCH. IT COULD NOT BE DETECTED BY THE NAKED EYE.  THE AD WAS ACTUALLY DUE AT A/F TIME 2573.4 AND WATER DROPS 9726.  WE PERFORMED IT DURING WINTER MAINT AT A/F 2530.8 AND 9521 WATER DROPS.  APPROVED REPAIRS WILL BE CARRIED OUT AND THE AC RELEASED FOR SERVICE. (TC NR 20080331001)                                                                                                                                                                                                                        2H72 4R3  RRTA14EA   ATC14   6  CP871     
             20080521     CE  2008       5          21         CA080331002      120080312G2510505530401       CABLE ASSY                              CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL  SEAT            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSTALLATION OF SERVICE KIT SK210-175 - SECONDARY SEAT STOP, IT WAS FOUND THAT THE THREADS ON THE HOUSING FOR THE ADJUSTMENT CABLE WERE CRACKED. (TC NR 20080331002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A12    E274    5  NP910     
             20080521     EA  2008       5          21         CA080331003      120080317G57112151003268      SPAR CAP                                CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2531 2531                                                      (CAN) WHILE PERFORM AD CF-1992-26R1, ULTRA SONIC INSPECTION OF THE WING REAR SPAR CAP, CRACKS WERE INDICATED ON BOTH REAR SPAR CAPS. VISUAL INSPECTIONS WERE CARRIED OUT AND CRACKS DISCOVERED ON BOTH SPAR CAPS AT WS 51.00 FS 434.80.   THIS AD WAS DUE AT A/F TIME 2651.3 AND WATER DROPS 9820. WE CARRIED IT OUT DURING WINTER MAINT AT A/F TIME 2530.8 AND WATER DROPS 9521.  THE AC MFG WAS CONTACTED AND APPROVED DRAWINGS SENT SHOWING REPAIRS. (TC NR 20080331003)                                                                                                                                                                                                                                                                     2H72 4R3  RRTA14EA   ATC14   6  CP871     
             20081105     NE  2008       11         5          CA080331004      220080319G7314C8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              AUX FUEL        NOISY           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       860                                                            (CAN) AUX FUEL PUMP HAD EXCESSIVE NOISE THE PUMP WAS REPLACED. (TC NR 20080331004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
             20080521     EA  2008       5          21         CA080331006      120080328G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       2522625226                                                     (CAN) FLAP FAILED ON APPROACH , LT FLAP INDICATING 3 DEG , RT INDICATING 4 DEG  PARTIAL FLAP LANDING CARRIED OUT.  MAINT ACTIONS : ALL 8 FLAP ACTUATORS REPLACED IAW COMPANY FLAP FAIL POLICY. (TC NR 20080331006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20080521     NM  2008       5          21         CA080331007      120080327G575317039312001     FLAP TRACK                              EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              TE FLAPS        GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3862                                                           (CAN) UPON INSP OF THE IB FLAP TRACK RAILS, GOUGES ARE EVIDENT ON THE UPPER INNER SURFACE FACE AND ON THE UPPER SIDE FACE THAT ARE OUT OF LIMITS. SEE ALSO SDR 20080318006 FOR DETAILS.   RAIL AFT, RAIL, RAIL MAIN 1, RAIL MAIN 2 OUT PN:  170-39320-001, 170-39060-01, 170-39310-001, 170-39312-001  DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL C/A  CARRIED OUT IAW MFG INSTRUCTION. REF: IC2007-17005998C, IC2008-17002015A, IC2008-17002163. (TC NR 20080331007)                                                                                                                                                                                                                              2L72 4F4  FRTA56NM   E00063EN             
             20080521     EU  2008       5          21         CA080331008      120080325G3600                B-NUT                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  CRACKED         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA       7625                                                           (CAN) FOLLOWING AN ANNUAL INSP AND A SATCOM AVIONICS UPGRADE IN THE INITIAL CLIMB PHASE OF A TEST FLIGHT , CABIN PRESSURE WAS INCREASING AT A MAXIMUM RATE. ECS WAS PROMTPLY SHUTDOWN ,CABIN DUMPED, AC LEVELED OFF AND RETURNED TO AIRPORT FOR LANDING. THE SENSE LINE FROM THE CONTROLLER TO THE AUXILLARY VOLUME TANK WAS FOUND TO HAVE A CRACKED B-NUT. UPON A SLIGHT TUG , NUT SEPARATED COMPLETLY AND LINE COULD BE PULLED COMPLETLY FROM FITTING. A NEW LINE WAS INSTALLED , SUBSEQUENT GROUND RUNS AND TEST FLIGHT PROVED SATISFACTORY. SOME OF THE WIRING NECESSARY FOR THE PROJECTS LEADING UP TO THIS INCIDENT WAS CARRIED OUT IN THIS AREA (UPPER FIREWALL).  IT IS BELIEVED THAT THE LINE MAY HAVE BEEN DISTURBED IE TYWRAPS, PERHA1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080521     EA  2008       5          21         CA080331009      220080320G8530LW12966         CYLINDER                                PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       469  469                                                       (CAN) DURING A ROUTINE INSP, THERE WAS EVIDENCE OF A CRACK LOCATED AROUND THE INTAKE HSG. THE VALVE COVER WAS REMOVED AND FURTHER VISUAL INSP REVEALED THE INTAKE VALVE WAS HITTING THE SIDE OF THE INTAKE HOUSING. WE FEEL THE CONSTANT HITTING OF THE HOUSING CAUSED A STRESS CRACK. CYLINDER WAS REPLACED. (TC NR 20080331009)                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20080521     EA  2008       5          21         CA080401001      120080327G7830W31G1120        WIRE                                    CNDAIRCL600 CL6002B19   1900309EA                                                               THRUST REVERSER BROKEN          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) ABOUT 20 MINUTES BEFORE EXPECTED ARRIVAL , RECEIVED THAT THERE WAS REV UNLOCKED MESSAGE ON EICAS IN FLIGHT, THE CREW ACCORDING TOOK QUICK CHECKLIST OPERATION, SHUTDOWN THE LT ENGINE MANUALLY, DID SINGLE ENGINE LANDING PROCEDURES.  STARTED THE TROUBLESHOOTING. CHECKED THE PDU, ETC. FINALLY, FOUND THE PROBLEM, THE WIRE OF THE W31G/1/1-20 OF THROTTLE LOCKOUT THROTTLE LOCKOUT WAS BROKEN, THE BROKEN WIRE WAS TOO SHORT,  (ALL THE WIRE SHOULD HAVE THE SAME LENGTH NORMALLY) THEY SHOULD BE RIGGED TO MAKE SURE EVERYTHING WOULD BE OK, WE CHANGED THE THROTTLE LOCKOUT MICROSWITCH REF AMM78-37-01, AND REF ESPM20-16-10C, DID THE SOLDER SLEEVE WIRE SPLICING OF THROTTLE LOCKOUT MICROSWITCH, TESTING IS NORMAL BETWEEN EVERY2L72 4F    RTA21EA                        
             20080521     NE  2008       5          21         CA080401002      220080313G7230806101          BLADE                                   BOEING727   72722C      138400FNM  PWA   JT8   JT8D7B      52053NE                              COMPRESSOR      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       186512963                                                      (CAN) WHILE PERFORMING AC DAILY INSP, NR (3) ENGINE C-1 FAN ASSY WAS FOUND TO HAVE SUBSTANTIAL DAMAGE TO (3) BLADES. THE (3) BLADES HAD SIGNIFICANT L/E DEFORMATION WITH ONE EXHIBITING VISUAL CRACKING. THE C-1 FAN WAS REMOVED FROM SERVICE AND REPLACED.  THE AC WAS INSPECTED IAW MFG ABNORMAL OCCURRENCE "BIRD STRIKE".  NO FAULTS WERE FOUND.   IT HAD BEEN OBSERVED AT THE END OF THE PRECEDING FLIGHT THAT ICE ACCUMULATION FALLING FROM THE EMPENNAGE AFTER ARRIVAL AND SHUTDOWN. IT IS SPECULATED THAT INGESTION OF ICE AT SOME STAGE OF FLIGHT MAY HAVE OCCURRED. THERE HAD BEEN NO INDICATIONS OF ENG OR AIRFRAME ABNORMALITIES DURING THE FLIGHT AND THE PROCEEDING DAILY INSP HAD NOT REVEALED THE DAMAGE. (TC NR 20080401002)    2L73 4F4  F  A3WE    E2EA                 
             20080602     EA  2008       6          2          CA080401004      220080326G7200                ENGINE                                  DHAV  DHC6  DHC6200     2802620EA  PWA   PT6   PT6A20      52043EA                              LEFT            POWER LOSS      W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA            4517                                                      ON TAKEOFF, THE LEFT ENGINE LAGGED BEHIND NOT PRODUCING MAX.  POWER, TROUBLE SHOOTING FOUND THE TEMPERATURE COMPENSATOR UNIT LEAKING P3 AIR.  THE PART WAS REPLACED AND THE PROBLEM WAS FIXED. (TC NR 20080401004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H72 3T3  TRTA9EA    E4EA                 
             20080602     NM  2008       6          2          CA080401005      120080401G3222                PIN                                     EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NLG             MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      DURING INSPECTION, FOUND NUT ON LOWER DRAG BRACE ATTACHEMENT HINGE PIN NOT SAFETIED WITH CUTTER PIN AND PRC ADRIFT SEE ATTACHEMENT.  NO EVIDENCE OF WORK PREVIOUS ACCOMPLISHED ON THE NOSE GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA56NM   E00063EN             
             20080602     NM  2008       6          2          CA080401008      120080313G32132821A000003     STRUT                                   EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              LT MLG          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2604 2604                                                      DURING THE SERVICING OF THE LEFT MAIN GEAR IT AT BEEN NOTICE THAT THE AIR KEPT COMING OUT FROM THE OIL VENT VALVE.  AS PER EMBRAER, TO FIX THE PROBLEM THE MAIN GEAR AS TO BE CHANGE AIR CANADA FLEET AS BEEN ADVISED AND SEEMS TO BE A KNOWN CONDITION (TC NR 20080401008).                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA57NM   E00070EN             
             20080602     NM  2008       6          2          CA080401010      120080401G323265C330325       ARM                                     BOEING737   737490      1384715NM                                                               MLG ACTUATOR    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       34053                                                          WHILE PERFORMING CUSTOMER T/C (AD 99-10-12) INSPECTION OF MLG ACTUATOR BEAM ARM, UT INSPECTION FINDS THAT RT MLG ACTUATOR BEAM ARM IS CRACKED CYCLES/TSN ARE AIRFRAME.  NO EVIDENCE THAT THIS PART HAS BEEN REPLACED SINCE A/C MANUFACTURE. (TC NR 20080401010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080602     EA  2008       6          2          CA080402001      120080331G3040                HEATER                                  DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE                              WINDSHIELD      SMOKE           W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE CREW OBSERVED SMOKE IN THE COCKPIT AND QUICKLY NOTICED THAT THE SMOKE WAS COMING FROM THE LT WINDSHIELD ELECTRICAL TERMINALS.  THE WINDSHIELD HEATING SYSTEM WAS TURNED OFF AND THE SMOKE STOPPED.  DECISION WAS MADE TO TURN BACK AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  LINE MAINTENANCE DISCOVERED THAT THE LT WINDSHIELD L1 TERMINAL WIRE NR 3041-48B12C WAS BURNT.  THE RT WINDSHIELD TERMINALS WERE INSPECTED AND THE L2 TERMINAL WIRE NR 3041-40A12NA WAS FOUND WITH BURNT MARKS.  BOTH WIRES WERE REPLACED AND THE SYSTEM TESTED SERVICEABLE.  THE AIRCRAFT WAS RELEASED AND A VERIFICATION FLIGHT WAS CONDUCTED. (TC NR 20080402001)                                                               2H72 4T4  TRTA13NM   E20NE                
             20080602     NE  2008       6          2          CA080402002      220080305G7532                BLEED VALVE                             CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              COMPRESSOR      MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      THE CREW EXPERIENCED ENGINE VIBRATIONS, FOLLOWED BY AN EEC MANUAL LIGHT.  ENGINE POWER INCREASED AS EXPECTED, BUT THE CREW WAS UNABLE TO FURTHER MODULATE POWER BY MOVING THE THRUST LEVER.  THE ENGINE WAS SHUT DOWN AS A RESULT AND THE FLIGHT CONTINUED TO PLANNED DESTINATION.  THE COMPRESSOR BLEED VALVE ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE COMPONENT WILL BE INVESTIGATED AND RESULTS FORWARDED FOR REVIEW. (TC NR 20080402002)                                                                                                                                                                                                                                                                             2L72 4F4  FRTA22CE   E00059EN             
             20080602     NE  2008       6          2          CA080402005      220080314G7261                TANK                                    AEROSPATR42 ATR42*      8680900EU  PWA   120   PW120            NE                              ENGINE OIL      LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        DEDESCENT        1                      CA                                                                      DURING DESCENT, OIL MIST WAS NOTED IN THE CABIN FOLLOWED BY A LOW OIL PRESSURE WARNING INDICATION.  THE ENGINE WAS SHUT DOWN BY THE CREW.  TROUBLESHOOTING REVEALED LOW OIL LEVEL IN THE TANK, AND SIGNS OF EXTERNAL OIL LEAKAGE.  THE ENGINE IS TO BE REMOVED FOR INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080402005)                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA53EU   E20NE                
             20080602     EA  2008       6          2          CA080402006      220080328G853072877           TAPPET                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              NR 1 CYLINDER   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1490                                                      WHEN REPLACING NR 1 CYLINDER THE HYDRAULIC TAPPET BODY WAS FOUND CRACKED IN TWO PLACES. (TC NR 20080402006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA                
             20080602     EA  2008       6          2          CA080402007      120080402G3150                WARNING LIGHT                           CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              ILLUMINATED     W      BE  EMER. DESCENT           ENGINE SHUTDOWN                                                         J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      AT THE TOP OF DESCENT WHEN PULLING BACK POWER, THE CREW GOT THE "LOW OIL PRES WARNING" ON THE LT ENG, SHORTLY FOLLOWED BY THE LOW OIL PRES INDICATION.  ALL OTHER PARAMETERS NORMAL.  CREW THEN ACTIONED EMERGENCY PROCEDURES AND SHUT DOWN LT ENG AND LANDED. (TC NR 20080402007)                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20080602     EA  2008       6          2          CA080402008      120080314G2435                BRUSHES                                 DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A34      52043EA                              STARTER/GEN     WORN            W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            379                                                       STARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3T4  T  A806    E4EA                 
             20080602     NE  2008       6          2          CA080402010      220080316G7320                EEC                                     AEROSPATR72 ATR72              EU  PWA   PW120 PW124B           NE                              ENGINE          MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      DURING TAKEOFF ROLL, THE ENGINE TORQUE INDICATED 75 PERCENT.  THE TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK TO THE RAMP.  THE EEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.  THE REMOVED UNIT WILL BE RETURNED FOR INVESTIGATION AND UPDATES PROVIDED TO TC. (TC NR 20080402010)                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRT        E2ONE                
             20080603     EA  2008       6          3          CA080402011      220080304G7200                ENGINE                                  EMB   312   EMB312             SO  PWA   PT6   PT6*        52043EA                                              POWER LOSS      W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      DURING TRAINING MANEUVERS, THE PILOT REPORTED A LOSS OF ENGINE POWER.  PILOT ATTEMPTED TO RECOVER WITHOUT SUCCESS, AND EJECTED SAFELY.  AIRCRAFT CRASHED IN AN EMPTY FIELD.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 4T3  TRT        E2NE                 
             20080602     NE  2008       6          2          CA080402014      220080321G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              POWER LOSS      W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      DURING CLIMB, ENGINE POWER WAS LOST ACCOMPANIED BY A LOUD NOISE.  THE ENGINE WAS SECURED AND THE AIRCRAFT RETURNED TO BASE.  INITIAL INVESTIGATION REVEALED SEVERE ENGINE DAMAGE INCLUDING FRACTURE OF THE 2ND STAGE POWER TURBINE BLADES.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.  (TC NR 20080402014)                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRT        E20NE                
             20080602     NE  2008       6          2          CA080402017      220080327G7200                ENGINE                                  AEROSPATR72 ATR72201    8680943EU  PWA   PW120 PW124B           NE                                              MAKING METAL    W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      THE OIL PRESSURE INDICATION REDUCED TO ZERO FOLLOWED BY A LOUD NOISE, OIL MIST AND ODOR IN THE CABIN.  THE ENGINE THEN FLAMED OUT.  INITIAL INSPECTION REVEALED A CONTAMINATED CHIP DETECTOR AND THE PROPELLER DIFFICULT TO TURN.  THE ENGINE IS TO BE REMOVED FOR INSPECTION AND UPDATES WILL BE PROVIDED.                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA53EU   E2ONE                
             20080602         2008       6          2          CA080402018      420080317G6122                GOVERNOR                                BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A67B     52043NE                              PROPELLOR       MISRIGGED       W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      TAKEOFF WAS ABORTED WHEN THE ENGINE WOULD NOT PRODUCE FULL POWER.  INVESTIGATION REVEALED IMPROPER RIGGING OF THE PROP GOVERNOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA24CE   E26NE                
             20080602     NE  2008       6          2          CA080402019      220080401G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      THE CREW HEARD A LOUD NOISE ACCOMPANIED BY AN AIRCRAFT YAW.  UPON POWER REDUCTION, THE ENGINE SHUT DOWN BY ITSELF.  INITIAL INVESTIGATION REVEALS SEVERE INTERNAL ENGINE DAMAGE.  THE ENGINE WILL BE INVESTIGATED AND UPDATES WILL BE PROVIDED. (TC NR 20080402019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRT        E20NE                
             20080602     EA  2008       6          2          CA080403002      120080331G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                                              MALFUNCTIONED   W      L   ABORTED APPROACH                                                                                FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA       24045                                                          THE POST MAINTENANCE TEST FLIGHT WAS UNSUCCESSFUL. THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON APPROACH WHEN THE FLAPS WERE SELECTED FROM 0 TO 8 DEGREES.  THE FLAP ELECTRONIC CONTROL UNIT (FECU) CODES WERE RETRIEVED. THE RT BRAKE AND POSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED, THE LT BPSU WAS RE-RIGGED AND THE FECU WAS REPLACED FOR TROUBLESHOOTING.  THE AIRCRAFT WAS RELEASED AND COMPLETED A SUCCESSFUL TEST FLIGHT.  RT BPSU, P/N 855D100-9, S/N 372, TSN 24045:44, CSN 13150, TSR 20:02, CSR 12. FECU, P/N 601R93050-7, S/N 331, TSN 14405:58, CSN 10815, TSR 7938:28, CSR 6408. (TC NR 20080403002)                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20080602     WP  2008       6          2          CA080403003      220080331G73108945682         TUBE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP                              ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 RK PARTIAL RPM/PWR LOSS      FLUID LOSS                                          CLCLIMB          1                      CA                                                                      DURING TAKEOFF, THE CREW NOTED THE LT ENGINE WAS A LITTLE LOW ON POWER.  DECIDED TO RETURN TO THE AIRPORT AS THE FUEL FLOW INDICATION FOR THAT ENGINE WAS ERRATIC.  THE LANDING WAS UNEVENTFUL.  ONCE ON THE GROUND THE AIRCRAFT WAS INSPECTED BY MAINTENANCE AND THEY DETERMINED THE LINE FROM THE FUEL FLOW TRANSMITTER TO THE FUEL FLOW DIVIDER HAD SPLIT AT A BEND RADIUS IN THE TUBE CAUSING A SOMEWHAT LARGE FUEL LEAK.  THE LEAK WAS ENOUGH TO AFFECT ENGINE PERFORMANCE.  THE LINE WAS FOUND TO BE INSTALLED CORRECTLY WITH NO EXISTING DAMAGE TO THE LINE OR AREA OF THE SPLIT.  THE AGE OF THE LINE COULD NOT BE ACCURATELY DETERMINED BUT IT WAS IN VERY GOOD CONDITION AND THE PART NUMBER WAS CORRECT FOR THE ENGINE INSTALLATION. 2L72 4T4  TRTA8SW    E4WE                 
             20080602     SW  2008       6          2          CA080403005      120080331G56102621126905      WINDSHIELD                              SWRNGNSA226 SA226T      8780122SW  GARRTTTPE331TPE33110U   01514WP                              COCKPIT         CRACKED         W      BA  EMER. DESCENT           UNSCHED LANDING                                                         W  INADEQUATE Q C                                                                CRCRUISE         1                      CA       1986                                                           IN LEVEL CRUISE AT FLIGHT LEVEL 220 APPROXIMATELY 25 MINUTES AFTER DEPARTURE, THE LEFT HEATED WINDSHIELD SUDDENLY SHATTERED.  ATC WAS ADVISED AND DESCENT REQUESTED FOLLOWED BY REQUEST FOR RETURN TO CYWG.  AFTER ESTABLISHING THE RETURN COURSE AND LEVELING AT 9000 FEET, THE PASSENGERS WERE BRIEFED AND THE AIRCRAFT PROCEEDED BACK AT REDUCED CRUISE SPEED AND COMPLETED A NORMAL LANDING.  UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT.                                                                                                                                                                                                                           2L72 4T4  TRTA5SW    E4WE                 
             20080602     EU  2008       6          2          CA080403007      120080319G2121                BEARING                                 AIRBUSA319  A319112     3930323EU  CFMINTCFM565CFM565B6    13802NE                              RECIRC FAN      OVERHEATED      W      B   EMER. DESCENT                                                                                   MBJOVER TEMP                 SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CLCLIMB          1                      CA       19565                                                          NEAR TOP OF CLIMB, COCKPIT ODOR OF ACRID BURNING SMELL NOTICED.  NO ECAM OR VISUAL CUES.  DURING CRUISE CHECK NOTICED FAN IN AMBER DISPLAYED ON COND PAGE.  RECYCLED CAB FAN AND SMELL REOCCURRED IMMEDIATELY.  RETURNED TO AIRPORT.  THE SHOP REPORT INDICATED THAT THE REAR BEARING SEIZED, THE FRONT BEARING WAS DRY, THE FAN OVERHEATED BUT THE STATOR WAS ELECTRICALLY NORMAL.  THE FAN WAS DIRTY AND SMELLED OVERHEATING.                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA28NM   E37NE                
             20080602     NE  2008       6          2          CA080403008      220080401G8550100243          SHAFT                                   CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE  HAMSTD43E   43E60       NE  ENGINE OIL      SHEARED         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  LDLANDING        1                      CA            946                                                       (CAN) JUST BEFORE TURNING BASE LEG FOR LANDING THE RT BMEP GAUGE FELL TO ZERO.  NO OIL WAS OBSERVED LEAKING FROM ENGINE ALTHOUGH THE OIL QUANTITY WAS SLOWLY FALLING.  LANDING WAS CARRIED OUT NORMALLY.  ON ROLL OUT QUANTITY WAS READING 8 GALLONS, SO THE RT ENGINE WAS SHUT DOWN.  MAINTENANCE DISCOVERED THAT THE SCAVENGE PUMP HAD INGESTED A PIECE OF A CASTLE NUT WHICH HAD BROKEN OFF ONE OF THE NUTS P/N 542 FROM ONE OF THE REDUCTION PINION GEAR SHAFTS.  THIS HAD CAUSED THE FAILURE OF THE GEAR/SHAFT P/N 100243 IN THE ACCESSORY DRIVE CASE.                                                                                                                                                                                     2H72 4R4  RRTA14EA   E231    6  CP871     
             20080602     NE  2008       6          2          CA080403009      220080116G8520128495          MAIN BEARING                            DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD22D   22D30       NE  MASTER ROD      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1474                                                      DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP.  INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD BEARING.  ENGINE REMOVED FOR OVERHAUL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3R3  RRCA806    5E1     5  CP736     
             20080602     GL  2008       6          2          CA080404001      120080303G5310C2TP63ND        SPAR                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      WHEN REPLACING FRONT CENTER SPAR DUE CRACK.  REAR CENTER SPAR DISCOVERED CORRODED BEHIND CENTER MOUNT BRACKET.  SPAR REPLACED.  THIS CORROSION WAS NOT VISABLE UNTIL ACCESS TO INSIDE OF TAILPLANE WAS GAINED (TC NR 20080404001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3R3  RRCA806    5E1                  
             20080602     SW  2008       6          2          CA080404002      120080326G2913                SHAFT                                   SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              HYD PUMP        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1155                                                      DURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PUMP HAD SHEARED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA8SW    E4WE                 
             20080602     NM  2008       6          2          CA080404004      120080402G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              HYDRAULIC SYS   FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1339                                                           DURING CRUISE FL 120, NR 2 ENG HYD PRES CAUTION LIGHT ILLUMINATED.  HYD NR 2 PRESS - 0 PSI - AFTER PERFORMING ABNORMAL CHECKLIST WITH PTU ON, PRESS 3000 PSI.  UNEVENTFUL LANDING.  MAINTENANCE CREW REPLACED THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E00062EN             
             20080602     EA  2008       6          2          CA080404005      120080331G282339423091        SHUTOFF VALVE                           DHAV  DHC3  DHC3        2800202EA  GARRTTTPE331TPE33110R   0517 WP                              FUEL SYSTEM     UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            77                                                        ENGINE WOULD NOT SHUT DOWN USING NORMAL SHUT DOWN PROCEDURES.  EMERGENCY SHUTOFF PROCEDURES USED.  TROUBLESHOOTING FOUND FUEL SHUTOFF VALVE U/S (SOLENOID STICKING).  REPLACED FUEL SHUTOFF VALVE.  ENGINE RUN-UP AND SHUT DOWN NORMAL.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3R4  T  A815    E4WE                 
             20080602     NM  2008       6          2          CA080404006      120080331G24201701320         GENERATOR                               EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              APU             FAULTED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA       2802                                                           ON FIN 309 WHILE T/S A LONG HISTORY FAULT OF APU GEN FAULT.  ARCING WAS FOUND AT THE LUG T3 ATTACH POINT WITH THE APU GENERATOR.  APU GENERATOR WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA57NM   E00070EN             
             20080602     SO  2008       6          2          CA080404007      120080329G4990GTCP36150G      APU                                     GULSTMG1159 GIV         3980115SO  RROYCETAY   TAYMK6118        NE                                              LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       5558 21                                                        APU AUTO SHUT DOWN WITH LOW OIL PRESSURE FAULT.  OIL QTY RE-ADJUSTED AND APU STILL SHUT DOWN FOR LOW OIL PRESSURE.  REPLACED OIL PRESSURE SWITCH AND APU STILL SHUT DOWN INTERMITTENTLY.  AFTER TROUBLE SHOOTING WITH DIRECT OIL PRESSURE GAUGE FOUND OIL PRESSURE DELIVERY WITH INTERMITTENT LOW OIL PRESSURE READING.  SUSPECTING OIL PUMP OR PRESSURE REGULATOR.  LOANER APU INSTALLATION IN PROGRESS, MORE INFO WILL BE GIVEN WHEN REPORT OF REPAIR SHOP WILL BE GIVEN.                                                                                                                                                                                                                                                                     2L72 4F4  FRTA12EA   A25NE                
             20080602     CE  2008       6          2          CA080404009      120080404G2510                CABLE                                   CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL  PILOT SEAT      OUT OF ADJUST   W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      FLIGHT CREW DISCREPANCY, PILOTS SEAT DOES NOT SLIDE BACK INTERMITTENTLY.  SEAT REMOVED AND VISUALLY INSPECTED.  REEL ASSEMBLY CABLE ADJUSTED AND SEAT FUNCTION TESTED WITH NO DEFECTS FOUND.  SEVERAL AIRCRAFT IN OUR FLEET OF CESSNA 100 SERIES AIRCRAFT HAVE EXPERIENCED SIMILAR DISCREPANCIES, AND THE PASSENGER SEATED WAS UNABLE TO EXIT THE CABIN.                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
             20080602     NE  2008       6          2          CA080406001      220080331G73210301037950      LINE                                    SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              FUEL CONTROL    BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      TUBE WAS DISCOVERED CRACKED AND SEPARATED FROM FLARE AT P2 TAP END DURING ROUTINE INSPECTION.  ORIGINALLY, BLACK DEPOSITS WERE NOTICED AT B-NUT AND WHEN DISASSEMBLED, FOUND COMPLETE FAILURE OF TUBE FROM FLARE END.  CLOSE TOLERANCE FIT OF TUBE PROBABLY PROHIBITED ANOMALY FROM BEING NOTICED EARLIER.                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UNCH9EU    E19EU                
             20081105     NE  2008       11         5          CA080407001      220080404G7200C632A2116102    HOUSING                                 UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5291                                                           (CAN) CRACK INDICATION FOUND ON UPPER RT AREA OF INPUT HOUSING BOSS. THIS WAS FOUND DURING OVERHAUL OF THE MODULE.  PART SENT TO MFG FOR EVALUATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U3  UNCR0001RD E34NE                
             20080602         2008       6          2          CA080407002      120080331G3297472011          WIRE HARNESS                                                                                                                            NLG WOW         MISINSTALLED    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      AN OPERATOR FOUND THAT DURING INSTALLATION OF MOD SUM 4-125401, FINDING THE NEW HARNESSES PN.47201-1 THREE OUT OF SIX HARNESSES PULLED FROM STOCK WERE MISS WIRED.  ON CONNECTOR 3261-P32 PINS A-B AND D-E WERE WIRED REVERSED.  HARNESSES APPROPRIATELY REPAIRED IAW MANUFACTURER PROVIDED DATA AND RETURNED TO STOCK.  TO ADDRESS THIS ISSUE, SERVICE LETTER DH8-SL-32-014A ADVISING OF POSSIBLE MANUFACTURING FAULTS WAS RAISED.                                                                                                                                                                                                                                                                                                                                                       
             20080602     EA  2008       6          2          CA080407003      120080406G2752852D1001921     ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              FLAP            UNSERVICEABLE   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      ON APPROACH AT 4000 FT SELECTING FLAPS FROM 0 - 8 DEG, FLAP FAIL MSG APPEARED IMMEDIATELY WITH NO MOVEMENT OF FLAPS.  AIRSPEED 215 AT THE TIME.  A/C WAS AT -57 DEG FOR 1 HR IN CRUISE, GND -4.  FECU INTERGRADED AND FOLLOWING FAULT CODES DISPLAYED AS FECU WAS LOOKED AT: (1) JAM (2) LEFT BPSU (3) 1 5 1B.  TRIED TO GO FURTHER AFTER THE STEP OF `GO` IN THE FIM AND IT WOULD GIVE THE FAULT CODE 1 5 1B  CB 1-F4 AND CB 2-F4 AND SYSTEM RESET WITH NO FURTHER FAULTS.  FERRY FLIGHT PAPERWORK COMPLETED.  A/C FERRIED.  TROUBLESHOOTING GOING ON, ACTION PLAN TO INSPECT AND LUBE ALL DRIVES AND CHANGE ALL FLAP ACTUATORS WITH NEWLY OVERHAULED UNITS SENT.  INFORMATION WILL BE UPDATED WHEN AVAILABLE.                                 2L72 4F4  FRTA21EA   E15NE                
             20080602     GL  2008       6          2          CA080407004      120080404G32341760A000004     LEVER                                   BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              MLG             LOOSE           W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      AFTER TAKEOFF, IT WAS REPORTED THAT THE CREW WERE UNABLE TO RETRACT THE FLAPS FROM THE 10 DEGREE POSITION TO THE 0 DEGREE POSITION.  PRELIMINARY REPORT STATES THAT A LOOSE SCREW WAS FOUND INSIDE THE FLAP LEVER GUARD.  THE FORWARD RIGHT SCREW LOCATED INSIDE THE GUARD WAS FOUND TO BE PROTRUDING SUFFICIENTLY TO PREVENT THE LEVER FROM MOVING FROM THE 10 DEGREE POSITION TO THE 0 DEGREE POSITION.  ALL THREE REMAINING SCREWS WERE FOUND TO BE SECURE.  A VISUAL AND TACTILE INSPECTION CAN BE PERFORMED TO ENSURE THAT ALL 4 SCREWS LOCATED INSIDE THE FLAP LEVER GUARD ARE SLIGHTLY COUNTERSUNK AND DO NOT SHOW ANY SIGNS OF LOOSENESS (REFER TO FIGURE1).  PLEASE REPORT ANY ANOMALIES FOUND DURING THIS INSPECTION.                 2L72 4F4  FRTT00005NYE00010LA             
             20080602     EA  2008       6          2          CA080407005      220080403G7200PT6A20          ENGINE                                  DHAV  DHC6  DHC6100     2802610EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL                  STOPPED         W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CLCLIMB          1                      CA       117864634                                                      AFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHECKS, THE CREW HEARD A LOUD POP AND SCRAPPING NOISE FROM THE NUMBER ONE ENGINE.  THE FLIGHT CREW OBSERVED THAT THE NUMBER ONE PROPELLER WAS STOPPED AND ALL ENGINE GAUGES WERE AT ZERO.  EMERGENCY CHECKLIST WAS FOLLOWED AND THE AIRCRAFT LANDED SAFELY WITH ONE ENGINE RUNNING.  ENGINE TO BE REMOVED FOR EVALUATION BY REPAIR FACILITY.                                                                                                                                                                                                                                                                               1H72 3T3  TRTA9EA    E4EA    6  CP15EA    
             20081105     EU  2008       11         5          CA080407006      120080405G2913A5026780        PUMP                                    SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B    60037NE                              HYDRAULIC SYS   MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       2763 2763                                                      (CAN) DURING NORMAL FLIGHT DURING A BIRD TOWING OPERATION THE PILOT RECEIVED A BING INDICATING A FAILURE. AIRSPEED 60KTS, 1000 FT AGL, 170 FT LINE WITH BIRD, 45 MINUTES INTO FIRST FLIGHT OF THE DAY:  " BING " HEARD IN HEADSET, HYD WARNING LIGHT OBSERVED, NOTICE CHANGE OF FEEL TO THE CYCLIC CONTROL (ACCUMULATORS ACTIVATED) CHECKED THAT BOTH HYD SWITCHES HAD NOT BEEN INADVERTENTLY ACTIVATED. OBSERVED AIRSPEED 60KTS, SWITCHED HYD CUT OFF TO ON POSITION, CONTINUED TO DECENT TO A LAKE, SET UP FLAT APPROACH WITH BIRD.  RADAR ALT INDICATED BIRD WAS 5 FT OFF GROUND LOAD WAS JETTISONED AT 25KTS IAS  POSITION FOR A SECOND APPROACH AND LANDED HELICOPTER WITHOUT INCIDENT THE HYDR PUMP WAS REPLACED AFTER AND ACFT WAS TEST F1G71 3U3  U  H9EU    E00054EN             
             20080602     SW  2008       6          2          CA080407007      120080405G6322R476204971      GEAR SET        BELL        4762060025  BELL  47    47G4        1181030SW  LYC   O540  VO540B1B3   41532EA                              COOLING FAN     SHEARED         W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      CA       77                                                             APPROX 100 HRS AGO TRANSMISSION WAS O/H AND NEW PMA GEAR SET WAS INSTALLED S/N GR586A FROM HELICOPTER TECH DURING FLIGHT PILOT HEARD AND FELT NOISE AND MADE A PRECAUTIONARY LANDING AND FOUND COOLING FAN DRIVE PULLEY AND APPROX 1.25 INCHES OF THE DRIVE SHAFT WAS MISSING.  WE ARE SENDING IN REMAINING SHAFT SEGMENT WHERE IT SHEARED FOR METALLURGICAL ANALYSIS.                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  2H3     E304                 
             20080602     EA  2008       6          2          CA080407010      120080402G3250                CABLE                                   DHAV  DHC6  DHC6200     2802620EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  STEERING        BROKEN          W      D   RETURN TO BLOCK                                                                                 S  AFFECT SYSTEMS                                                                TXTAXI/GRND HDL  1                      CA                                                                      STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3T3  TRTA9EA    E4EA    6  CP15EA    
             20080602     EU  2008       6          2          CA080408001      120080408G25204030082SRS      ATTACH FITTING                          PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  PAX SEAT        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8953                                                           DURING 100 HOUR INSPECTION PASSENGER SEAT RECLINE HYDRAULIC MOUNT ATTACHMENT FOUND CRACKED.  SEAT MANUFACTURER IS ERDA. NOT FOUND IN ASSEMBLY MANUFACTURER LIST.  REPAIR INFORMATION REQUESTED THROUGH AIRCRAFT MANUFACTURER, PILATUS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20080602     EA  2008       6          2          CA080408002      120080329G275070745           CONTROL UNIT                            CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              TE FLAP MOTOR   FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       8989 8989                                                      PRIOR TO DEPARTURE FLIGHT CREW COMPLETED A STAB TRIM RESET.  SHORTLY AFTER FLAP RETRACTION ON TAKEOFF, FLIGHT CREW RECEIVED AN AP TRIM IS ND ASSOCIATED WITH AN AP PITCH TRIM CAUTION MESSAGE.  SUBSEQUENTLY CREW RECEIVED A ELEVATOR SPLIT CAUTION MESSAGE.  CREW FOLLOWED QRH, CIRCLED TO BURN OFF FUEL AND LANDED BACK AT DEPARTURE AIRPORT WITHOUT INCIDENT.  MAINTENANCE CHECKED ELEVATOR TRIM POSITION FULL NOSE DOWN, NEUTRAL AND FULL NOSE UP OK.  AUTO PILOT ELEVATOR SERVO OPERATION CHECKED OK.  ELEVATOR SPLIT MESSAGE TROUBLESHOT PER FIM TASK OK.  PROBLEM ISOLATED AS MDC DISPLAYED AN INTERNAL FAULT OF THE MOTOR CONTROL UNIT CHANNEL 2 INTERNAL HOLD ON RELAY.  MOTOR CONTROL UNIT REPLACED.  OPERATIONAL TESTS OF THE SSCU,2L72 4F4  FRTA21EA   E00063EN             
             20080602     NM  2008       6          2          CA080408003      120080404G2130                CABIN PRESSURE                          BOEING757   75728A      1384976NM  RROYCERB211 RB211535E43754555NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 G  MULTIPLE FAILURE                                                              CLCLIMB          1                      CA                                                                      AIRCRAFT C-GTDX DEPARTING FROM YYZ ON APRIL 4TH 2008, AROUND 7000 FT AN EICAS MSG AUTO PRESSURIZATION SYS 1 AND 2, AIRCRAFT RETURNED BACK TO YYZ AND REQUESTED FIRE TRUCKS ON ARRIVAL DUE TO OVERWEIGHT LANDING.  TROUBLESHOOTING CARRIED OUT, BOTH PRESSURIZATION CONTROL UNITS AND STBY ALTIMETER REPLACED AS PRECAUTIONARY MEASURE.  FLIGHT TEST CARRIED OUT SUCCESSFULLY.  INVESTIGATION IS ON GOING.                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA2NM    E12EU                
             20080602     EA  2008       6          2          CA080408004      120080330G3230101655          UPLOCK ROLLER                           DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RH MLG          SEIZED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       3589520079                                                     RT MLG FAILED TO EXTEND ON LANDING GEAR SELECTION, CREW PERFORMED GO-AROUND AND USED ALTERNATE GEAR EXTENSION.  ALL LANDING GEAR EXTENDED AND NORMAL LANDING CARRIED OUT.  MAINTENANCE INSPECTION FOUND RT MLG UPLOCK ROLLER SEIZED, ROLLER REPLACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE.  TIMES PROVIDED ARE SHOCK STRUT TIMES, ROLLER IS NOT SERIALIZED AND NOT TRACKED FOR ACTUAL TIMES.                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080602     EU  2008       6          2          CA080409001      120080325G259740900011        WIRE                                    AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2*         GL                              COFFEEMAKER     BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       4341 483                                                       IN CRUISE AFT GALLEY RT COFFEEMAKER BURNED.  ALL C/BS WERE PULLED.  HALON FIRE EXTINGUISHER WAS USED AS A PRECAUTIONARY MEASURE.  C/B ON COFFEE MAKER FOUND POPPED.  FOUND WIRES TO PRESSURE SWITCH BURNED AND DISCONNECTED.  NO OTHER WIRING DAMAGE ON THE COFFEE MAKER.  COFFEE MAKER REPLACED AND ROUTED TO SHOP FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA35EU   E23EA                
             20080602     EU  2008       6          2          CA080409003      120080407G2133                OUTFLOW VALVE                           AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              CABIN PRESSURE  MALFUNCTIONED   W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      AFTER 30 MIN IN CRUISE, CAB PRESSURE REG NR 2 FAULT, FOLLOWED BY CAB PRESSURE REG NR 1 FAULT.  UNABLE TO CONTROL IN MANUAL.  EMERGENCY DESCENT AND QAR PROCEDURES FOLLOWED.  PAX MASK SYSTEM ACTIVATED IN AUTO.  FLIGHT RETURNED TO STATION AT FL 10,000 FT.  ACFT WAS REMOVED FROM SERVICE FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA35EU   E23EA                
             20080602     EA  2008       6          2          CA080409004      120080330G3040601R3303313     CONTROLLER                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              WINDSHIELD TEMP OVERTEMP        W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       1432514325                                                     ON DESCENT THROUGH 21000 FEET INTO ARRIVAL AIRPORT, CAPTAINS LT WINDSCREEN SHATTERED.  CREW DONNED OXYGEN MASKS AS A PRECAUTION.  CREW DECLARED AN EMERGENCY WITH ATC AND MADE ANNOUNCEMENT TO THE PASSENGERS.  FLIGHT LANDED WITHOUT INCIDENT.  MAINTENANCE REPLACED THE WINDSHIELD ASSEMBLY P/N 601R33033-13, S/N 01057H1890, TIMES AND CYCLES SAME AS THE TEMPERATURE CONTROLLER.  MAINTENANCE ALSO REPLACED THE LT WINDSHIELD TEMPERATURE CONTROLLER SUSPECTING THAT IT HAS CAUSED AN OVERHEAT CONDITION.                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20081105     SW  2008       11         5          CA080409005      120080409G2450MS2207375       CIRCUIT BREAKER                         BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              OVERHEAD PANEL  INOPERATIVE     W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT ABLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANEL IS WAS NOTED THAT IN EXCESS OF 20 BREAKERS WERE DIFFICULT TO OR UNABLE TO BE CYCLED. REQUIRED CIRCUIT BREAKERS WERE REPLACED. INSPECTION CRITERIA TO NOW INCLUDE CYCLING BREAKERS AT INTERVALS TO REDUCE THE CHANCE OF A BREAKER NOT POPPING WHEN REQUIRED AND CAUSING FURTHER PROBLEMS/DAMAGE. (TC NR 20080409005)                                                                                                                                                                           1G71 4U4  U  H1SW    E17EA                
             20080602     EA  2008       6          2          CA080409006      220080330G7230                BLADES                                  BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                              COMPRESSOR TURB FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      ON APPROACH, THE CREW NOTED ENGINE TEMP AT APPROX 900 DEGREES FOLLOWED BY SOME NOISES.  THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED.  INITIAL INVESTIGATION REVEALED LOSS OF COMPRESSOR TURBINE BLADE MATERIAL AND SHROUD SEGMENT MATERIAL, THE ENGINE WAS SENT FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 4U4  U  H4SW    E22EA                
             20080602     EA  2008       6          2          CA080409008      120080409G521033130131        PISTON                                  CNDAIRCL215 CL2151A10   1900320EA                                                               ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4499                                                           ANOTHER OPERATOR INFORMED OUR QUALITY ASSURANCE DEPARTMENT OF THEIR FINDING CRACKS IN THE ACTUATOR THREADED PORTION IN 5 OUT OF 7 ACTUATORS.  INSPECTED ALL 14 OF OUR FLEET ACTUATORS AND FOUND 4 TO BE CRACKED ALSO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4R    RTA14EA                        
             20081105     NE  2008       11         5          CA080410004      220080401G7314LW15473         PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       881                                                            (CAN) DURING A DAILY INSP OIL WAS FOUND LEAKING FROM THE ENGINE DRIVEN FUEL PUMP, PART WAS REMOVED AND REPLACED (TC NR 20080410004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20080602     EA  2008       6          2          CA080410005      120080408G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              RT FLAP SYS     UNSERVICEABLE   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       3291                                                           ON DESCENT, CREW SELECTED AND RECEIVED FLAPS 8 DEGREES, WHEN THEY ATTEMPTED TO PROCEED TO FLAPS 20 CREW RECEIVED A FLAP FAIL MESSAGE.  FLIGHT LANDED WITHOUT INCIDENT.  FECU MESSAGE POINTED TO THE RT BPSU AS THE FAULT.  THE RT BPSU WAS REPLACED, FLAP SYSTEM RIGGED AND FUNCTION CHECKED SERVICEABLE.  THE A/C RETURNED TO SERVICE WITH NO FURTHER FAULTS.                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20081105     WP  2008       11         5          CA080410006      120080409G6310                SHAFT                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CLUTCH          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1998                                                           (CAN) CLUTCH WAS REMOVED FOR GRINDING NOISE ON GROUND RUN. DURING DISASSEMBLY THE OIL IN THE CLUTCH WAS VERY BLACK DUE TO INTERNAL WEAR OF THE SHAFT, HSG AND SPRAG. THE SPRAG CAGE CROSSBAR WAS CRACKED, PEANUT INNER EARS WERE BROKEN OFF, WEAR ON THE INNER SURFACE OF THE PEANUTS (POSSIBLE SLIPPAGE) AND EXCESSIVE CAGE WINDOW WEAR.                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
             20080602     SO  2008       6          2          CA080410009      220080312G8530AEC631397SN2B22 CYLINDER HEAD                           CESSNA414   414         2075908CE  CONT  O520  TSIO520N    17040SO  MCAULY3AF32C3AF32C505   GL  ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA            105                                                       PILOT FLYING IN CRUISE FLIGHT, WHEN HE HEARD A POP AND EXPERIENCED LOSS OF ENGINE POWER.  FEATHERED PROPELLER AND LANDED AT NEAREST AIRPORT.  ENGINE CYLINDER REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  ORTA7CE    E8CE    5  CP22EA    
             20081105     EU  2008       11         5          CA080411001      120080220G6700D107610E        ACTUATOR                                BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              TRIM SYS        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080411001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 3U3  U  H3EU    E4CE                 
             20080602         2008       6          2          CA080411002      420080409G6122210332          PILOT VALVE     WOODWARD                                                                                                                GOVERNOR        DAMAGED         W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               NRNOT REPORTED   1                      CA       97                                                             THE GOVERNOR WAS MANUFACTURED BY ONTIC, ONTIC HAS THE MANUFACTURING RIGHTS TO THE FORMER WOODWARD GOVERNOR COMPANY PISTON ENGINE GOVERNORS.  THE GOVERNOR WAS RECEIVED FROM THE AIRCRAFT MANUFACTURE, DIAMOND AIRCRAFT INDUSTRIES, FOR REPAIR IN APRIL 2008.  ACCORDING TO A CUSTOMER CLAIM/RETURN AUTHORIZATION FORM RECEIVED FROM DIAMOND, THE GOVERNOR WAS REMOVED FROM AIRCRAFT SERIAL NR 40.438 ON OR ABOUT SEPTEMBER 21, 2005, WITH AIRCRAFT TTSN OF 96.9 HOURS.  WITH ORIGINAL COMPLIANT OF ENGINE OVERREVED DURING FLIGHT, COULD NOT CONTROL PROPELLER.  THE NAME PLATE ON THE GOVERNOR GIVES A ASSY DATE OF 08/04 DURING INSPECTION OF THE GOVERNOR IN OUR SHOP, AFTER REMOVAL OF THE TOP COVER, IT WAS FOUND THAT THE HEAD END HAD SEP                                          
             20081105     EU  2008       11         5          CA080411003      120080220G670010513142        ROD END                                 BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              BEARING         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G72 3U3  U  H3EU    E4CE                 
             20080602     NM  2008       6          2          CA080411004      120080408G29106517840330      LINE                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D15      52051NE                              HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      AFTER TAKEOFF WHEN GEAR SELECTED UP, HYDRAULIC SYSTEM "A" LOW LEVEL LIGHT ILLUMINATED AND HYDRAULIC QUANTITY DROPPED TO 2.0 GAL.  FLIGHT CREW DECLARED AN EMERGENCY AND RETURNED FOR APPROACH.  PER FLIGHT CREW CHECKLIST GEAR WAS MANUALLY LOWERED HOWEVER FLIGHT CREW WAS UNABLE TO MANUALLY LOWER THE LT GEAR.  TWO ATTEMPTS WERE MADE AND THEN THE FLIGHT CREW SELECTED ON ONE "A" SYSTEM HYDRAULIC PUMP TO GET THE LT GEAR DOWN AND LOCKED.  THE PUMP WAS THEN TURNED OFF AGAIN.  THE AIRCRAFT LANDED SUCCESSFULLY WITH NO ADDITIONAL FAULTS.  MAINTENANCE PERSONNEL FOUND A PIN HOLE LEAK ON THE A SYSTEM HYDRAULIC RETURN LINE RETURNING FROM THE A SYSTEM HEAT EXCHANGER.  A PERMANENT REPAIR WAS CARRIED OUT BY THE INSTALLATION OF A P2L73 4F4  F  A3WE    E2EA                 
             20080602     GL  2008       6          2          CA080411006      220080409G725023063354        TURBINE                                 BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              ENGINE          DAMAGED         W      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA       4509 1226                                                      ON THE THIRD MAIN ROTOR STROBING FLIGHT OF THE MORNING AND WHILE ACCELERATING FROM 100KTS TO 120KTS, A LOW HOWLING NOISE WAS HEARD WHICH INTENSIFIED RAPIDLY AND WAS FOLLOWED IMMEDIATELY BY AN ENGINE CHIP LIGHT.  A FORCED LANDING WAS MADE TO A FIELD.  AN EXTERNAL INSP INCH BY 4 INCH PIECE OF SHEET METAL WAS FOUND BROKEN AWAY FROM THE AFT RIGHT SIDE OF THE EXHAUST STACK.  AFTER REMOVAL OF THE OUTER COMBUSTION CASE MAJOR VISIBLE DAMAGE WAS FOUND TO THE 1ST AND 2ND STAGE TURBINE BLADE TIPS.  TURBINE SECTION IS BEING SENT TO STANDARD AERO LTD FOR INSPECTION WITH ROLLS ROYCE PARTICIPATION.  1ST AND 2ND TURBINE WHEEL CYCLES ARE 2004, 3RD AND 4TH STAGE CYCLES ARE 4977.  ENGINE DATA COULD NOT BE DOWNLOADED FROM THE ECU,1G71 3U3  UO H2SW    E1GL                 
             20080602     CE  2008       6          2          CA080411007      120080407G32450923150         TUBE                                    CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE  MCAULY4HFR344HFR34C762  NE  NLG WHEEL       LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       62                                                             NOSE TIRE FOUND LOW ON POST FLIGHT INSPECTION BY 10 PSI.  NOSE WHEEL ASSY REMOVED FOR TEAR DOWN AND INVESTIGATION.  SPARE BUILT-UP WHEEL ASSY INSTALLED.  TEAR DOWN SHOWED INNER TUBE HAD PIN HOLE IN OUTER CIRCUMFERENCE AT ONE END OF A FOLD MARK.  NO OTHER FAULTS FOUND WITH TIRE OR TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3T3  TRTA7CE    E4EA    6  C3PNE     
             20080603     GL  2008       6          3          CA080414001      120080407G5711                SPAR                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5796                                                           CRACKS FOUND WHILE COMPLYING WITH SB2/47.  CRACKS JUST VISIBLE WITH FLUORESCENT PENETRANT INSPECTION.  WHEN SPAR REMOVED CRACKS WERE VISIBLE TO NAKED EYE ON THE INTERIOR OF SPAR AND ON GUSSET BETWEEN SPAR AND GUSSET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3R3  RRCA806    5E1     5  CP206     
             20080603     WP  2008       6          3          CA080414003      120080410G2435                GEAR                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER GEN     WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       58                                                             UPON POST FLIGHT INSPECTION, STARTER TEETH FOUND WORN, REMOVED AND INSTALLED NEW STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
             20080603     WP  2008       6          3          CA080414004      120080410G6310                CLUTCH ACTUATOR                         ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1552                                                           UPON INSPECTION, CARRIED OUT METHOD 2 AND THE ACTUATOR KEPT RUNNING .                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20080603     EA  2008       6          3          CA080414005      220080411G72303012060         DUCT                                                                       PWA   PT6   PT6A27      52043EA                                              DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      METAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                4  T          E4EA                 
             20080603         2008       6          3          CA080414006      420080407G221008071           STATIC LINE                             AIRTRCAT802 AT802A      0390308SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  AUTO PILOT SYS  DETERIORATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       697                                                            DURING RE-ACTIVATION OF THE AIRCRAFT, THE MAINTENANCE CREW NOTICED THAT THE STATIC LINE FOR THE AUTO PILOT ALTITUDE HOLD P/N 0807-1 WAS DETERIORATED AND CRACKED.  THE LINE WAS REPLACED WITH A SERVICEABLE PART.  ALL OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED FOR SERVICEABILITY.                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
             20080603     NM  2008       6          3          CA080414008      120080328G3242                BRAKE DISC      BFGOODRICH              DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MLG BRAKE ASSY  WARPED          W      O   OTHER                                                                                           MJ OVER TEMP                 WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       395056254                                                      RAMP CREW NOTICED THAT RT INBOARD (NR 3) MAIN WHEEL WAS FLAT WHILE AIRCRAFT WAS PARKED AT GATE.  MAINTENANCE DISCOVERED THE NR 3 BRAKE UNIT WITH A WARPED/OVERHEATED BRAKE DISKS WHICH CAUSED THE FUSE PLUGS ON THE NR 3 MAIN WHEEL TO BLOW.  MAINTENANCE REPLACED THE NR 3 BRAKE UNIT AND THE NR 3 AND 4 MAIN WHEEL ASSEMBLIES.  TAXI AND FUNCTION CHECKS OF THE BRAKING SYSTEM WERE COMPLETED WITH NO FURTHER FAULTS FOUND.  WHEEL SHOP CONFIRMED BRAKE UNIT DID OVERHEAT AND THAT IT WAS NOT A FAULT WITH THE UNIT.                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080603         2008       6          3          CA080414009      120080414G31107003652631      DISPLAY                                                                                                                                 COCKPIT         INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FAIL AT INSTALLATION, AND CAME BACK OUT WITH THE SAME PROBLEM THAT WE SENT FOR REPAIR. DISPLAY BLANK OUT AFTER POWER UP O 5800145883,DATE REPAIR MARCH 14 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
             20080603     EU  2008       6          3          CA080415004      120080408G2750Z4243130000     CONTROL CABLE                           ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA                              TE FLAPS        FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O0 A76EU   1E10                 
             20080603     SW  2008       6          3          CA080415005      120080412G56102719442004      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              COCKPIT         CRACKED         W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA       1233                                                           DURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AIRCRAFT DESCENDED THE CABIN DIFF WAS LOWERED AND AIRSPEED REDUCED.  UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT.                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA8SW    E4WE                 
             20080603     NE  2008       6          3          CA080415006      220080411G7250                BLADE                                                                      TMECA ARRIELARRIEL1B    6OO30NE                              TURBINE WHEEL   DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      1ST STAGE TURBINE WHEEL BLADE LEADING EDGE DAMAGE IN ZONE 2 ON A TOTAL OF 8 BLADES.  THE DAMAGE WAS CAUSED BY THE SEMI-CONDUCTOR OF THE IGNITER, P/N 9550175400, THAT DISLODGED ITSELF FROM THE HOUSING. THIS WAS FOUND DURING A SCHEDULED 100/150 HR ENGINE INSPECTION.  THE AFFECTED MO3 HAS BEEN SEND TO MANUFACTURER FOR FUTURE INVESTIGATION.  SUBSEQUENTLY ALL OTHER ENGINE IGNITER WHERE INSPECTED AND REMOVED FROM SERVICE DO TO LOOSENESS OF THE SEMI-CONDUCTOR.  PICTURES WERE TAKEN AND SEND TO MANUFACTURER.                                                                                                                                                                                                                               3  U          E19EU                
             20080521     WP  2008       5          21         CA080415007      120080411G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       79                                                             (CAN) AFTER FIRST GROUND RUN, STARTER CRACKED, REPLACED STARTER (TC NR 20080415007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20080521     EU  2008       5          21         CA080416001      120080414G5302V40GT3911AA     SPRING                                  BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              TAIL BOOM       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COMING OUT OF A MAJOR INSP, WHERE THE EJECTION SPRINGS ON ALL THE COWLS ( P/N 105-62648, 105-62664, 105-62643, 105-62663 AND 105-30851) WERE REPLACED. SEVERAL EJECTION SPRINGS P/N V40GT39-1-1AA WERE BREAKING INTO (2) PIECES. THIS PROBLEM HAPPENED STATICALLY ON THE GROUND. THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG, BATCH NR S0000243616 COMING FROM DIFFERENT LOT NR. BREAKAGE HAPPENS IN THE MFG LOGO STAMPED ON THE EJECTION SPRING.  NEW EJECTION SPRINGS SAME PN, SAME BATCH NR USED TO REPLACE BROKEN ONES ON THIS AC. (TC NR 20080416001)                                                                                                                                                                           1G72 3U3  U  H3EU    E4CE                 
             20080521     NE  2008       5          21         CA080416002      220080416G7414                COIL                        BL6006163   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP.  WHEN VENT PLUG WAS REMOVED DIRTY BROWN OIL WAS FOUND IN THE MAGNETO. UPON DISASSEMBLY THE OIL SEAL WAS FOUND TO BE LEAKING. THE COIL WAS LOOSE IN THE HOUSING UNDER THE COIL CLAMPS. THE COIL HAD DARK BROWN MATERIAL AROUND THE MOUNTING AREA OF THE COIL POLES FROM WEARING AGAINST THE HOUSING. BOTH THE COIL AND HOUSING WERE UNSERVICEABLE DUE TO THE AMOUNT OF WEAR. THE MAGNETO HAD A NEW STYLE OF HOUSING WITH THE LETTERS (TCM) RAISED IN THE CASTING AND A NEW CONTINENTAL ALPHA SYS DATAPLATE. THIS MAG WAS REBUILT  IN JANUARY OF 2007. THE MAG WAS RETURNED TO MFG FOR WARRANTY PURPOSES. (TC NR 20080416002)                                                                           1G71 3O3  O  H11NM   1E4                  
             20080521         2008       5          21         CA080416003      420080416G2562ELT10           ELT                                     BBAVIA7     7GCAA       21101N8SW  LYC   O320  O320A2B     41508EA                                              INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN TESTING UNIT FOR ITS 12 MONTH CERTIFICATION IAW CAR 571 APPENDIX G, UNIT DID NOT HAVE ANY TRANSMIT POWER. ELT TRANSMITTER BOARD REPLACED AND UNIT TESTED SERVICEABLE. (TC NR 20080416003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  A759    E274                 
             20080521     WP  2008       5          21         CA080417003      120080413G7920                PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE OIL      LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       978                                                            (CAN) DURING INSPECTION THERE WAS EVIDENCE OF OIL COMING OUT OF THE DRAIN LINE. THERE HAS BEEN MANY PUMPS LEAKING FORM THE SEALS AND THIS ALLOWS ENGINE OIL TO BYPASS AND FLOW OUT OF THE DRAIN. PUMP WAS REPLACED AND AIRCRAFT RETURN TO SERVICE. DATE CODE ON THE PUMP IS 4105. (TCNR 20080417003)                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20080521     EU  2008       5          21         CA080417010      120080221G5610                SEAL                                    SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              CHIN BUBBLE     DEPARTED        W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      CA                                                                      (CAN) CHIN BUBBLE WINDOW AND SEAL DEPARTED THE AIRCRAFT IN CRUISE FLIGHT. AIRCRAFT WAS LANDED AND CHECKED FOR DAMAGE, NOT FOUND. REVIEW INDCATED THAT THE WINDOW WAS REMOVED FOR MAINT BEFORE THE OCCURANCE.   WILL FOLLOW UP FOR SPECIFIC PN (TC NR 20080417010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH9EU    E19EU                
             20080521         2008       5          21         CA080418001      120080416G3310REE75R          RHEOSTAT        VIKING      72510090005                                    PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  RESISTANCE COILSMELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CONCERNED WITH THE USE OF RHEOSTAT (PN REE75R) FOR REPLACEMENT OF RHEOSTAT SWITCH 20465-1. THE SB 7-33-21 CALLS THE NEW RHEOSTAT, A RHEOSTAT SWITCH BUT IT DOES NOT HAVE AN "OFF" POSITION LIKE THE ORIGINAL RHEOSTAT SWITCH HAD. AS SUCH, WHEN IT IS TURNED TO THE SIMULATED OFF POSITION, IT IS STILL IN CIRCUIT (EVIDENCED BY THE FACT THAT THE UTILITY LIGHT HAS A SLIGHT GLOW) AND DISSIPATING MAXIMUM WATTAGE.  THE HEAT IS TRANSFERRED THROUGH THE RHEOSTAT SHAFT CAUSING KNOB PN MS91528-1C1-B TO BECOME DEFORMED AND HOT TO THE TOUCH.  ALSO, THE PANEL MATERIAL ADJACENT TO THE RHEOSTAT SHOWS EVIDENCE OF HEAT DAMAGE (CRACKING/DISCOLORATION).  HAVE CONDUCTED BENCH TESTS ON THIS RHEOSTAT TO SIMULATE THE AC CIRCUIT AND HAV       4  T          E4EA    6  CP1NE     
             20080521     NM  2008       5          21         CA080418002      120080417G2612                FIRE DETECTOR                           BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              NR 1 NACELLE    FALSE INDICATIONW      F   ACTIVATE FIRE EXT.                                                                              N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, AT APPROX 1,000 FEET AGL, THERE WAS A FIRE WARNING ON THE NR 1 ENGINE. THRUST LEVER RETARDED, LIGHT REMAINED ON. EMERGENCY DRILL COMPLETED AND LIGHT EXTINGUISHED AFTER FIRE BOTTLE DISCHARGED.  AC RETURNED AND LANDED WITHOUT FURTHER INCIDENT.  THERE WAS NO EVIDENCE OF A FIRE.  MAINT FOUND THE FAULT IN THE NR 1 FIRE DETECTION B SYS. (TC NR 20080418002)                                                                                                                                                                                                                                                                                                                                                           2L73 4F4  F  A3WE    E2EA                 
             20080521         2008       5          21         CA080418003      120080318G3245302120402       TUBE                                                                                                                                    MLG TIRE        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MULTIPLE FAILURES OF INNER TUBES ON VARIETY OF COMPANY C-208 MAIN WHEELS. TUBES FAIL IN DIFFERENT WAYS FROM PIN HOLES TO 18 INCH SPLITS. THERE HAVE BEEN NO FOREIGN OBJECTS FOUND IN THE AFFECTED TIRES AND ASSY PRACTICES HAVE BEEN OBSERVED TO ENSURE CORRECT PROCEDURES ARE BEING FOLLOWED. TUBES ARE PURCHASED FROM A VARIETY OF SUPPLIERS AND ORIGINATE IN DIFFERENT COUNTRIES. (TC NR 20080418003)                                                                                                                                                                                                                                                                                                                                                                            
             20080521         2008       5          21         CA080418004      420080417G6113VT2E16231       PLATE                                   DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  PROP SPINNER    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       35                                                             (CAN) RECEIVED A CALL REGARDING DAMAGE THAT OCCURRED TO THE PROP BACKING PLATED ON A TURBO BEAVER WE COMPLETED REG, C-FOEU. THIS DAMAGE IS THE RESULT OF OUR INSTALLATION OF OUR PROP POSITION TRANSMITTER MOD STCSA 98-46, VT2E 1623.  IDENTIFIED THE PROBLEM TO BE THE INCOMPATIBILITY BETWEEN THE PROP SPINNER BACKING AND OUR POSITION INDICATOR. THE BACKING PLATE IN QUESTION HAS A DIFFERENT PROFILE FROM THE ONES THAT WE HAVE SEEN BEFORE. COMPARED THIS PROBLEM BACKING PLATE TO OUR A/C AND THERE IS A BIG DIFFERENCE, OURS ALLOWS ALMOST .5 CLEARANCE AND THERE IS NO INTERFERENCE WITH THE CAM ROD THROUGH THE TOTAL MOTION.   MFG NEEDS TO IDENTIFY THIS COMPATIBILITY ISSUE IN THE STC AND FOR THE INTERIM SEND OUT A SL TO THE O1H71 3T4  T  A806    E4EA    6  CP15EA    
             20080521     SO  2008       5          21         CA080421001      120080408G3210424052          COTTER PIN      PIPER       7872331     PIPER PA44  PA44180     7104402SO  LYC   O360  LO360E1A6   41514EA  HARTZLHCC2Y HCC2YR2     GL  TORQUE LINK     MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COTTER PIN MISSING ON LT MLG TORQUE LINK DURING WALK AROUND.  BOLT REMOVED AND FOUND DRY OF LUBRICATION, WHICH COULD HAVE CAUSE NUT TO TURN AND SHEARING OF COTTER PIN.  NEW BOLT INSTALLED AND LUBRICATED ON BOTH MAIN GEAR TORK LINKS. (TC NR 20080421001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A19S0   E286    5  CP920     
             20080521     NE  2008       5          21         CA080422002      220080417G72503053094CL       BLADE                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  ENGINE          DEFORMED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       820                                                            (CAN) THE PILOTS NOTICE THAT THE ENGINE WAS RUNNING 50 DEGREES HOTTER THAN NORMAL. A HOT SECTION (HSI) WAS COMPLETED AND IT WAS FOUND THAT THE OLD SEGMENT 3053094CL WAS INSTALLED 820 HOURS BEFORE WITH A NEW WHEEL AND BLADES. THE SEGMENTS HAD DEFORMED AND THE CT BLADES HAD RUBBED AGAINST THE SEGMENTS CAUSING EXCESSIVE CLEARANCES. THIS WORK HAD BEEN DONE BY MFG.  THE HOT SECTION WAS SENT BACK FOR WARRANTY CONSIDERATION . (TC NR 20080422002)                                                                                                                                                                                                                                                                                      1L72 4T4  T  A24CE   E4EA    6  CP15EA    
             20080522         2008       5          22         CA080422003      420080420G8300                COUPLER                                 LKHEED188   188A        5262602WP  ALLSN 501D  501D13      03004GL  ALLSN A6441 A6441FN606  GL  ENG/GEARBOX     UNKNOWN         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING START SEQUENCE OF NR 4 ENGINE, IT WAS OBSERVED THAT RPM AND ACCELERATION CLIMBED TOO FAST, BEFORE LIGHT OFF, ENGINE START ABORTED AND FOUND ENGINE DECOUPLED FROM GEARBOX. SUSPECT TORQUE SHAFT COUPLER (TC NR 20080422003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L74 4T4  TRT4A22    E282    6  CP898     
             20080522     NE  2008       5          22         CA080423003      220080421G73201520KDC0501     EEC                                     BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                              ENGINE          UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) THE AIRCREW REPORTED THE FOLLOWING, AC WAS CRUISING AT FL450 AND CREW REALIZED THAT THE LT ENGINE SPOOLED DOWN TO IDLE WITHOUT PILOT INPUT. CREW ATTEMPTED TO MOVE THE THROTTLE IN EPR AND N1 MODE AND THERE WAS NO REACTION FROM THE LT ENGINE.  EICAS MESSAGE (L FADEC FAULT) (CYAN) POSTED.  CREW REQUESTED LOWER FLIGHT LEVEL AND LEVELED OFF AT FL370. APU WAS STARTED. THEY DESCENDED FURTHER TO FL290 AND SHUTDOWN THE LT ENGINE TO ATTEMPT A START AND RUN ON THE OPPOSITE ENGINE ELECTRONIC CONTROLLER (EEC) CHANNEL TO REGAIN LT ENGINE CONTROL.  ENGINE WAS RESTARTED AND ALL LT ENGINE CONTROLS RETURNED TO NORMAL OPERATING CONDITIONS.  CREW DIVERTED, AS A PRECAUTIONARY MEASURE, IN ORDER TO HAVE THE AC EVALUATED AND REP2L72 4F4  FRTT00003NYE00061EN             
             20080521     NM  2008       5          21         CA080423004      120080416G56105893543130      WINDSCREEN                              BOEING727   727260      138408KNM  PWA   JT8   JT8D17      52049NE                              COCKPIT         BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        AB FLAME/FIRE                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA                                                                      (CAN) AFTER COCKPIT SETUP SMOKE AND FLAME WAS OBSERVED BY THE FLIGHT CREW FROM THE TOP LT CORNER OF THE R1 WINDOW.  WHEN THE R1 WINDOW HEAT WAS SELECTED OFF THE FLAME AND SMOKE CEASED. THE R1 WINDSCREEN WINDOW HEAT SYS WAS DEFERRED BY MAINT. UPON ARRIVAL AT THE DESTINATION THE R1 WINDOW WAS REPLACED AND THE R1 WINDOW HEAT CONTROLLER WAS ALSO REPLACED AS A PRECAUTION.  THE AC WAS RETURNED TO SERVICE. (TC NR 20080423004)                                                                                                                                                                                                                                                                                                          2L73 4F4  FRTA3WE    E2EA                 
             20080521     NE  2008       5          21         CA080423011      220080330G7200                ENGINE                                  CESSNA500   500CESSNA   2076602CE  PWA   JD15  JT15D1A          NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA                                                                      (CAN) THE CREW REPORTED VIBRATIONS SHORTLY AFTER TAKEOFF AND WAS ATTEMPTING TO RETURN TO POINT OF DEPARTURE. THE AC CRASHED. ALL ON BOARD WERE FATALLY INJURED.  BOTH ENGINES SHOWED INDICATIONS CHARACTERISTIC OF THE ENGINES PRODUCING LOW POWER OR WINDMILLING UNDER AIR LOADS AT THE TIME OF IMPACT. THERE WERE NO INDICATIONS OF ANY PRE-IMPACT ANOMALIES TO ANY OF THE COMPONENTS OBSERVED.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080423011)                                                                                                                                                                                                                                     1L72 4F4  F  A22CE   E25EA                
             20080521     NE  2008       5          21         CA080423012      220080417G7261                OIL SYSTEM                              AMD   FALC50FALCON2000  2730170NM  PWC   PW306 PW306C      52169NE                              ENGINE          LEAKING         W      A   UNSCHED LANDING                                                                                 KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, THE CREW NOTED OIL SMELL FOLLOWED BY VISIBLE VAPOR IN THE CABIN AIR AND OIL PRESSURE GAUGE FLUCTUATIONS. THE FLIGHT WAS DIVERTED TO AN ALTERNATE LANDING SITE. THE ENGINE WAS SHUTDOWN FOLLOWING LANDING. OIL WAS OBSERVED INSIDE THE BYPASS DUCT AND FAN STATOR.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080423012)                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA50NM   E35NE                
             20080521     EA  2008       5          21         CA080423013      220080328G7321                FUEL CONTROL                            BEECH 90    E90         1152914CE  PWA   PT6   PT6A28           EA                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH, UPON RETARDING THE POWER LEVER TO IDLE, THE ENGINE ACCELERATED TO 90 PERCENT NG WITH AN ASSOCIATED TEMPERATURE OF 800 DEGREES. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND FEATHER THE PROP. THE FUEL CONTROL WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20080423013)                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3T4  T  3A20    E4EA                 
             20080521     CE  2008       5          21         CA080423014      120080417G7500                LINE                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ENGINE          FRACTURED       W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) OPERATOR REPORTS (2) EVENTS OF POWER LOSS FOLLOWED BY ENGINE SHUT DOWN. ONE EVENT APRIL 17, 2008, THE OTHER APRIL 18, 2008. BOTH CAUSED BY FRACTURE OF THE PY LINE.  AIRCRAFT RETURNED TO SERVICE FOLLOWING 2ND REPLACEMENT OF THE PY LINE. (TC# 20080423014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA24CE   E4EA                 
             20080522     NM  2008       5          22         CA080424001      120080418G2910AE2463510E0124  FLEX LINE                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KF FLUID LOSS                FLT CONT AFFECTED                                   CRCRUISE         1                      CA                                                                      (CAN) AFTER TAKEOFF WITH GEAR RETRACTON NR 2 HYD SYS QUANTIY DROPPED TO 2 QUARTS, THE CREW ELECTED TO RETURN TO THE AIRFIELD. DURING LANDING THE NR 2 HYD ISOLATION LIGHT CAME ON AND THE AC LOST THE OB SPOILERS, AND STEERING. THE AC WAS TOWED TO THE HANGAR AND THE LEAK WAS TRACED TO THE NOSE GEAR PRESSURE LINE NEAR THE SWAGE. TT ON THIS PART IS UNDETERMINED. (TC NR 20080424001)                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080522     SO  2008       5          22         CA080424003      220080423G741410160844        BRUSHES         BENDIX      BL3492205   CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF32C3AF32C93    GL  MAGNETO         MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       363                                                            (CAN) LT ENGINE REPORTED DIFFICULT TO START. MAGNETO REMOVED AND BENCH TESTED, FOUND TO HAVE LOW AND INCONSISTENT OUTPUT. MAGNETO DISASSEMBLED FOR INSP AND FOUND CARBON BRUSH ASSY NOT INSTALLED IN DISTRIBUTOR GEAR. NO EVIDENCE OF BRUSH OR SPRING REMNANTS FOUND INSIDE OF MAGNETO. MAGNETO RE-ASSEMBLED WITH NEW BRUSH, BENCH TESTED IAW BENDIX OVERHAUL MANUAL X42000-1. MAGNETO RE-INSTALLED ON ENGINE, ENGINE STARTS NORMAL. (TC NR 20080424003)                                                                                                                                                                                                                                                                                        1L72 3O3  O  3A25    E8CE    5  CP22EA    
             20080522     NE  2008       5          22         CA080424005      220080423G742090591507        IGNITION LEAD                           CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              LT ENGINE       DEFECTIVE       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1971                                                           (CAN) DURING ROUTINE INSP OF THE ENGINE, THE LT ENG OB IGNITER LEAD WAS FOUND DEFECTIVE. UPON REMOVAL OF IGNITER FROM LEAD, FOUND THE LEAD`S CENTER ELECTRICAL POST LOOSE AT IGNITER END.  APPROX ONE INCH OF THE CENTER POST OF LEAD FEEL OUT WITH CERAMIC INSULATOR AND NOTED BURNING MARKS AROUND WHERE THE CENTER CORE HAD BROKEN AWAY.  LEAD REPLACED WITH NEW UNIT. (TC NR 20080424005)                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA22CE   E00053EN             
             20080522     NM  2008       5          22         CA080425002      120080421G274032EN614         WARNING SWITCH                          BOEING727   72722C      138400FNM  PWA   JT8   JT8D7B      52053NE                              LOWER STABILIZERCLOSED          W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      (CAN) WHILE ATTEMPTING TAKEOFF, TAKEOFF WARNING INTERMITTENT, HORN SOUNDED UPON POWER LEVER ADVANCEMENT. TAKEOFF WAS ABORTED AND AC RETURNED TO BLOCKS. TROUBLESHOOTING REVEALED THE LOWER HORIZONTAL STABILIZER TAKEOFF WARNING SWITCH WAS NOT CONTACTING ACTUATING CAM. THE SWITCH WAS FOUND TO BE HOLDING CLOSED DUE TO BINDING OF THE ROTARY SHAFT. FURTHER EXAMINATION REVEALED SHAFT HAD BEEN BENT. IT IS SPECULATED THAT ICE MAY HAVE BUILD UP ON THE SWITCH ACTUATION (STABILIZER) CAM. THE AC HAD JUST BEEN DE-ICED DUE TO SNOW ACCUMULATION PRIOR TO TAKEOFF ATTEMPT. THE SWITCH WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080425002)                                                                                     2L73 4F4  F  A3WE    E2EA                 
             20080522     NM  2008       5          22         CA080425006      120080425G5311654653969       FRAME                                   BOEING737   737490      1384715NM                                                               BS 616          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) VISUAL INSPECTION FOUND THAT INNER FRAME CHORD AT BS 616, RT, WL 200 AT STUB BEAM TO BE CRACKED. (TC NR 20080425006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
             20080522     NM  2008       5          22         CA080426001      120080423G8120310440001       TURBOCHARGER                            DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 1 ENGINE     LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA       4484718251                                                     (CAN) AFTER TAKEOFF, CREW HAD LOW OIL PRESSURE INDICATION ON THE NR1 ENGINE, CREW DID PRECAUTIONARY ENGINE SHUTDOWN AND ADVISED THEY WERE RETURNING. FLIGHT LANDED WITHOUT INCIDENT. MAINT INSPECTED THE ENGINE AND FOUND OIL COMING OUT OF LP OUTLET AND COVERING TOP OF THE ENGINE, ALSO FOUND SEAL DAMAGE . THE ENGINE WAS CLEANED, GROUND RUNS WERE C/O AT MAX POWER FOR 30 MIN TO SEE IF ANY SMOKE SMELL TO SHOW CONTAMINATED DUCTING AND TO SEE IF OIL IS STILL COMING OUT. LEAK FROM COMPRESSOR FOUND TO BE BEYOND LIMITS, ENGINE CHANGE TO BE C/O. TEARDOWN REPORT TO FOLLOW WHEN AVAILABLE. (TC NR 20080426001)                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080522     NM  2008       5          22         CA080428001      120080424G2761                CASE            SMITHSIND               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ACTUATOR        RUPTURED        W      D   RETURN TO BLOCK                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       49425                                                          (CAN) WHEN TAXING INTO POSITION FOR TAKEOFF, THE CREW RECEIVED A NR1 HYD ISO VALVE AND A ROLL SPLR IB HYD CAUTION LIGHTS. THE AC RETURNED TO GATE AND A HYD LEAK WAS OBSERVED AT THE RT WING. FURTHER INVESTIGATION REVEALED THAT THE RT IB SPOILER ACTUATOR CASING HAD RUPTURED AND CAUSED THE LEAK. THE ACTUATOR WAS REPLACED, ADJUSTED, LEAK CHECKED AND TESTED SERVICEABLE. THE AC WAS RELEASED AND RETURNED INTO SERVICE.  TSR: 1657:43 CSR: 1678 (TC NR 20080428001)                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20080522     EA  2008       5          22         CA080428002      220080425G853005K21104        CYLINDER HEAD                           MOONEYM20   M20C        5870208SW  LYC   O360  O360A1D     41514EA  MCAULY2D34C 2D34C53     GL  ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA            440                                                       (CAN) ON TAKEOFF PILOT FELT SLIGHT VIBRATION THROUGH RUDDER PEDALS. AFTER GETTING TO HIS CRUISE LEVEL THE VIBRATION GOT WORSE. HE RETURNED TO THE AIRPORT, AC WAS BROUGHT INTO MAINT SHOP AND COWLING WAS REMOVED. COMPRESSION TEST WAS COMPLETED AND IT WAS FOUND THAT NR3 CYL NO COMPRESSION. CYL WAS REMOVED FROM ENGINE. FOUND THAT THERE WAS A HOLE BURNED UNDER THE EXHAUST VALVE SEAT AND THERE WAS A PART OF THE EXHAUST VALVE MISSING. RECORDS INDICATE THAT AT ENGINE OVERHAUL THE EXHAUST VALVES AND SEATS WERE REPLACED. AME WONDERS IF WHEN THEY CHANGED THE SEAT THAT THEY MAY HAVE CRACKED THE CYL ALLOWING THE EXHAUST GASES TO BURN THROUGH THE CYL UNDER THE SEAT. (TC NR 20080428002)                                        1L71 3O3  O  2A3     E286    5  CP7EA     
             20080522     NM  2008       5          22         CA080428005      120080421G324629685           BEARING                                 BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R320  CR3204123F1 GL  WHEEL ASSY      FAILED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA            238                                                       (CAN) DURING TAXI FOR DEPARTURE, THE AC FOLLOWING THE SUBJECT S/N 4168 AC, REPORTED (SMOKE AND FIRE) FROM THE RT GEAR. THE F/A CONFIRMED. THE AC STOPPED AND PASSENGERS WERE EVACUATED ON THE TAXIWAY. INSP BY MAINT DETERMINED THE CAUSE TO BE A WHEEL BEARING FAILURE. THE WHEEL WAS REMOVED AND THE AC WAS TOWED TO THE HANGER.  MAINT REPLACED THE MAIN WHEEL ASSY AND THE AC RETURNED TO SERVICE. (TC NR 20080428005)                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN6  CP5NE     
             20081105     EU  2008       11         5          CA080507004      120080430G6420                FORK                                    BOLKMS117   BK117B2     5626013EU  LYC   LTS101LTS101750B1 41560NE                              TAIL ROTOR      BINDING         W      CR  ABORTED TAKEOFF         AUTOROTATION                                                            F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       65                                                             (CAN) ACFT WAS UNDERGOING A TEST FLIGHT FOR RADAR ALTIMETER TROUBLESHOOTING. 5 MINUTES INTO CRUISE FLIGHT, A SUDDEN VIBRATION WAS INDUCED INTO AIRFRAME AND ALL FLIGHT CONTROLS. PILOT IMMEDIATELY RETURNED TO BASE FOR AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPON INSP OF ACFT, IT WAS FOUND THAT 1 TAIL ROTOR MOUNTING FORK WAS BINDING WHILE ATTEMPTING TO FEATHER BLADE. IT WAS ALSO NOTED THIS BLADE HAD NO AVAILABLE MOVEMENT IN THE FLAPPING AXIS. REMOVAL OF TAIL ROTOR INNER SLEEVE ASSY. REVEALED 1 OUTER BUSHING WAS PROTRUDING BEYOND THE INNER SLEEVE BY 1.80MM. INSPECTION OF THE MOUNTING FORK ALSO INDICATED ABRASION MARKS ON THE INSIIDE WHERE THE DISLODGED BUSHING HAD COME INTO CONTACT. SUSPECT ACFT VIBRATION A RESULT1G72 3U3  UNCH13EU   E5NE10               
             20081105     EU  2008       11         5          CA080508007      120080506G5610350A25904320    WINDSHIELD                              UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B1   60056NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1943 1943                                                      (CAN) DURING INSP, A CRACK WAS FOUND IN THE UPPER LT CORNER OF THE PILOTS WINSHIELD. WINDSHIED HAS BEEN REPLACED. THIS IS THE 4TH WINDOW REPLACED ON THIS ACFT IN 1943 HRS. IAW CONVERSATIONS WITH THE MFR THE THICKNESS OF THE WINDOWS WILL BE INCREASED IN THE FUTURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 3U3  U  H9EU    E00054EN             
             20081105     WP  2008       11         5          CA080508020      120080428G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       392                                                            (CAN) ON START ACFT STARTER GEN DID NOT ENGAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
             20081105     NM  2008       11         5          CA080510002      120080102G6220                BEARING         ROBSIN                  ROBSINR22   R22BETAII   7640110NM                                                               M/R HEAD        WORN            W      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              ININSP/MAINT     1                      CA       2169                                                           (CAN) PILOT REPORTED A LATERAL VIBRATION HAD BEEN PROGRESSIVELY GETTING WORSE OVER THE PAST WEEK. UPON VISUAL INSP OF THE MAIN ROTOR HEAD THERE WAS A BLACK PASTE (SMOKING) AROUND ONE OF THE TEETER HINGE BEARINGS. AFTER REMOVING MAIN ROTOR HEAR IT WAS FOUND THAT THE THRUST WASHER HAD BEEN CHAFING THE OTBD FACE OF THE BEARING.  THE MAIN ROTOR HEAD WAS REMOVED AND REPLACED WITH A SERVICABLE HEAD. (TC NR 20080510002)                                                                                                                                                                                                                                                                                                                1G71 3O      H10WE                        
             20081105     EU  2008       11         5          CA080513007      120080506G6320332A3210073P    TRANSMISSION                            SNIAS AS332 AS332L      8680809EU  TMECA MAKILAMAKILA1A    60040EU                              MAIN ROTOR      MAKING METAL    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA            2581                                                      (CAN) TRANSMISSION CHIP LIGHT ILLUMINATION. FERROUS METAL CHIPS, WHISKERS AND FLAKES FOUND IN FILTER AND SUMP AND ON CHIP DETECTOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2G72 4U4  U  H4EU    E12NE                
             20081105     WP  2008       11         5          CA080513008      120080506G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              HYDRAULIC SYS   LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1064                                                           (CAN) DURING INSPECTION FOUND THE LT FWD SERVO LEAKING. (TC NR 20080513008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081105     WP  2008       11         5          CA080514007      120080508G6510                SHAFT                                   ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              COOLING FAN     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       473                                                            (CAN) ON POST FLIGHT THE COOLING FAN WAS FOUND SPUN ON THE LOWER BEARING AND SHAFT ASSY. (ALIGNMENT MARK MISALIGNED) (TC NR 20080514007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   E295                 
             20081105     SW  2008       11         5          CA080515002      120080515G6710                CYCLIC CONTROL                          BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                                              OBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARANCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC FLIGHT CONTROL. INCLUDED WITH THIS REPORT IS A DOCUMENT WITH SOME PRELIMIARY APPROXIMATE VALUES AND PICTURES OF THE CLEARANCE AND INTERFERANCE THAT EXISTS.  INSTALLATION OF THE SEAT KIT AS IAW AAL-292-035-001, UNDER STC APPROVAL NR SH 06-31                                                                                                                                                                                                                                                 1G71 4U4  U  H4SW    E22EA                
             20081105     SW  2008       11         5          CA080516003      120080513G6520212040004103    GEARBOX                                 BELL  412   412EP       1182205SW  PWA   PT6T  PT6T3       52045EA                              TAIL ROTOR      LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    LDLANDING        1                      CA       24                                                             (CAN) 90 DEGREES, GEARBOX STARTED LEAKING AFTER 7.8 HOURS OF FLIGHT. UPON LANDING (TOTAL FLIGHT TIME OF 24.1 HOURS ON THE HOURMETER),THE OIL LEVEL WAS CHECKED IN THE 90 DEGREE AND FOUND TO BE EMPTY, WITH OIL SPLASHED ALL OVER THE GEARBOX. THE GEARBOX WAS FILLED WITH OIL TO THE NORMAL LEVEL AND THE ACFT WAS HOVERED FOR HALF AN HOUR AND CHECKED FOR LEAK, WHICH WAS CONFIRMED. THE OIL WAS LEAKING FROM THE PITCH CHANGE MECHANISM. THE OIL FILLER CAP WAS CHECKED FOR BLOCKAGE BUT WAS FOUND OK.                                                                                                                                                                                                                                      1G72 4U4  U  H4SW    E22EA                
             20081105     EU  2008       11         5          CA080516013      120080515G6220350A37116200    STOP                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              MAIN ROTOR      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7162                                                           (CAN) SUPPORT WAS FOUND BROKEN DURING THE AFTER LAST FLIGHT INSPECTION BY THE PILOT. NO SIGN OF FLIGHT CONTROL PROBLEM, VIBRATION OR NOISE WAS NOTICED. WORST CASE SCENARIO, IF THE DROOP RING GOT STUCK BETWEEN ONE BLADE AND THE MAST, IT COULD BE FATAL SINCE ONLY (2) OUT OF (3) WAS KEEPING THE RING CENTERED. (TC NR 20080516013)                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H9EU    E19EU                
             20081105     SW  2008       11         5          CA080521002      120080513G6410                BEARING                                 BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              T/R BLADE       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1421 1421                                                      (CAN) DURING THE 100 HR INSP A SMALL CRACK WAS FOUND ON THE INBD FEATHERING BEARING ON ONE OF THE TAIL ROTOR BLADES. CRACK WAS NOTICED AS A BLACK LINE AT THE TOP OF THE BEARING.  THIS IS A CRACK THAT WAS QUITE COMMON 10-15 YEARS AGO AND SEEMS TO HAVE RESURFACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H2SW    E1GL                 
             20081105     SW  2008       11         5          CA080521007      120080516G6310206040270       CLUTCH                                  BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              FREEWHEEL UNIT  MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1421                                                           (CAN) NOISE FROM FREEWHEEL ON SPOOLDOWN, NO INDICATIONS ON CHIP PLUG. REMOVED FREEWHEEL ASSY AND FOUND CLUTCH NOT FULLY RELEASING. REPLACED FREEWHEEL ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H2SW    E4CE                 
             20081105     SW  2008       11         5          CA080523002      120080522G6220AN17420         BOLT                                    BELL  205   205A1       1181414SW  LYC   T53   T5317BLYC   41616NE                              STAB BAR DAMPER BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE PERFORMING ADI, AME DISCOVERED THAT A STAB BAR DAMPER TUBE ASSY P/N: 204-010-925-009 AND A DAMPER LEVER P/N: 212-010-301-001 WERE MISSING. IT APPEARS THAT THE TUBE ASSY UPPER BOLT P/N: AN174-20 BROKE OFF FIRST AND WAS THE CONTRIBUTING FACTOR OF THE DAMAGE.  THE REMAINS OF SUBJECT BOLT (NUT WASHER AND SHANK WILL BE SENT FOR INVESTIGATION/ANALYSIS FOR POSSIBLE METAL FATIGUE AND/OR CORROSION. (REMAINS OF SUBJECT BOLT WERE STILL IN STAB BAR FRAME, INBOARD SIDE)  STAB BAR DAMPER P/N: 204-010-937-009 WILL BE REPLACED AS A PRECAUTIONARY MEASURE AND SENT FOR INSVESTIGATION AS WELL FOR A POSSIBLE INTERNAL FAILURE/SEIZURE WHICH MIGHT HAVE CONTRIBUTED TO SUBJECT BOLT FAILURE.  STAB BAR DAMPER TUBE RIGGING FOR 1G71 4U4  U  H1SW    E17EA                
             20081105         2008       11         5          CA080523005      420080516G2311TK760HG         TRANSCEIVER                             SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              UHF SYSTEM      INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RADIO WOULD NOT TRANSMIT, REMOVED AND INSTALLED SERVICABLE RADIO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  UNCH9EU    E19EU                
             20081105     WP  2008       11         5          CA080523006      120080518G2432RG2415          BATTERY                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MASTER          LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       73                                                             (CAN) DURING DI FOUND THE BATTERY LEAKING, REPLACED WITH A NEW ONE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081105     GL  2008       11         5          CA080527002      220080521G723023057142        STATOR          ALLSN                   BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              6TH STAGE       MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            3486                                                      (CAN) COMPRESSOR ASSY WAS REMOVED FOR O/H, AT WHICH TIME IT WAS NOTED THE 6TH STAGE STATOR BAND WAS MISSING ONE BLADE, WITH IMPACT DAMAGE NOTED ON OTHER BLADES ALSO IN THE 6TH BAND. NO DAMAGE NOTED FWD OF 6 TH STAGE. BURNER CAN REMOVED AND TURBINE INSPECTED FOR FOD, BUT NONE WAS FOUND. IT DID NOT APPEAR THAT THE STATOR WENT THROUGH THE ENGINE, HOWEVER, AT THIS TIME, WE WERE UNABLE TO LOCATE THE DEPARTED BLADE. THE CRACK APPEARS RECENT, AND IT IS BELIEVED THE BLADE CRACKED IN THE LAST 100 HOURS OF OPERATION (TC NR 20080527002)                                                                                                                                                                                             1G71 3U3  U  H2SW    E4CE                 
             20081105     SW  2008       11         5          CA080528003      120080523G5302206032400027S   RING            BELL                    BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              TAIL BOOM       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK FOUND ON TAIL BOOM RING DURING ROUTINE INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H2SW    E1GL                 
             20081105     SW  2008       11         5          CA080528004      120080523G5300206031337003    FITTING                                 BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                                              CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK DETECTED ON FITTING DURING ROUTINE INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E1GL                 
             20081105     SW  2008       11         5          CA080528007      120080525G5100427065125111    SHROUD                                  BELL  427   427         1182207SW  PWC   PW207 PW207D           NE                              FUSELAGE        CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3800                                                           (CAN) OPERATOR REPORTED A MAIN ROTOR TRANSMISSION OIL LINE FAILURE. INSP REVEALED CHAFING DAMAGE TO THE OIL-LINE SHROUD ASSY FROM THE FIREWALL CLOSEOUT METAL EDGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  R00001RCE42NE                
             20081105         2008       11         5          CA080528010      420080417G830023068295        GEARSHAFT       ALLSN                   SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              GEARBOX         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE GEARBOX WAS RECEIVED FOR OVERHAUL.  A CRACK WAS FOUND DURING THE MPI PROCESS AT THE REPAIR FACILITY. THERE ARE (2) THROUGH CRACKS IN THE REAR SEAL JOURNAL AREA OF THE POWER TAKEOFF GEARSHAFT.  THE POWER TAKEOFF (PTO) GEAR IS SN CG119988. (TC NR 20080528010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U3  U  H1NE    E1GL                 
             20081105     WP  2008       11         5          CA080528014      120080522G2822D8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       609                                                            (CAN) AUX FUEL PUMP UNSERVICEABLE, CHANGED OUT FUEL PUMP WITH A SERVICABLE ONE. (TC NR 20080528014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081105     NE  2008       11         5          CA080530001      120080529G6730S156520421041   SERVO                                   SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              MAIN ROTOR      LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4694 1156                                                      (CAN) DURING A POST-FLIGHT INSP, MECHANIC FOUND MOVEMENT BETWEEN THE FORK AND PISTON. THE PRIMARY SERVO WAS REPLACED.  AFTER DISASSEMBLY AT REPAIR STATION, IT WAS DISCOVERED THAT THE MOVEMENT WAS CAUSED BY THE BREAKDOWN OF A LAMINATED REPAIR SHIM INSTALLED BETWEEN THE FORK AND PISTON ROD, CAUSING THE LOSS OF TORQUE BETWEEN THE SERVO FORK AND PISTON ROD.  SUBMITTING THIS SDR IAW OUR REPAIR STATION CANADIAN SUPPLEMENT.  AN ASB 64B29-8 WAS RELEASED BY THE MFG, ON MAY 24, 2008 (TC NR 20080530001)                                                                                                                                                                                                                               2G72 4U4  U  H4EA    E15EA                
             20081106     EU  2008       11         6          CA080530003      120080528G6730SC5083          SERVO                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              FLT CONTROLS    WORN            W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             HOHOVERING       1                      CA       2895 2895                                                      (CAN) STIFF FLIGHT CONTROLS IN ALL RANGE OF TRAVEL, IN HOVER, CRUISE, LANDING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
             20081229     NE  2008       12         29         CA080601001      220080521G720070BM035420      MODULE                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          NOISY           W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       2955 2955                                                      (CAN) SQEALING NOISE COMING FROM ENGINE.  SHUTDOWN AFTER FLIGHT, SUSPECT TURBINE BLADE RUB.  MODULE 2 AND MODULE 3 REMOVED AND SENT TO MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E19EU                
             20081106         2008       11         6          CA080602005      120080516G78103031988         EXHAUST DUCT                                                               PWA   PT6   PT6A27      52043EA                              ENGINE          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       135771220                                                      (CAN) DAMAGED EXHAUST DUCT, PRIMARY FAILURE WAS TO THE INNER CONE OF THE EXHAUST DUCT, APPEARED TO CRACK AT NR 3 BEARING END AND EVENTUALLY DAMAGED THE T/E OF THE PT ROTOR BLADES. (TC NR 20080602005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                4  T          E4EA                 
             20081229     GL  2008       12         29         CA080603005      220080602G7314                PUMP                                    HUGHES369   369E        4470707WP  ALLSN 250C  250C20R2         GL                              FUEL            MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) REINFORCED PAPER WIPERS LEFT IN THE FUEL TANK AFTER WORK CARRIED OUT.  DURING A 300 HOUR INSP, THERE WAS SIGNIFICANT FUZZ LIKE DEBRIS FOUND IN THE ENGINE DRIVEN FUEL PUMP FILTER THAT WAS A BLUISH COLOR.   WHEN PICKING UP THE HELICOPTER AT THE SERVICE CTR WHERE THE ACFT WAS DISASSEMBLED, INSPECTED, PAINTED AND REASSEMBLED, USED ONE OF THEIR SHOP TOWELS DURING THE ACCEPTANCE INSP.  CALLED THE SERVICE CTR TO CONFIRM THAT THEY WERE USING THIS TYPE OF WIPER. THAT WAS VERIFIED AS CORRECT. THE FUEL CELL WAS OPENED UP AND A LARGE INTACT WIPER WAS FOUND OVER THE START FUEL PUMP. A SECOND .5 PIECE WAS RECOVERED FROM THE FUEL CELL INTERCONNECT AREA. AN SMS REPORT WAS PREPARED AND OUR INTERNAL SAFETY TEAM IS NOW DOIN1G71 3U3  U  H3WE    E4CE                 
             20081106         2008       11         6          CA080603006      120080528G574400100018273     HINGE BRACKET                                                                                                                           RT WING         WORN            W      I   CABIN DEPRESSURIZATION                                                                          O  OTHER                                                                         ININSP/MAINT     1                      CA       1191                                                           (CAN) REAR SPAR, RT LOWER WING AILERON, HINGE BRACKET INNER OUTER SHELL BECOMING LOOSE IN BEARING (REPLACED WITH NEW) (TC NR 20080603006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 
             20081106     CE  2008       11         6          CA080604005      120080530G29104529101067001   LINE                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              HYDRAULIC SYS   CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       2614                                                           (CAN) DURING CRUISE, THE ACFT EXPERIENCED A HYDRAULIC FAILURE. THE CREW DECLARED AN EMERGENCY, LANDING WITHOUT FLAPS. INVESTIGATION REVEALED A KINK IN A HYDRAULIC SUPPLY LINE IN THE PYLON AREA OF THE LT ENGINE. A CRACK HAD FORMED IN THE KINKED AREA AND THE FLUID WAS RELEASED FROM THE PRESSURIZED LINE.                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTT00008WIE6WE                 
             20081106     SW  2008       11         6          CA080604011      120080528G5340                ATTACH FITTING                          BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              LIFT LINK       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEAM IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 4U4  U  H1SW    E17EA                
             20081106     NE  2008       11         6          CA080604013      220080603G7200                ENGINE                                  CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ACFT TOOKOFF AND ENGINE FLAMED OUT AT 41000 FT, ENGINE RESTARTED AT 25 000 FT AND LANDED SAFELY. ENG MFG WAS CALLED AND OPERATOR INSTRUCTED TO DO POWER ASSURANCE.  AT THE TIME ARCRAFT WAS AT IMC SOME 17NM OFF TRACK DIVERTING AROUND SOME MODERATE INTENSITY RADAR RETURNS.  RADAR PICTURE GAVE NO CAUSE FOR CONCERN WITH THE PATH WHICH WAS CHOSEN AND INDICATED THAT ACFT WAS WELL CLEAR OF THE CELLS. LIGHT TURBULENCE BEING EXPERIENCED IN CLOUD WAS NOT NOTEWORTHY AND COMMONPLACE FOR FLIGHTS IN THE REGION. HOWEVER UNEXPECTED UNPAINTED ACTIVITY WAS ENCOUNTERED AND IN CLOSE PROXIMITY TO A LIGHTENING FLASH FOLLOWED BY THE SOUND OF ICE PARTICLES IMPACTING THE ACFT, BUT THE TURBULENCE WAS STILL LIGHT. VERY SHORTLY AFTER2L72 4F4  FRTA21EA   E15NE                
             20081106     EA  2008       11         6          CA080604016      120080602G5280                ROD                                     CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              MLG DOOR        OUT OF RIG      W      A   UNSCHED LANDING                                                                                 ED VIBRATION/BUFFET          INFLIGHT SEPARATION                                 CLCLIMB          1                      CA                                                                      (CAN) UPON GEAR RETRACTION DURING TAKEOFF A RHYTHMIC THUMPING SOUND WAS HEARD COMING FROM THE NOSE AREA. A RETURN TO FIELD WAS REQUESTED AND AN EMERGENCY DECLARED. NO EICAS MESSAGE WAS POSTED AND NOISE STOPPED WHEN GEAR SELECTED DOWN.  LANDING DONE WITHOUT ANY ISSUE. ACFT WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER TROUBLESHOOTING NOISE SUSPECTED TO BE COMING THE NOSE LANDING GEAR DOOR FUNCTIONAL TEST PROCEDURE FTP S604-323001 R  RECHECKED FOR  -DOOR MECHANISM RIGGING PARA 5.1.2 -GEAR MANUAL RELEASE PARA5.6.4 -LANDING GEAR FUNCTIONAL CHECK PARA 5.8  MINOR ADJUSTMENT DONE TO R/H NOSE DOOR ACTUATING ROD SYS WAS CHECKED AND FOUND OK AND ACFT WAS RELEASED FOR FLIGHT TEST.          2L72 4F4  FRTA21EA   E15NE                
             20081106     SW  2008       11         6          CA080606002      120080603G6410212010750113    BLADE                                   BELL  205   205B               SW  LYC   T53   T5313B      41549NE                              TAIL ROTOR      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       573                                                            (CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING.  AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDULED FOR THE 25 HRS AME INSP PORTION OF THE AD AFTER THE DAYS FLYING.  AME INSPECTED T/R BLADES AND DETERMINED ONE BLADE TO BE UNSERVICEABLE DUE TO POSSIBLE CRACK. THE SUSPECT DEFECT IS LOCATED AT A 45 DEGREE ANGLE ON/THRU THE MAIN SPAR APROX .333 OF BLADE LENGTH OUT FROM THE ROOT. THE DEFECT IS APROX 2 INCHES IN LENGTH. T/R BLADE REPLACED WITH SERVICEABLE UNIT AND SENT FOR FURTHER INSP. THERE HAVE BEEN NO DAMAGE OR ABNORMAL INCIDENTS NOTED TO HAVE AFFECTED THE BLADE, AND THERE ARE NO INDICATIONS OF ANY IMPACT OR OTHER DAMAGE IN THE SUSPECT AREA.  WILL SEND ADDITIONAL INFO AFTER INSPECT THE BLA1G71 4U4  U  H1SW    E17EA                
             20081106     SW  2008       11         6          CA080606004      120080604G2740C200G3R         SWITCH                                  FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  STAB TRIM       INTERMITTENT    W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) LT SAS FAILED AND ALL STAB TRIM FUNCTIONS FAILED. MASTER DISCONNECT SWITCH REPLACED AND TEST FLIGHT CARRIED OUT SERVICIBLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081106     SW  2008       11         6          CA080606005      120080516G3246LM29749         BEARING                                 FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33110UG  01514WP  MCAULY4HFR344HFR34C652  NE  LH NOSE WHEEL   LACK OF LUBE    W      D   RETURN TO BLOCK                                                                                 W  INADEQUATE Q C                                                                TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI FOR DEPARTURE THE PILOT NOTICED A VIBRATION FROM THE NOSE GEAR. HE RETURNED AND MAINT FOUND LT NOSE WHEEL INNER BEARING SEAL WAS STICKING OUT FROM ITS SEAT. WHEEL BEARING WAS ALSO FOUND TO BE ROUGH TO THE (FEEL) AND WERE DRY.  NOSE WHEEL ASSY REPLACED AND CHECKS CARRIED OUT SERVICIBLE.                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081229     NE  2008       12         29         CA080606008      220080530G7321350A57147620    CONTROL LEVER                           SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              FCU             INCORRECT       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GOVERNOR LEVER P/N 350A57-1476-20 WAS FOUND ON FCU WHERE LEVER P/N 350A57-1472-20 SHOULD HAVE BEEN. UPON CONFIRMATION WITH MFG THIS WAS CONFIMED. AS THIS ACFT CAME TO US, ON B2 S/N 1685 WE ASSUMED THAT THE INSTALLATION WAS CORRECT. THE RIGGIN WAS WAY OUT AND WE COULD NOT REACH THE REQUIRED RPM. LEVER WAS REPLACED, RIGING WAS CARRIED OUT AND THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
             20081106     EU  2008       11         6          CA080608003      120080603G2752                NUT             TALLEY      1251T100    BNORM BN2   BN2A26      1520226EU  LYC   O540  O540E4C5    41532EA  HARTZLHCC2Y HCC2YK2     GL  FLAP ACTUATOR   STRIPPED        W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING A TRAINING FLIGHT, ON OVERSHOOT FROM A ABORTED LANDING, FLAPS RETRACTED UN-COMMANDED. PILOT REDUCED POWER AND WAS ABLE TO LAND STRAIGHT AHEAD ON REMAINING RUNWAY. INSPECTION FOUND THE FLAP ACTUATOR STRIPED.  ACTUATOR WAS REMOVED AND SENT FOR OVERHAUL.  OVERHAUL FACILITY REPORT THAT THE STRIPPED BRASS NUT WAS MADE OF A SOFTER THAN STANDARD MATERIAL.  THERE WAS IN EVIDENCE IN THE AVAILABLE LOGS OF THE TIME IN SERVICE SINCE NEW OR OVERHAULED. OVERHAULED ACTUATOR WAS RE-INSTALLED IN ACFT.                                                                                                                                                                                                                          1H72 3O3  O  A17EU   E295    5  CP920     
             20081106     SW  2008       11         6          CA080609004      120080603G2742DL5040M6        ACTUATOR                                SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  PITCH TRIM      UNRESPONSIVE    W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA            6486                                                      (CAN) SHORTLY AFTER DEPARTING, AND ACCELERATING THROUGH 200KTS, THE PITCH TRIM STOPPED RESPONDING. TRIM SONALERT WAS SOUNDING WHENEVER THE TRIM SWITCH WAS USED, HOWEVER THE TRIM GAUGE WAS NOT MOVING AND THE ACFT CERTAINLY WAS NOT TRIMMING. THIS WAS ATTEMPTED ON THE CAPTAIN AND F/O`S SIDE, AS WELL AS THE STANDBY TRIM SWITCH ON THE PEDESTAL. THE CREW REDUCED POWER TO MAKE CONTROLLING THE A/C EASIER AND USED THEIR KNEES TO KEEP THE ACFT LEVEL AND CONTINUED. AS THE ACFT SLOWED FOR ARRIVAL, THROUGH ABOUT 180 KTS, THE TRIM BEGAN RESPONDING AGAIN. THE ACFT LANDED NORMALLY AND MAINT WAS INFORMED.  MAINT REPLACED THE PITCH TRIM ACTUATOR AND THE PROBLEM HAS NOT REOCCURRED. THE ACTUATOR WILL BE SENT FOR REPAIR/OVERHAUL AN2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081105     SW  2008       11         5          CA080609005      120080605G750027621009        TUBE                                    SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              BLEED AIR       LEAKING         W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA            21639                                                     (CAN) THE CREW OF THE ACFT REPORTED LOW POWER FROM THE NR 1 ENGINE. DURING THE COURSE OF TROUBLESHOOTING MX SUSPECTED A BLEED AIR LEAK CAUSED BY A CRACK IN THE BELLOWS FOR THE BLEED AIR LINE. THIS FLEXIBLE JOINT IS COVERED IN A WIRE HEAT SHIELD AND UPON CUTTING AWAY THE SHIELD TO INSPECT THE BELLOWS IT WAS DISCOVERED THAT THE LEAK WAS ORIGINATING FROM THE SEAM WHERE THE BELLOWS ARE FITTED TO THE RIDGED TUBING. THIS PART WAS MANUFACTURED IN 1980 AND IS BELIEVED TO BE ORIGINAL EQUIPMENT. ANY DEFECT IN THIS AREA WOULD BE IMPOSSIBLE TO DETECT ON A VISUAL INSPECTION.                                                                                                                                                        2L72 4T4  TRTA8SW    E4WE                 
             20081106     SW  2008       11         6          CA080609006      120080531G21202784142007      DUCT                                    SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  BLEED AIR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE INSP IT WAS DISCOVERED VISUALLY THAT A BLEED AIR LINE TO THE HEAT EXCHANGER OF THE AIR CYCLE MACHINE HAD CRACKED 2 INCHES, ABOUT ONE THIRD THE CIRCUMFERENCE OF THE TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081106     EA  2008       11         6          CA080609007      120080606G2751601R590141      DETECTOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FALSE ACTIVATIONW      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA       9197 9197                                                      (CAN) ON APPROACH CREW RECEIVED `FLAPS DEGRADED` MESSAGE ON EICAS, WHEN FLAPS SELECTED TO 45DEG, FLAPS CONTINUED TO SELECTED 45DEG POSITION. AFTER LANDING WHEN SELECTING FLAPS UP, CREW RECEIVED `FLAP FAIL MESSAGE AND FLAPS REMAINED AT 43DEG. MAINT OBTAINED FAULT CODES INDICATING SKEW DETECTION ISSUE. FLAPS RESET AND ACFT FERRIED TO MAINT BASE. MAINT INSP FOUND NO OBVIOUS FAULTS AND FLAP OPERATION NORMAL. SKEW DETECTOR BOX REMOVED AND REPLACED WITH DUMMY BOX. ACFT RETURNED TO SERVICE UNDER MEL FOR FLAP SKEW DETECTION UNSERVICEABLE.                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
             20081106     EU  2008       11         6          CA080609009      120080604G575313760B462       ATTACH FITTING                          BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  FLAP SYSTEM     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRYING OUT A 7 DAY SERVICE CHECK, TECH FOUND 3 FLAP TO SLAT ATTACHEMENT CLEATS, P/N`S 137201B88, 137202B62 AND 137203B57 WERE FOUND TO BE CRACKED. THE FLAP SECTION WAS REMOVED AND A SERVICEABLE UNIT INSTALLED.  FUNCTION CHECKS CARRIED OUT WITH NO FAULTS FOUND AND THE ACFT RELEASED TO SERVICE. THIS IS A KNOWN FAULT WITH THE BAE 3112 ACFT.                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
             20081106     SW  2008       11         6          CA080610001      120080609G6230206010467105    LEVER                                   BELL  206   206B        1181511SW                                                               SWASHPLATE      MISMARKED       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) MFG HAS BEEN MADE AWARE THAT A QUANTITY OF 94 LEVER ASEMBLIES HAVE BEEN MIS-IDENTIFIED AS -107 INSTEAD OF -105 AS REQUIRED BY ENGINEERING DRAWING NOTE. -105 IS A TIME LIFED COMPONENT AND GOVERNED BY MM CHAPTER 4 , -107 IS NOT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U      H2SW                         
             20081106         2008       11         6          CA080610003      120080609G575125W181001501    SKIN                                                                                                                                    LT AILERON      DELAMINATED     W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       4411                                                           (CAN) WHILE ON DECENT THROUGH 32,000 FT ENROUTE A MUFFLED BANG WAS HEARD BY THE CREW OF THE ACFT. AFTER A REVIEW OF THE ACFT INDICATIONS AND HANDLING AND GENERAL CONDITION, IT WAS UNCERTAIN WHERE THE NOISE HAD COME FROM. IT HAD BEEN THOUGHT THAT IT MAY HAVE BEEN A CABIN SLIDING DOOR. NO PROBLEMS WERE ENCOUNTERED ON THE APPROACH OR LANDING. MAINT DURING A POST FLIGHT WALK AROUND FOUND THE LT AILERON UPPER SURFACE DELAMINATING FROM THE HONEYCOMB STRUCTURE FROM ABOUT HALFWAY OUT THE AILERON TO THE INBD EDGE. REPLACEMENT AILERON ON ORDER AND THE DAMAGED ONE WILL BE SENT FOR FURTHER INVESTIGATION.                                                                                                                                                                   
             20081106     EA  2008       11         6          CA080611001      120080524G2997M2750012MW3U00  WIRE                                    CNDAIRCL600 CL600*      1900302EA                                                               HYD SYSTEM      DAMAGED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE RUNNING ACFT HYDRAULIC SYS IN HANGAR FOR CONTROL SYS FUNCTIONAL CHECKS, AN AUDIBLE BANG WAS HEARD FROM THE BACK OF THE CABIN, ALONG WITH A FLASH. (INTERIOR IS REMOVED). CIRCUIT BREAKER FOR HYDRAULIC SYS NR1 (B161) POPPED SHORTLY AFTER THIS OCCURRENCE. UPON INVESTIGATION FOUND DAMAGE WIRE HARNESS BELOW FLOORBOARD AT FS520 BETWEEN BL19 AND BL27. WIRES AFFECTED ARE:  HYDR SYS NR1 TRIPLE TWISTED ALL ARE ARCED AND SEVERED: DB93A12WHT, DB94A12BIU, DB95A12ORN, HYDRAULIC SYS NR2 TRIPLE TWISTED INSULATION IS DAMAGED AND MELTED: DB81A12WHT, DB82A12BIU, DB83A12ORN - HYDRAULIC SYSTEM NR3 TRIPLE TWISTED SOOT ON THE WIRE INSULATION  WIRES CABLE P/N M27500-12MW3U00 IS KAPTON WIRE.                                  2L72 4F    RTA21EA                        
             20081106     SW  2008       11         6          CA080611002      120080318G6220C807382         BEARING RACE                            BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                              PUSH-PULL       FRACTURED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5059                                                           (CAN) THE PUSH-PULL CONTROL ASSY CENTER RACE FRACTURED AS A RESULT OF FATIQUE. THE FRACTURE OCCURED NEAR WHERE THE ASSY WAS LOCATED IN AN INSTALLATION-INDUCED BEND RADIUS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  UNCH2SW    E1GL                 
             20081106     SW  2008       11         6          CA080611003      120080606G2820412061634105    VENT LINE                               BELL  412   412         1182202SW                                                               FUEL SYSTEM     CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2307                                                           (CAN) FOUND RT FUEL VENT LINE P/N 412-061-634-105 HAS RUB MARK AT WL 41. LENGTH 0.700X0.100. LOCATION: RT DOOR POST PANEL. CUT MADE WITH SHARP EDGE OF BOTTOM FOOT DOOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 4U      H4SW                         
             20081106     GL  2008       11         6          CA080611005      120080609G5551BSFS159160      ATTACH BRACKET                          DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN1     52008NE                              HORIZONTAL STAB WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       692                                                            (CAN) DURING ANNUAL INSP WITH AN AOG AIR SUPPORT WING ANGLE INSTALLED MODIFICATION, MOVEMENT WAS FOUND IN THE HORIZONTAL STABILIZER FWD ATTACH POINTS. THE HORIZONTAL STABILIZER FWD ATTACH BRACKETS WERE REMOVED AND INSPECTED AND IT APPEARS THAT THE FUSELAGE FITTING WAS WEARING INTO THE HORIZONTAL STABILIZER ATTACH FITTING (PN BSFS-159/160).                                                                                                                                                                                                                                                                                                                                                                                           1H71 3R3  RRCA806    5E1                  
             20081230     NE  2008       12         30         CA080611006      220080525G72000292005220      ENGINE                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                                              MAKING METAL    W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA       8428                                                           (CAN) WHILE DOING AIRBORNE SURVEY WORK (BIRD TOWING), ENGINE CHIP LIGHT ILLUMINATED. HELICOPTER DESCENDED TO VALLEY BOTTOM AND MADE A PRECAUTIONARY LANDING.  UPON LANDING, THE ENGINE MOMENTARILY DECELLERATED AND THEN RE-ACCELERATED. ENGINE WAS SHUTDOWN AND RAPIDLY DECELERATED ACOMPANIED BY A GRINDING/RUBBING NOISE. POST FLIGHT INSPECTION REVEALED A LARGE AMOUNT OF METAL CHIPS ON THE ENGINE CHIP PLUGS.  ENGINE REMOVED AND SENT TO MFG FOR FURTHER INVESTIGATION.                                                                                                                                                                                                                                                                 1G71 3U3  U  H9EU    E19EU                
             20081106     WP  2008       11         6          CA080611007      220080610G720031080981        BEARING                                 FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33110    01514WP  MCAULY4HFR344HFR34C652  NE  ENGINE          SPALLED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            13                                                        (CAN) THE REAR TURBINE WAS FOUND WITH HEAVY SPALLING, GALLING, HEAVY SCORING AND MISSING MATERIAL OFF THE OUTER RACEWAY AND ON THE ROLLING ELEMENTS. THE BEARING HAD ONLY 12.5 HOURS SINCE NEW/CAM. THE ENGINE WAS MAKING A STRANGE GRINDING SOUND THAT WAS NOTICED BY LINE MAINT.  ANOTHER REAR TURBINE BEARING FAILED ON ENGINE P44436C INSTALLED ON AC. THE BEARING ONLY HAD 16.4 HOURS ON IT. INVESTIGATION CARRIED OUT AND BOTH BEARING WERE RECIEVED ON THE SAME PO. THE PO CAME IN WITH 4 BEARING, ANOTHER ONE DISCOVERED ROUGH TO SPIN IN INVENTORY. REMOVED REMAINING 4TH BEARING FROM OUR SYS. MFG CONTACTED IN REGARDS OT THE SITUATION POINTING TOWARDS BAD BATCH. MFG IS RESEARCHING THE PROBLEM.  ALL CONTACTED TO ASSIST IN PROBL2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081106     SW  2008       11         6          CA080611009      120080605G324631418A          BEARING SEAL                            FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  NLG WHEEL       DISPLACED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A PREFLIGHT WALK AROUND OF THE ACFT THE INNER BEARING SEAL OF THE RT NOSE WHEEL ASSY WAS NOTED TO BE DISPLACED SO THAT ONE SIDE OF THE SEAL WAS RIDING UP ON THE HUB AND THE OPPOSITE SIDE WAS IN TOWARD THE AXLE TO THE EXTENT THAT THE BEARING ROLLERS WERE VISIBLE. NOSE WHEEL ASSY REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081106     SW  2008       11         6          CA080611010      120080610G3246LM299710        BEARING RACE                            SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE3311     01514WP  MCAULY4HFR344HFR34C652  NE  NOSE WHEEL      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE INNER SEAL WAS NOTED TO BE PROTRUDING MORE THAN NORMAL. WHEEL ASSY WAS REMOVED AND THE INNER RACE WAS FOUND TO NOT BE SEATED ALL THE WAY. SERVICEABLE WHEEL ASSY WAS INSTALLED ON THE ACFT AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T3  TRTA8SW    E3WE    6  C3PNE     
             20081106     EA  2008       11         6          CA080612001      120080611G5753600143023       VANE            BOMBDR                  CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348E5A1   30062NE                              TE FLAP         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A DAILY INSPECTION, THE LT INBD FLAP VANE WAS FOUND CRACKED ON THE UPPER SURFACE. THE CRACK IS APPROXIMATELY 2 INCHES LONG. FLAP TO BE REMOVED AND SENT OUT FOR FLAP VANE REPLACEMENT. LOANER FLAP TO BE INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E00063EN             
             20081113     NE  2008       11         13         CA080612002      220080605G7200                ENGINE                                                                     PWC   PW615 PW615FA     52282NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) DURING LANDING TOUCHDOWN AND BRAKING, BOTH ENGINES REPORTEDLY INCREASED UNCOMMANDED TO FULL POWER. CREW ABORTED LANDING AND PERFORMED A GO-AROUND. DURING BASE LEG, TO CONTAIN AIRSPEED CREW SHUT DOWN RT ENGINE AND AT THIS TIME THE LT ENGINE POWER REDUCED TO FLIGHT IDLE, UNCOMMANDED WITH NO THROTTLE RESPONSE. CREW PERFORMED A LANDING WITH NO INJURES. THE ACFT SUSTAINED 2 BLOWN TIRES. ON SITE INVESTIGATION, DATA DOWNLOADS AND ANALYSIS INDICATES AN ISSUE WITH THE THROTTLE QUADRANT. THE CAS MSGS AND EVENTS REPORTED BY THE FLIGHT CREW WERE DUPLICATED DURING SIMULATION TESTING. THE NTSB HAS RETAINED THE QUADRANT FOR FURTHER INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE        4  F          E00073EN             
             20081106     EA  2008       11         6          CA080612003      120080612G2820C6PF1034105     LINE                                    DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              FUEL SYSTEM     MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 4 AND NR 6. THE INSTALLER FOUND THE TUBE ASSEMBLY TO BE .7500 INCHES TOO SHORT FOR THE LOCATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA9EA    E4EA                 
             20081106     EA  2008       11         6          CA080612004      120080612G2820C6PF103479      LINE                                    DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              FUEL SYS        MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 5 AND NR 8 AS PART OF THE MOTIVE FLOW SYS. THE INSTALLER FOUND THE TUBE ASSY TO BE ONE INCH TOO LONG FOR THE LOCATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3T4  TRTA9EA    E4EA                 
             20081106     NE  2008       11         6          CA080612005      220080612G7414                BEARING                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         LOOSE           W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       453                                                            MAG RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS A FACTORY NEW MAG. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND NONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSP AND THE MAG WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081106     NE  2008       11         6          CA080612006      220080612G7414                BEARING         BENDIX                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         LOOSE           W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       501                                                            (CAN) MAG WAS RECEIVED FOR A 500 HOUR INSP BEFORE DISASSEMBLY 0.004 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS A FACTORY NEW MAGNETO. REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND NONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSPECTION AND THE MAG WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20081106         2008       11         6          CA080612007      220080612G7414                BEARING                                                                                                                                 MAGNETO         LOOSE           W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) MAG WAS SOLD TO A CUSTOMER AS AN EXCHANGE UNIT. WHEN INSTALLING THE CUSTOMERS MAGNETO DRIVE 0.004 INCH OF END PLAY WAS NOTICED AT THE ROTOR. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THIS WAS A FACTORY REBUILT MAGNETO. THE MAG WAS REPAIRED BY PROPERLY SHIMMING THE BEARINGS AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                               
             20081113     CE  2008       11         13         CA080613004      120080605G3250AN310A          BOLT                                    CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              COCKPIT         MISINSTALLED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LEFT RUDDER PEDAL SYSTEM INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BESIDE THE RIGHT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSPECTION CARRIED OUT AFTER FINDINGS AS DESCRIBED IN SDR 20080613002 (TC# 20080613004)                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    E274                 
             20081106     CE  2008       11         6          CA080613005      120080604G2720AN310A          BOLT            CESSNA                  CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160CTM    GL  RUDDER PEDAL    MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) LT RUDDER PEDAL SYS INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BESIDE THE RT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSP CARRIED OUT AFTER FINDINGS AS DESCRIBED IN SDR 20080613002.                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
             20081106     SW  2008       11         6          CA080613007      120080605G30002719156003      TRANSDUCER                              FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP                              DE ICE SYSTEM   DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6918                                                           (CAN) PILOT REPORTED DEICE PRESSURE GAUGE UNSERVICEABLE. DURING TROUBLESHOOTING MAINT FOUND THE DEICE PRESSURE TRANSDUCER CONTAMINATED WITH WATER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA18SW   E4WE                 
             20081106     WP  2008       11         6          CA080613009      120080603G2435BC3151004       STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       824                                                            (CAN) STARTER INTERMITTENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081106     CE  2008       11         6          CA080613010      120080611G6120A3495           LOCK PLATE                              MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE33110    01514WP  HARTZLHCB4T HCB4TN5     GL  PROPELLER       WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       99   99                                                        (CAN) DURING A ROUTINE PROP INSP, IT WAS FOUND THAT THE PITCH LOCK PLATE ALLOWS THE LATCH PIN TO SLIP OFF THE EDGE AND COULD JAM THE PIN. THIS COULD PREVENT IN FIGHT ENGINE START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
             20081106     SW  2008       11         6          CA080614001      120080612G2910                LINE                                    BELL  205   205A1       1181414SW  LYC   T53   T5317BLYC   41616NE                              HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KF FLUID LOSS                FLT CONT AFFECTED                                   HOHOVERING       1                      CA                                                                      (CAN) THE PILOT WAS FLYING THE HELICOPTER WHEN THE COLLECTIVE BECAME STIFF TO MOVE. THE PILOT RELEASED THE LOAD AND NR 2 HYDR SYS HAD FAILED. THE PILOT LANDED THE ACFT. IT WAS FOUND THAT NR 2 HYD SYS HAD LOST ALL IT`S FLUID DUE TO A HYDRAULIC LINE HAD CHAFED THROUGH CREATING A HOLE. MORE DETAILS ARE COMING.                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 4U4  U  H1SW    E17EA                
             20081106     NE  2008       11         6          CA080616001      220080611G7250                TURBINE                                                                    PWA   PW120 PW123            NE                              ENGINE          OUT OF BALANCE  W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       1866710033                                                     (CAN) EI PW100 2008-059 - VIBRATIONS DURING START, IT HAS BEEN DETERMINED THAT THE POWER TURBINE WAS OUT OF BALANCE THUS CAUSING THIS EVENT. (PRE SB21737)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  T          E20NE                
             20081105     EU  2008       11         5          CA080616002      120080611G28205282412189      LINE                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE                              FUEL SYS        CORRODED        W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) MX FOUND FUEL LEAKING FROM CENTER BELLY PANEL AND DURING INVESTIGATION FOUND A CORRODED FUEL LINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE                
             20081106     CE  2008       11         6          CA080616003      120080611G261224418922        FIRE LOOP                               CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  NACELLE         LOOSE           W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       1398713987                                                     (CAN) ENGINE FIRE WARNING INDICATION CAME ON IN FLIGHT. THE ENGINE WAS REPLACED THE PREVIOUS DAY AND THE FIRE WIRE MAY HAVE BEEN DISTURBED AT THAT TIME. THE PILOT LANDED AND THE FIRE WIRE WAS REPLACED AND CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081106     EA  2008       11         6          CA080616004      120080615G2750860D10018       FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              FLAP SYSTEM     UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) FLAP FAIL CAUTION MESSAGE ON FLAP RETRACTION. FLAPS WERE SELECTED FROM 8, 0 AND THE FLAP FAIL HAPPENED WITH FLAPS NOW INDICATING 0 ON EACH SIDE. A/C LANDED OVERWEIGHT DUE TO RETURNING WITH FLAP FAIL  FDR DATA RETRIEVED AND CALCULATED LANDING VERTICAL SPEED TO BE AT MOST 300 FT/SEC. THIS IS WELL BELOW THE MAX ALLOWABLE OF 360 FT/SEC. NO HEAVY LANDING CHECK REQUIRED. FECU SHOWS THAT FECU HAS FAILED. TECH OPS ACTION PLAN FOR THE INPUT TORQUE OF THE FLAP DRIVE SYS COMPLETED. NO FAULTS FOUND. WIRING FROM FECU TO FLAP HANDLE, LT AND RT BPSU`S RANG OUT AND ALL CHECKED OK. FECU REPLACED. GROUND TESTED SERVICEABLE.                                                                                                     2L72 4F4  FRTA21EA   E15NE                
             20081106     EU  2008       11         6          CA080616005      120080611G2731Z4244170000     CONTROL CABLE                           ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA                              ELEVATOR TAB    FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3800                                                           (CAN) AFT ELEVATOR TRIM CABLE WAS DISCOVERED FRAYED DURING REGULARLY SCHEDULED MAINT. IT WAS SURMISED THAT FURTHER OPERATION OF THE TRIM SYS WOULD HAVE LED TO SYS FAILURE BEFORE THE NEXT SCHEDULED INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O0 A76EU   1E10                 
             20081106     CE  2008       11         6          CA080617001      120080610G5720                SUPPORT                                 CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              SPEED BRAKES    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE OTBD HOLE IN THE SPEED BRAKE TRUNNION SUPPORT IS ABOUT .5 HOLE MISALIGNED WITH THE HOLE IN THE RIB WHERE THE UPPER OTBD AILERON CABLE PASSES THROUGH ON BOTH THE LT AND RT WING. THE AILERON CABLES WERE WORN AND HAD WORN INTO THE AFT SIDE OF THE HOLE IN THE TRUNNION SUPPORTS. REPAIR S-550-0699/04RD WAS ISSUED TO BLEND THE TRUNNION SUPPORT AND THE AILERON CABLES WERE REPLACED.                                                                                                                                                                                                                                                                                                                                              1L72 4F4  F  A22CE   E1NE                 
             20081106     CE  2008       11         6          CA080617002      120080418G534305430161        FITTING                                 CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              NLG             BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       7960                                                           (CAN) AS THE ACFT WAS TAKING OFF, THE NOSE GEAR COLLAPSED. THE ACFT WAS INSPECTED AND THE NOSE GEAR LOWER FITTING WAS FOUND BROKEN. IT IS UNDETERMINED AT THIS TIME IF THIS WAS A RESULT OF AN UNREPORTED HARD LANDING. RETAINED THE BROKEN PART TO CARRY OUT METALLURGY TESTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    1E10                 
             20081106     NE  2008       11         6          CA080617003      220080607G8530                EXHAUST VALVE                           CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 R2800CA3    52026NE  HAMSTD43E   43E60       NE  NR 9 CYLINDER   FAILED          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA            970                                                       (CAN) DURING CRUISE, THE FLIGHT CREW HEARD THE NR1 ENGINE BACKFIRE. THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED. DURING INVESTIGATION, THE MAINT CREW DISCOVERED THE EXHAUST VALVE IN CYL NR 9 HAD DROPPED INTO THE CYL. SOME PIECES OF THE VALVE WENT OUT THE EXHAUST PIPE. THE CYL WAS REPLACED, ENG GROUND RUN  AND THE MAIN OIL SCREEN WAS INSPECTED. THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                             2H72 4R4  RRTA14EA   5E8     6  CP871     
             20081106     EU  2008       11         6          CA080617004      120080616G3040                SHAFT                                   AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              WINDSHIELD WIPERSHEARED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ACFT ARRIVED AT GATE WITH CAPTAINS WINDSHIELD WIPER ASSEMBLY MISSING. FURTHER INVESTIGATION FOUND THAT CONVERTER SPLINED SHAFT HAD SHEARED OFF CAUSING THE WIPER ASSY TO DEPART ACFT WHILE TAXIING IN FROM LANDING TO APRON. WIPER ASSY WAS FOUND IN TAXIWAY. CONVERTER ASSY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA35EU   E23EA                
             20081106     NM  2008       11         6          CA080618001      120080615G3233AS11510K0330    HOSE                                    BOEING757   75728A      1384976NM  RROYCERB211 RB211535E43754555NE                              MLG ACTUATOR    LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) LT TRUCK TILT ACTUATOR RETURN LINE FOUND LEAKING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA2NM    E12EU                
             20081230     SW  2008       12         30         CA080618002      120080616G2510AAL292030001    SEAT FRAME                              BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              COCKPIT SEAT    INTERFERENCE    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING THE INSTALLATION OF VERTICAL REFERENCE SEAT KIT, IAW STC SH06-31, IT WAS DISCOVERED THAT THE CYCLIC FLIGHT CONTROL STICK IS INTERFERED WITH DUE TO THE SEAT NOW BEING POSITIONED FURTHER FWD AND ELEVATED BECAUSE OF THE KIT INSTALLATION. AN ELEVATION OF THE INSTALLATION IS ATTACHED TO PROVIDE DETAILS OF THIS ISSUE. THE CYCLIC CONTROL STICK CONTACTS THE SEAT FRAME WHEN THE SEAT IS TILTED. THE CYCLIC CONTROL STICK IS NOT ABLE TO CONTACT THE CONTROL STOP WHEN THE SEAT IS IN THE TILTED POSITION.                                                                                                                                                                                                                      1G71 4U4  U  H4SW    E22EA                
             20081106     NE  2008       11         6          CA080618003      220080602G7261                SEAL                                                                       PWA   PT6   PT6A60      52043NE                              NR 1 BEARING    LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING ENG COMPRESSOR RECOVERY WASH, ENGINE OIL LOSS FROM NR 1 BEARING SEAL. MULTIPLE ENGINE SPOOLS ARE REQUIRED TO COMPLETE AN ENG COMPRESSOR RECOVERY WASH IAW ENG MFG. MAINT FOUND IN CARRYING OUT MULTIPLE ENGINE SPOOLS, INTERNAL ENG SCAVANGE PUMPS LOCATED IN THE AGB WERE NOT EFFICIENT ENOUGH THROUGH THE SPOOLING PROCESS AT LOW ENG SPEEDS TO SUCSESSFULLY SCAVANGE ENOUGH ENGINE OIL OUT OF THE AGB TO AVOID AN OVER FILL CONDITION OF THE AGB. SCAVANGE PUMPS ARE DESIGNED TO TAKE THE USED ENGINE OIL FROM THE AGB AND RGB AND PUMP THE OIL BACK INTO THE MAIN ENGINE OIL RESERVOIR. MAINT FOUND DURING ENGINE SPOOLING ALONE, THE PUMPS COULD NOT KEEP THE OIL AT A SAFE LEVEL IN THE AGB IN ORDER TO AVOID THE OIL TO SEEP       4  T          E4EA                 
             20081106     NM  2008       11         6          CA080618004      120080613G5210BACS12ER06K6    SCREW                                   BOEING737   737*               NM  GE    CFM56 CFM567B24        NE                              PAX DOOR ARM    MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1713417134                                                     (CAN) L1 MAIN CABIN ENTRANCE DOOR WAS FOUND TO HAVE RESTRICTED OPERATION FOR OPENING AND CLOSING UPON ARRIVAL AT THE GATE. GUIDE ARM LWR RADIUS LINK ATTACHING SCREW AND KEY WASHER WERE FOUND MISSING. PARTS REPLACED. SINCE THIS HAS OCCURRED RECENTLY ON ANOTHER ACFT IS PROCEEDING WITH A PRECAUTIONARY FLEET CAMPAIGN TO INSPECT THE L1 AND L2 DOOR HINGE ARM LINKS AND HARDWARE FOR CONDITION AND SECURITY. THIS WILL BE CARRIED OUT ON WJIS ENTIRE FLEET OF 737 NGS AND SHOULD BE COMPLETED WITHIN 90 DAYS OF THE CAMPAIGN DETAILS BEING FINALIZED.                                                                                                                                                                                     2L72 4F4  FRTA16WE   E00055EN             
             20081106     NE  2008       11         6          CA080618005      220080616G72006018T30P14      BLADE                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              ENGINE FAN      BENT            W      O   OTHER                                                                                           C  F.O.D.                                                                        NRNOT REPORTED   1                      CA                                                                      (CAN) FLIGHT INGESTED A BIRD INTO THE NR1 ENGINE ON APPROACH. MTC INSPECTED AND FOUND A BENT FAN BLADE. ACFT TAKEN OUT OF SERVICE FOR A FAN BLADE REPLACEMENT. THIS WAS REPORTED BY THE CREW PICKING UP THE ACFT FOR THE NEXT FLIGHT, AFTER THEIR WALK AROUND. BENT FAN BLADE FOUND ON THE NR 1 ENGINE AFTER EVIDENCE OF BIRD INGESTION REPORTED BY THE PILOT.  ADVISES THAT THE BIRD WENT THROUGH THE CORE. CONTAMINATION FOUND THROUGHOUT THE COMPRESSOR. COMPRESSOR WASH REQUIRED. BLADE REPLACEMENT IN PROGRESS.                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
             20081105     EA  2008       11         5          CA080618006      220080508G8530LW16740         VALVE           LYC                                                        LYC   O540  TIO540A2C   41532EA                              VALVE STEM      ELONGATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2700                                                           (CAN) VALVE STREACHED TO 6 THOU AND MANUFACTURES LIMITATION IS 2 THOU. CONCERN IS VALVE IS SODIUM FILLED AND WILL DISINTIGRATE IF THE STREACH IS BEYOND MANUFACTURES RECOMMENDATIONS. THE MAIN CONCERN IS THIS ENGINE IS ON CONDITION AND THE CYLINDERS ALL HAVE 2700 HOURS ON THEM AND IF ONE IS STREACHED THE QUESTION NOW IS ARE ALL THE VALVES STREACHED. THE POINT BEING IF YOU ARE WORKING ON AN AIRCRAFT THAT IS GOING ON CONDITION IT IS CLEAR THE VALVES NEED TO BE CHECKED BEFORE THE ENGINE GOES ON CONDITION.                                                                                                                                                                                                                              3  O          E14EA                
             20081105     EA  2008       11         5          CA080618007      220080602G8530LW16703         CYLINDER                                                                   LYC   O235  O235L2C     41505EA                              ENGINE          CRACKED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA            225                                                       (CAN) THE LOWER SPARK PLUG HOLE ON CYLINDER NR 4 HAD A CRACK, THE ACFT HAD BEEN INSPECTED ON MAY 24/08 AND THERE WAS NO APPARENT CRACKS OR ISSUES WITH THE CYLINDER, ON JUNE 2 IT WAS RUNNING ROUGH AND BROUGHT TO MX, THERE WAS FOULING OF THE PLUGS AND WHEN THE PLUG WAS REMOVED THE FINE CRACK WAS NOTED. THE OTHER CYLINDERS WERE INSPECTED AND FOUND TO BE CLEAR OF ANY CRACKS. THIS ENGINE HAD BEEN OVERHAULED 225 HOURS PREVIOUSLY AND THE CYLINDERS WERE OVERHAULED AS WELL. THE RECORDS SHOWED THAT THE CYLINDERS WERE OVERHAULED AS PER MANUFACTURERS SPECIFICATIONS. WE WILL CONTINUE TO MONITOR THE OTHER CYLINDERS AND WILL REPORT ANY FUTURE ISSUES REGARDING THESE CYLINDERS.                                                          3  O          E223                 
             20081105     EA  2008       11         5          CA080618008      220080604G7314A10014044       PUMP                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA                              FUEL SYSTEM     INOPERATIVE     W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) WHEN POWER WAS APPLIED THE PUMP WOULD OPERATE UNLESS IT WAS TAPPED WITH A HAMMER. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. WILL SUPPLY HOURS ON THE PUMP IN THE NEXT FEW DAYS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A20SO   E14EA                
             20081106     SO  2008       11         6          CA080618009      120080604G8120                BOLT            KELLY                   PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  TURBOCHARGER    MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            15                                                        (CAN) DURING INSP IT WAS DISCOVERED THAT BOTH BOLTS SECURING THE TURBO TO THE UPPER TURBO SUPPORT HAD COME OUT. THE TURBO WAS LEAKING EXHAUST GASES FROM THE SEAM BETWEEN THE TURBINE HOUSING AND THE BEARING HOUSING. WILL SUPPLY HOURS OF THE TURBO THE NEXT FEW DAYS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081106     EA  2008       11         6          CA080618010      120080602G5610NP13932212      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              COCKPIT         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RT COCKPIT SIDE WINDOW SHATTERED WHILE SITTING AT THE GATE. REMOVED AND REPLACED THE RT COCKPIT SIDE WINDOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E00063EN             
             20081106     NM  2008       11         6          CA080619001      120080618G3220                BUSHING                                 EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              NLG             MIGRATED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION, FOUND EVIDENCE OF BUSHING MIGRATED ON NLG RETRACK ACTUATOR , MAIN FITTING ASSY AND UPPER SHOCK STRUT ATTACHMENTS (PRC BROKEN).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA57NM   E00070EN             
             20081106         2008       11         6          CA080619002      420080617G2565101651303       SLIDE                                                                                                                                                   LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SLIDE UNIT`S HAVE BEEN DEVELOPING PROBLEMS WITH THE ADHESIVE HOLDING MANY OF THE SEAMS TOGETHER AS THEY AGE BEYOND THE 20 YEAR THRESHOLD. THERE HAVE BEEN SEVERAL INSTANCES WHERE SLIDE TUBES FROM UNITS MFG CIRCA 1984 HAVE RUPTURED UPON INFLATION TEST. MOST RECENTLY, A SLIDE MFG CIRCA 1986 (PN 101651-303, SN B51-325) SHOWED, UPON INFLATION TESTING, THAT MANY OF THE SEAMS HAVE BECOME COMPLETED DISBONDED IN AREAS SUCH AS THE CANOPY AS WELL AS IN BETWEEN THE MAIN UPPER AND LWR INFLATION TUBES. IT APPEARS THAT THE SLIDE UNITS, AS THEY AGE BEYOND 20 YEARS FROM DATE OF MFG, HAVE EXPONENTIALLY INCREASING FAILURE RATES AS SHOWN WHEN BROUGHT INTO THE SHOP ENVIRONMENT FOR CHECK/OVERHAUL. ONE CAN ONLY ASSUME THAT FAIL                                          
             20081105     CE  2008       11         5          CA080619003      120080618G5343AN35A           BOLT                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              TRUNNION        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CARRIED OUT VISUAL INSPECTION AS PER CAMPAIGN FOUND 4 BOLTS INSTALLED AND WASHERS AND NUTS. REMOVED HARDWARE INSTALLED NEW PARTS AS PER IPC 53-11-01 ITEM 109 AND 110. REPLACED ARM ASSY P/N 5565619-6 WITH NEW DUE DAMAGED AND NEW BOLT P/N NAS464P5LA28 DUE WORN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4F4  F  A22CE   E1NE                 
             20081106         2008       11         6          CA080619004      420080418G6122F624L           GOVERNOR                                PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  PROPELLER       MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA            6                                                         (CAN) AFTER INSTALLATION OF THE OVERHAULED GOVERNOR, THE TEST FLIGHT WAS CARRIED OUT AND THE ENGINE WAS OVER SPED. THE GOVERNOR WAS SENT BACK TO THE REPAIR FACILITY, THE FACILITY REPORTS NOTHING ABNORMAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081106         2008       11         6          CA080619005      420080619G8300310625801       BEVEL GEAR                                                                 PWA   120   PW120A           NE                              ASSY GEARBOX    MISMANUFACTURED W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) BEVEL GEAR P/N 3106258-01, S/N A0002WAB WAS FOUND TO BE NON-CONFORMING DUE TO MISSING POST PLATE BAKING OPERATION AFTER THE PART WAS SILVER PLATED. THIS PART WAS INTALLED IN ENGINE S/N 120673 WHICH WAS ALREADY SHIPPED TO THE CUSTOMER. THE CUSTOMER WAS INFORMED BY A LETTER TO RETURNED THE ENGINE WITHIN 60 HRS FLYING TIME IN ORDER TO REPLACED THE PART.                                                                                                                                                                                                                                                                                                                                                                                 4  T          E20NE                
             20081106     SO  2008       11         6          CA080619006      120080323G81204091709001      TURBOCHARGER                            PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          FAILED          W      A   UNSCHED LANDING                                                                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA            1                                                         (CAN) AN OVERHAULED ENGINE COMPLETE WITH NEW TURBOCHARGER WAS INSTALLED. AFTER THE FIRST HOUR OF THE FLIGHT THE TURBOCHARGER COMPLETELY FAILED. MAINT INSTALLED A NEW TURBOCHARGER AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081106     CE  2008       11         6          CA080619007      120080617G575350160018        FLAP TRACK                              BEECH 100   A100A              CE  PWA   PT6   PT6A28           EA  MCAULY4HFR344HFR34C762  NE  TE FLAPS        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A WALKAROUND THE PILOTS NOTICED EXCESSIVE PLAY ON THE RT OTBD FLAP AT THE INBD HINGE. THE FLAP WAS REMOVED FOR FURTHER INVESTIGATION AND THE INBD FLAP TRACK WAS FOUND TO BE CRACKED AT THE AFT END OF THE TRACK, THE CRACK WEAKEN THE TRACK ALLOWING IT TO SLIGHTLY BEND WITH THE FLIGHT LOADS. NO SECONDARY DAMAGE WAS FOUND. THE FLAP TRACK WAS REPLACED. AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                     1L72 3T4  T  A14CE   E4EA    6  C3PNE     
             20081106     EU  2008       11         6          CA080619008      120080506G2822P94B12203C      PUMP                                    SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              FUEL BOOST      INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA            221                                                       (CAN) BOOST PUMP FAILED IN FLIGHT, MOTOR STILL TURNING BUT NOT CREATING PRESSURE. SUSPECT SHEARED SHAFT OR DRIVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH9EU    E19EU                
             20081106     WP  2008       11         6          CA080620002      120080615G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       139                                                            (CAN) STARTER WOULD NOT TURN OVER THE ENGINE, TROUBLESHOOTING REVEALED THE STARTER WOULD NOT ROTATE THE STARTER GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20081106     GL  2008       11         6          CA080620004      120080618G5541                SPAR            DHAV                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FRONT SPAR WAS FOUND CRACKED AFTER THE RUDDER WAS REMOVED FOR REPLACEMENT OF UPPER HINGE BEARING. FRETTING WAS NOTICED AT BEARING BLOCK TO SPAR MOUNTING SURFACE/BEARING BLOCK WAS REMOVED AND CRACKS FROM THE (2) ATTACH HOLES WERE FOUND. 3 CRACKS FROM ONE HOLE EXTENDED BEYOND THE BEND OF THE FRONT SPAR. RUDDER REMOVED FROM SERVICE FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                    1H71 3R3  RRCA806    5E1                  
             20081106     GL  2008       11         6          CA080621001      220080611G72406870992         COMBUST CHAMBER                                                            ALLSN 250C  250C20B     03013GL                              ENGINE          CRACKED         W      K   NONE                                                                                            MJ OVER TEMP                 WARNING INDICATION                                  ININSP/MAINT     1                      CA                                                                      (CAN) ENGINE REPORTED HIGH OPERATING TEMP. ATTEMPTED POWER CHECK BUT NOTED 790 DEGREE TOT IN HOVER. ABORTED POWER CHECK UPON FURTHER VISUAL INSP FOUND RT ARM PIT CRACKED APPROX 5 INCH CRACK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         3  U          E4CE                 
             20081106     EA  2008       11         6          CA080622001      120080618G3230750005000       SELECTOR VALVE                          CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              MLG             FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) CREW TRIED (4) TIMES TO GET THE MLG DOWN. THEY USED THE EMERGENCY FREE FALL, AND THE MAINS CAME DOWN. (THE NOSE WAS ALL READY DOWN. NO EMERGENCY WAS DECLARED.) CONTACTED REPAIR STATION TO PIN THE LANDING GEAR, AND MAKE READY FOR THE FERRY FLIGHT. A/C TO FERRY FOR REPAIRS.  REMOVED AND REPLACED THE MAIN LANDING SELECTOR VALVE.                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
             20081106     NM  2008       11         6          CA080623001      120080424G325069355174        ROD END                                 BOEING737   737*               NM  PWA   JT8   JT8D17      52049NE                              STEERING TILLER WORN            W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       18425                                                          (CAN) MINOR BUT PERSISTENT VIBRATION COULD BE FELT IN THE STEERING TILLER DURING TAXI, PARTICULARLY AT HIGHER SPEEDS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E2EA                 
             20081106     CE  2008       11         6          CA080623002      120080619G3230AA5C            MOTOR                                   MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE33110    01514WP  HARTZLHCB4T HCB4TN5     GL  MLG             INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA       954  954                                                       (CAN) PILOT SELECTED GEAR DOWN THE DOOR MOTOR CIRCUIT BREAKER POPPED. MANUAL GEAR EXTENSION COMPLETED AND ACFT LANDED WITHOUT INCIDENT. MECHANIC DISPATCHED AND FOUND THE GEAR DOOR ACTUATOR/MOTOR UNSERVICEABLE. ACFT FERRIED TO MAINTENANCE BASE, DOOR ACTUATOR/MOTOR REPLACED AND GEAR SWING COMPLETED. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
             20081106     EA  2008       11         6          CA080623003      220080514G8520LW15628         SEAL                                    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  CRANKCASE       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            98                                                        (CAN) DURING 2 ROUTINE INSP OF THE ENGINE, IT WAS DISCOVERED THAT THE CRANKSEAL WAS LEAKING. A NEW SEAL WAS INSTALLED AT APPROXIMATLEY 50 HRS. THE NEXT SCHEDULED INSP CARRIED OUT AT 98 HRS REVEALED THE SEAL LEAKING AGAIN. THE ENGINE WAS STILL UNDER WARRENTY AND IT WAS DECIDED TO REMOVE THE ENGINE FROM SERVICE AND INSTALL A NEW ONE. THE ENGINE OVERHAUL FACILITY WAS REQUESTED TO PROVIDE A TEARDOWN REPORT AS A FOLLOW UP.                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081106     EA  2008       11         6          CA080623004      120080620G5200215260522       SHAFT                                   CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  DOOR            BROKEN          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       4896 4896                                                      (CAN) DURING AERIAL FIGHT FIGHTING OPERATIONS, THE PILOTS HEARD A LOUD BANG AFTER DROPPING THEIR LOAD OF WATER. THE "RT JACK READY" LIGHT WOULD NOT COME ON AS IT NORMALLY WOULD AFTER THE BOMB DOOR CYCLES AND LOCKS "CLOSED". THE PILOTS RETURNED TO BASE IAW COMPANY SOPS. MAINT FOUND THAT THE BOMB DOOR CLOSING JACK MOUNTING SPIGOT WAS SHEARED AND THAT THE ACTUATOR WAS HANGING FROM ITS HYDRAULIC LINES. NO OTHER DAMAGE WAS FOUND, THE SPIGOT WAS REPLACED, THE SYS FUNCTION-TESTED AIRWORTHY,AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                       2H72 4R3  RRTA14EA   ATC14   6  CP871     
             20081114     EA  2008       11         14         CA080623005      120080620G5240601R387271      UPLOCK                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              SERVICE DOOR    CRACKED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) PILOT REPORTED THAT THE SERVICE DOOR MESSAGE WAS DISPLAYED. MAINT WAS CALLED TO INVESTIGATE THE PROBLEM AND THEY WERE TOLD BY THE CREW THAT THE ENGINEER COULD NOT OPEN THE DOOR AND THEY START REMOVING THE DOOR LINER. ONCE REMOVED, THEY FOUND THAT THE SERVICE DOOR UP-LOCK MECHANISM HAD BROKEN COMPLETELY. BY LOOKING AT THE MATERIAL INSIDE THE CRACK IT WAS NOTICED THERE WERE SIGNS OF DIRT ACCUMULATION IN DIFFERENT AREAS MEANING THAT A CRACK DEVELOPED FOR QUITE SOME TIME.                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20081106     EA  2008       11         6          CA080623006      120080620G3070304310          HEAT TAPE                               CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              WATER LINE      BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE 96 MONTH INSPECTION ON ACFT BURNED HEAT TAPE PART NR 3043-10 AND 3043-15 WAS DISCOVERED. THIS TAPE WAS INSTALLED UNDER A DRAWING NR 34-260W011 ON THE AFT WATER SYSTEM LINES (AFT CABIN). THE SURROUNDING INSULATION AND AFFECTED PIPING WAS DEEPLY BURNED. THE BREAKER NEVER POPPED DURING THIS INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
             20081106     EU  2008       11         6          CA080623007      120080623G3030                HEATER          PILATS                  PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  PITOT TUBE      INOPERATIVE     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       7257                                                           (CAN) ACFT RETURNED WHEN PITOT STATIC HEAT FAIL LIGHT CAME ON. FOUND RT PITOT TUBE NOT HEATING, REPLACED TUBE TESTED SYSTEM AND PERFORMED LEAK TEST ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081106     EU  2008       11         6          CA080623008      120080618G53115331412041      FRAME                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17784                                                          (CAN) CORROSION WAS FOUND ON THE TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081106     EU  2008       11         6          CA080623009      120080621G53115331412041      FRAME                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14225                                                          (CAN) CORROSION FOUND ON TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081106     SW  2008       11         6          CA080623010      120080622G3260                BULB                                    GULSTM690TP 690         0141720SW  GARRTTTPE331TPE3315251K      NM                              MLG INDICATOR   INOPERATIVE     W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         APAPPROACH       1                      CA                                                                      (CAN) DISPATCHED FROM CYLB TO CYMM AT 11:10. ON DOWNWIND RT FOR 07 CYMM SELECTED GEAR DOWN BUT DID NOT GET A GEAR DOWN LIGHT FOR THE LT MAIN. GEAR APPEARED TO BE IN THE NORMAL DOWN POSITION, GEAR UNSAFE LIGHT WAS NOT ILLUMINATED, AND THE HYDRAULIC PRESSURE WAS NORMAL. MX WAS PHONED TO DISCUSS THE ISSUE, AND CONCLUDED THAT IT WAS PROBABLY A DEFECTIVE LIGHT. CYMM RADIO WAS CONTACTED TO HAVE EMERGENCY VEHICLES ALERTED. ACFT CIRCLED WEST OF CYMM UNTIL EMERGENCY VEHICLES ARRIVED AND THEN PROCEEDED TO LAND WITH NO FURTHER PROBLEMS. AFTER LANDING IT WAS DETERMINED THAT THE LT GEAR LIGHT BULB WAS BURNED OUT.  LT MAIN GEAR LIGHT BULB REPLACED.                                                                              1H72 3T4  T  2A4     E2WE                 
             20081106         2008       11         6          CA080623011      420080623G2562                G SWITCH        DORNEMARGLN                                                                                                             ELT             FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN PERFORMING THE ANNUAL TESTS REQUIRED BY CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. ELT REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
             20081106         2008       11         6          CA080623012      420080620G61224U1827          GOVERNOR                                CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE  HAMSTD43E   43E60       NE  PROPELLER       FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA            33                                                        (CAN) ON APPROACH TO TALBOT LAKE FOR A SCOOP (WATER PICK UP) THE RT ENGINE BEGAN TO SPEED UP UNCOMMANDED TO 3000 RPM AND AN OVERSHOOT WAS INITIATED. THE RPM LEVER WAS RETARDED IN AN ATTEMPT TO CONTROL THE RPM WITH NO RESPONSE. THE PROP OVERSPEED PROCEDURE WAS FOLLOWED AND THE ENGINE RESPONDED TO THROTTLE REDUCTION BUT WOULD NOT FEATHER. THE ENGINE AND PROP REMAINED STABLE AND LANDING WAS UNEVENTFUL. THE PROP GOVERNOR WAS CHANGED AND THE ACFT WAS RETURNED TO SERVICE. DUE TO THE TSO AND TYPE OF FAILURE THIS GOVERNOR WILL BE SENT OUT FOR A TEAR DOWN REPORT. A FOLLOW UP REPORT WILL BE GENERATED UPON RECEIPT OF THE TEAR DOWN REPORT.                                                                                     2H72 4R4  RRTA14EA   E231    6  CP871     
             20081106     EA  2008       11         6          CA080624001      220080624G7230                COMPRESSOR                                                                 PWA   PT6   PT6A21      52043EA                              ENGINE          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) EIR PT6A 2008-040 OVER TEMPERATURE EVENT OCCURRED AS A RESULT OF COMPRESSOR FAILURE DUE TO LOSS OF STACK RIGIDITY, WHICH RESULTED FROM A LOSS OF STRETCH ON THE COMPRESSOR TIE RODS (P/N 3019371). COMPRESSOR SELF-DESTRUCTED. TIE RODS WERE INSTALLED "NEW" AT PRIOR OVERHAUL (TSO 465 HOURS).  TIE RODS WERE FOUND TO BE WITHIN ALLOWABLE HARDNESS RANGE.  ENGINE WAS PREVIOUSLY A PT6A-11 MODEL BUT CONVERTED TO A PT6A-21 VIA TCCA APPROVAL IN SEPT/04.                                                                                                                                                                                                                                                                                      4  T          E4EA                 
             20081106     WP  2008       11         6          CA080624002      120080610G5345D2010104        ARM             DART                    ROBSINR44   R44         7640120WP                                                               MIRROR          SEPARATED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DART HAS RECEIVED REPORTS FROM CUSTOMERS THAT UNDER CERTAIN CIRCUMSTANCES ON D044-715-011 AND D022-716-011 CARGO MIRROR INSTALLATIONS AT CHG001 THE D2010-104 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM THE ASSEMBLY. DART SERVICE BULLETIN SB08-2 IS BEING ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED THESE ASSEMBLIES FROM DART.                                                                                                                                                                                                                                                                                                                                                                        1G71 3O      H11NM                        
             20081106     NM  2008       11         6          CA080624003      120080624G7933                INDICATOR                               BOEING727   727225      1384077NM  PWA   JT8   JT8D15      52051NE                              OIL TEMP        MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) ON TAKE-OFF/CLIMB OUT, THE NR 3 ENGINE EGT WAS 60 DEGREES HIGHER THAN ENGINES 1 AND 2. THROUGH 1000 FEET AGL THE NR 3 OIL TEMP WENT INTO THE RED BAND. A REDUCTION IN POWER FOR QUITE THRUST BROUGHT THE OIL TEMP BACK TO THE YELLOW BAND. A RESUMPTION IN POWER RESULTED IN THE OIL TEMO RETURNING TO THE RED BAND. THE ENGINE WAS SHUT DOWN AND THE ACFT RETURNED FOR LANDING.  MX REPLACED THE OIL TEMP INDICATOR AND BULB WHICH RECTIFIED THE PROBLEM.                                                                                                                                                                                                                                                                                2L73 4F4  F  A3WE    E2EA                 
             20081106     EU  2008       11         6          CA080624004      120080618G3397                WIRE                                    UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B1   60056NE                              NAV LIGHT       CHAFED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       125                                                            (CAN) THE GREEN NAV LIGHT POWER WIRE CHAFED INSIDE THE HORIZONTAL STABILIZER AND THE RESULTING SHORT CIRCUIT POPPED THE 6 AMP CIRCUIT BREAKER BUT NOT BEFORE DAMAGING THE POS LIGHT SWITCH AND THE LIGHT & ANCILLARY CONTROL UNIT (LACU).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G72 3U3  U  H9EU    E00054EN             
             20081114     CE  2008       11         14         CA080625001      120080606G29106317003136      LINE                                    CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              HYDRAULIC SYS   RUPTURED        W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       2115 2115                                                      (CAN) ACFT DEPARTED AND EXPERIENCED COMPLETE HYDR FLUID LOSS. ACFT GEAR ALTERNATE EXTENDED AND RETURNED TO AIRPORT. TROUBLESHOOTING REVEALED RUPTURED HYDR PRESSURE LINE INBD OF SERVICE QUICK CONNECT. LINE REPLACED WITH NEW, AND SYS BLED. ACFT RUN FOR 10 MIN AND ALL 3 SYS FILTERS REMOVED AND CHECKED FOR DEBRIS. NONE NOTED. FILTERS REPLACED WITH NEW IAW AMM 29-10-00. AND SYS BLED. ALL SYS INCLUDING GEAR CYCLED 40 TIMES. ACFT RUN AND SYS CHECKED SERVICEABLE. RUPTURE APPEARED TO BE A MFG FLAW THAT WAS NOT NOTICEABLE DUE TO THE HYDR LINE IDENT LABEL BEING PLACED OVER THE FLAW.                                                                                                                                              1L72 4F4  FRTA1WI    E3GL                 
             20081114     SO  2008       11         14         CA080625002      120080429G2997                CONNECTOR                               PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA  HARTZLHCE2Y HCE2YR2     GL  HYD POWERPACK   LOOSE           W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) HYDR FLUID NOTED LEAKING FROM MANUAL HYDR HAND PUMP UPON POST-TAKEOFF GEAR RETRACTION. ATTEMPT TO RE-EXTEND GEAR WITH STANDARD SYS OR MANUAL HAND PUMP FAILED. CO2 EMERGENCY DEPLOYED, GEAR EXTENSION UNSUCCESSFUL. S-PIN ON BACK OF PRIORITY VALVE REMOVED BY OTHER CREW MEMBER ONBOARD (WITH GUIDANCE FROM AME ON GROUND VIA RADIO). PIN FOUND DIFFICULT TO REMOVE, TOOLS AND CONSIDREABLE FORCE REQUIRED. GEAR IMMEDIATELY EXTENDED WITH NORMAL INDICATIONS ONCE PIN WAS REMOVED, SUCCESSFUL LANDING EXECUTED.                                                                                                                                                                                                                         1L72 3O3  O  1A10    E14EA   5  CP9EA     
             20081114     EU  2008       11         14         CA080625003      120080620G75007275031504      PIPE                                    SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F26 NE  HP BLEEDAIR     CRACKED         W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) ON TAKE OFF ROLL WITH THE CTOT ENGAGED, THE NR1 ENGINE TEMP INCREASED TO 900 DEGREES AT A TORQUE OF 60 PERCENT. THE CREW REDUCED ENGINE POWER AND AT THIS TIME THEY DID HAVE A STEADY DECREASE IN ENGINE TEMP. THE ACFT RETURNED TO THE RAMP AND MAINT WAS DISPATCHED TO INVESTIGATE THE PROBLEM. UPON OPENING THE ENGINE COWLS MAINT DISCOVERED THAT THE HP BLEED PIPE HAD CRACKED ALL THE WAY AROUND THE LOWER CLAMP CREATING A BLEED AIR LEAK. PIPE WAS REPLACED AND THE ACFT RELEASED BACK INTO SERVICE.                                                                                                                                                                                                                              2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20081114     SW  2008       11         14         CA080625004      120080618G2910                LINE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  HYD SYSTEM      CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, CREW NOTED A DROP IN HYDR PRESSURE FOLLOWED BY THE ILLUMINATION OF THE HYDR WARNING LIGHTS. THE HYDR PRESSURE WENT TO ZERO AND CREW CREW CONSULTED TO APPROPRIATE CHECKED LIST AND COMPLETED A MANUAL EXTENSION OF THE LANDING GEAR USING THE ALTERNATE EXTENSION PROCEDURES. THE ACFT LANDED WITHOUT INCIDENT. AN INSP BY MAINT DETERMINED THAT HYDR FLUID HAD BEEN LOST DUE TO A LEAK IN A HYDR TUBING IN THE LT GEAR WELL. LINE HAD A CRACK AT THE FLARE AND RESULTED IN THE LEAK. LINE WAS REPLACED WITH NEW, FUNCTION, OPERATION, AND LEAK CHECKS COMPLETED AND THE ACFT RETURNED TO SERVICE.                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081114     SW  2008       11         14         CA080625005      120080612G6210206015001119    BLADE                                   BELL  206   206L        1181522SW  ALLSN 250C  250C20R2         GL                              MAIN ROTOR      DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       753                                                            (CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H2SW    E4CE                 
             20081118     SO  2008       11         18         CA080625006      120080622G2823                SCREW                                   PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA  SNSNCH76E   76EM8S5     EA  FUEL SELECTOR   IMPROPER PART   W      D   RETURN TO BLOCK                                                                                 WS INADEQUATE Q C            AFFECT SYSTEMS                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON GROUND RUN UP, DURING NORMAL PROCEDURE, PILOT MOVED FUEL SELECTOR TO LT FROM RT AND TRY TO COME BACK TO RT. BUT HANDLE WAS SEIZED ON FUEL SELECTOR PANEL ATTACHING SCREWS. FOUND FUEL SELECTOR COVER SCREWS MAKING CONTACT WITH HANDLE AND PREVENTING MOVEMENT FROM LT TO RT POSITION. COVER REMOVED AND AREA INSPECTED AND NO DAMAGE FOUND. COVER INSTALLED WITH APPROPRIATE SCREWS AND FUNCTIONAL CHECK C/O. INSTALLATION C/O IAW MM. FUEL SELECTOR PANEL WAS REMOVED AND REINSTALLED FOR THE ELT SWITCH WIRING INSTALLATION.  GOOD FUNCTIONAL CHECK OF THE FUEL SELECTOR HAS NOT BEEN COMPLETED AFTER PANEL INSTALLATION. IT IS A GOOD THING PILOT DID A GOOD WALK AROUND AND FUEL SELECTOR CHECK.  SUGGEST TO MAKE A INDEPENDENT IN1L71 3O3  O  2A13    E286    5  NP4EA     
             20081118     CE  2008       11         18         CA080625007      120080624G53121014302851      BULKHEAD                                BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9057                                                           (CAN) MAINT WAS CARRYING OUT THE FIRST 1000 CYCLE REPETITIVE INSP AFTER  INITIAL 10000 CYCLE STRUCTURAL INSP. FOUND A 4 INCH CRACK IN THE FS 280.275 BULKHEAD WEB, ON THE LT SIDE AT THE STRINGER NR 4 CUTOUT.  THE BULKHEAD WAS CRACKED ALL THE WAY THROUGH. THICKNESS IS .040 INCH AT THIS AREA. THE CRACK ORIGINATED IN A POORLY DONE STRINGER CUTOUT.   THIS IS THE HIGH TIME IN OUR FLIGHT. IT ACCRUES APPROX 1.4 CYCLES/HOUR IN AIR AMBULANCE WORK.                                                                                                                                                                                                                                                                                       2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20081118     EA  2008       11         18         CA080625008      120080612G27426009230167      ACTUATOR                                CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF348E5A1   30062NE                              HORIZ STAB      MALFUNCTIONED   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  NRNOT REPORTED   1                      CA       869  869                                                       (CAN) DURING A FLIGHT, PILOT REPORTED A PITCH TRIM CHANNEL NR1 INOP LIGHT ON. TROUBLESHOOT THE TRIM SYS AND FOUND NR1 TRIM ACTUATOR BRAKE COIL OPEN. HORIZ STAB TRIM ACTUATOR (P/N 600-92301-67/21207-008 S/N Y2003)  WAS REPLACED WITH A REPAIRED UNIT WITH TSN 868.8 HRS, CSN 613 CYCLES.  UNIT WAS FUNCTIONAL TESTED IAW AMM 27-40-00 TRIM SYS TEST AND PASSED TEST, RETURNED ACFT TO SERVICE.  DURING OUR NEXT FLIGHT ON 17 JUNE 08, FOR ABOUT 20 MINUTES THE ACTUATOR WORKED FINE. BUT AFTER THAT THE PILOT REPORTED CHANNEL NR1 AND NR2 INOP LIGHT ON. AFTER ATTEMPTING TO RESET THE TRIM SYS BY THE AFM RECOMMENDATION AND FAILED TO RESET, THE PILOT RETURNED TO BASED WITH THE  ACTUATOR TRIM FROZEN TO THE LAST SET FLIGHT POSITION. T2L72 4F4  FRTA21AE   E00063EN             
             20081230     NE  2008       12         30         CA080626001      220080619G7314LW15473         PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       600                                                            (CAN) OIL LEAK NOTICED PRIOR TO ANNUAL INSP.  OIL WAS LEAKING OUT THE VENT LINE FROM THE FUEL PUMP.  REMOVED PUMP,  REMOVED FUEL VENT FITTING, FOUND VENT CHAMBER FULL OF ENGINE OIL.  REPLACED WITH NEW PUMP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081118     EA  2008       11         18         CA080626002      220080624G8520982C9HE2        MAIN BEARING                                                               WRIGHTR1820 982C9HE2    67020EA  HAMSTD43D   43D51       NE  NR 1 ENGINE     FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA            460                                                       (CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL TEMP ON NR1 ENGINE INCREASING. A PRECAUTIONARY SHUTDOWN WAS INITIATED ENGINE FEATHERED ACFT RETURNED AND LANDED WITH NO EVENT.  INVESTIGATION FOUND THE MAIN OIL SCREENS CONTAMINATED (SUSPECT MAIN BRG FAILURE) ENGINE IS BEING REMOVED AND REPLACEMENT ENGINE INSTALLED ACFT WILL BE RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                     4  R          E259    6  CP8879    
             20081118     WP  2008       11         18         CA080627001      120080623G243514924HTH        HOUSING                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER-GEN     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       24                                                             (CAN) STARTER WAS GRINDING ON STARTUP, UPON FURTHER INVESTIGATION AND REMOVAL OF THE STARTER IT WAS FOUND TO HAVE A CRACKED HSG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081118     NE  2008       11         18         CA080627002      220080624G7200LTS100750B      ENGINE                                  BOLKMS117   BK117B2     5626013EU  LYC   LTS101LTS101750B1 41560NE                              NR 2            FLAMED OUT      W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING NR2 ENGINE START UP PROCEDURE NR2 ENGINE FLAMED OUT. NR2 ENGINE WAS SET TO IDLE AND UPON TURNING ON NR2 GENERATOR, ENGINE SPOOLED DOWN. THERE WERE NO SURGES WITH THE INSTRUMENTS. ACFT WAS SHUTDOWN AND INSPECTED. DURING INSP NO FAULTS WERE DETECTED. A FUEL SAMPLE WAS TAKEN AND SHOWED THAT IT WAS CLEAR AND FREE OF WATER. ALL FUEL SUPPLY LINES TO THE NR2 ENGINE WERE INSPECTED AND FOUND NO FAULTS. ALL AIR LINES WERE REMOVED AND VISUALLY INSPECTED AND CAPPED LEAK CHECKED AROUND THE FLARES AND NO FAULTS WERE DETECTED. AIR LINES WERE REINSTALLED AND NR2 ENGINE ASSY WAS LEAK CHECKED IAW MM NO FAULTS DETECTED. THE NR2 ENG WAS GROUND RUNNED AND LEAK CHECKED NO FAULTS WERE FOUND. ACFT WAS RETURNED TO SERVICE 1G72 3U3  UNCH13EU   E5NE10               
             20081118         2008       11         18         CA080627003      120080625G2910MS21926J4       FITTING                                 GULSTM                             GARRTTTFE731TFE73140    29001NE                              NLG             LOOSE           W      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA       1175                                                           (CAN) ON DESCENT THE LT AND RT HYDR PUMP LIGHTS FLICKERED ON AND OFF. LOW HYD RESERVOIR ALSO ILLUMINATED. ALL SYS FUNCTIONED NORMAL AND AFTER  ACFT WAS STABILIZED ON APPROACH NO FURTHER LIGHTS WERE SEEN DURING OR AFTER LANDING. UPON A POST FLIGHT WALK AROUND HYDR FLUID WAS NOTED DOWN THE BELLY OF THE ACFT FROM NOSEWHEEL WELL BACK. RESERVOIR WAS FOUND LOW AND 1.5 LITRES OF FLUID WAS ADDED. GROUND RUNS WERE CONDUCTED AND NO LEAK WAS SEEN. MAINT WAS DISPATCHED TO THE SCENE, AFTER JACKING IT WAS FOUND THAT B-NUT ON THE 90 DEGREE FITTING FOR THE DOWNLOCK ACTUATOR HAD BACKED OFF AND THE FITTING WAS FOUND LOOSE WITH THE O-RING AND BACK UP RING DISTORTED. A NEW BACK UP RING AND O-RING WERE INSTALLED , GEAR WAS SWUNG AN       4  F          E1NM                 
             20081118     EA  2008       11         18         CA080628002      120080622G5610NP13932112      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      CA       2651                                                           (CAN)"THE FOS WINDSHIELD SHATTERED IN FLIGHT. THE OUTTER PANE IS BROKE".  REMOVED AND REPLACED THE WINDSHIELD.  WINDSHIELD, (RT) NP-139321-12 03017H4489  TSO: 2651.2/CSO: 2069.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20081119     NE  2008       11         19         CA080630001      220080522G7200                ENGINE                                  BOEING737   737217      1384464NM  PWA   JT8   JT8D17A     52049NE                              NR 2            FAILED          W      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              APAPPROACH       1                      CA                                                                      (CAN) - ON DESCENT, A "BUZZING" SOUND WAS HEARD IN THE FLIGHT DECK FOR APPROX 5-10 SEC. THIS WAS FOLLOWED BY 1 OR 2 "POPS" AND THEN A LOUD "BANG" AT WHICH TIME THE NR 2 ENGINE LOST THRUST.  NR 2 ENG TEMP CLIMBED BUT THERE WAS NO ENG OVERHEAT OR FIRE WARNING. ATC ADVISED OF EMERGENCY, AFTER LANDING, THE ACFT WAS BROUGHT TO A FULL STOP IN THE MIDDLE OF THE RUNWAY AND THE ENGINE WAS SHUT DOWN.  C.F.R. APPROACHED THE ACFT AND NOTICED "SMOKE" AND A "GLOW" FROM THE NR 2 ENGINE. THERMAL IMAGING OF THE ACFT WAS ALSO PERFORMED. THEY APPLIED FOAM TO THE NR 2 ENGINE AT THIS TIME.  CREW OPTED FOR A RAPID DEPLANEMENT THROUGH THE FORWARD L1 EXIT.  NO VISIBLE DAMAGE TO THE ENGINE. IT WAS NOTED UPON FURTHER INVESTIGATION THAT 2L72 4F4  F  A16WE   E2EA                 
             20081118     CE  2008       11         18         CA080630002      120080623G270107118505        CONTROL COLUMN                          CESSNA185   A185F       2072821CE  LYC   O540  IO540*      41532EA  MCAULYD3A34 D3A34C401   GL                  CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1692                                                           (CAN) WHILE CARRYING OUT AN ANNUAL INSP AND SEB 01-3 R1 HEAVY CORROSION WAS FOUND INTERNALLY IN CONTROL YOKE.  A/C HISTORY SHOWED FRESH WATER SUBMERSION IN 1982.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A24    1E4     5  CP47GL    
             20081118     SO  2008       11         18         CA080630003      120080425G8011149NLR          STARTER                                 PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       61                                                             (CAN) AFTER SITTING FOR 4 MONTHS, THE PILOT TRIED TO START THE ENGINE AND AFTER ONE REVOLUTION THE STARTER QUIT. THE STARTER WAS REMOVED AND REPLACED. THE ARMATURE END OF THE STARTER HSG WAS BROKEN OUT AND TWISTED, INDICATING THAT SOMETHING WAS BINDING IN THE ARMATURE AREA. STARTER SENT TO MFG FOR TEAR DOWN AND FOLLOW UP.                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081118     WP  2008       11         18         CA080630004      120080627G8010A1294BBT        SWITCH                                  CVAC  440   440         2422902WP  ALLSN 501D  501D13D     03004GL  ALLSN A6441 A6441FN606  GL  COCKPIT         SHORTED         W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NR 1 ENG STARTED TO ROTATE WHEN START ARM SWITCH SELECTED TO START POSITION, WHILE NR 1 START BUTTON NOT ENGAGED AND ATTEMPTING TO START NR2 ENG.  NR 1 ENGINE START SWITCH FOUND SHORTING INTERMITTENTLY INTERNALLY WHEN START BUTTON IS ROCKED SIDE TO SIDE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4R4  T  6A6     E282    6  CP898     
             20081107     EA  2008       11         7          CA080630005      120080629G3230555406          SELECTOR VALVE                          CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              NLG             UNSERVICEABLE   W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA       223268866                                                      (CAN) GEAR DISAGREE MSG ON GEAR DOWN SELECTION, MAINS INDICATING GREEN AND THE NOSE INDICATING WHITE. CREW CYCLED GEAR WITH SAME RESULT. THEY THEN DID AN ALTERNATE EXTENSION AND GOT THE 3 GREEN INDICATION AND LANDED WITH NO PROBLEM. (LANDING GEAR RETRACTION SYSTEM) MX T/S REVEALED THE NLG DOOR SELECTOR VALVE TO BE AT FAULT. THE SELECTOR VALVE WAS REPLACED AND GEAR SWINGS WERE C/O AND THE ACFT WAS CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
             20081110     EA  2008       11         10         CA080701003      120080630G5751                SKIN            BOMBDR                  DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE                              AILERON         DAMAGED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DEPARTING AND DURING CLIMB OUT THE ACFT WAS STRUCK BY LIGHTNING CAUSING DAMAGE TO LT AILERON TIP. DECISION WAS MADE TO RETURN THE ACFT TO AIRPORT FOR INSPECTION. INSPECTION COMPLETED PER AMM 05-50-31 AND DAMAGE WAS FOUND AT THE LT AILERON TIP AND ALL STATIC DISCHARGES. AILERON TIP REPLACED, AILERON BALANCE CHECKED AS PER AMM 57-60-71, ALL STATIC WICKS REPLACED AND CHECKED SERVICEABLE. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E20NE                
             20081110     CE  2008       11         10         CA080701004      120080627G52105043003211      HOOK            BEECH                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              PAX DOOR        OUT OF ADJUST   W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) ACFT DEPRESSURIZED AT 20000 FEET. ACFT DESCENDED TO 10000 FEET AND LANDED WITHOUT INCIDENT MX FOUND THE UPPER FORWARD DOOR HOOK WAS NOT LATCHING PROPERLY THAT CAUSED THE DOOR SEAL TO BLOW OUT CAUSING THE DECOMPRESSION. DOOR HOOK ADJUSTED AND THE DOOR SEAL WAS SECURED.                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3T4  T  A14CE   E4EA                 
             20081110     EA  2008       11         10         CA080702001      120080629G5610NP1393226       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THE FIRST OFFICERS SIDE WINDOW INNER PANE IS CRACKED. FERRIED THE PLANE.  SLC REPLACED THE FIRST OFFICERS SIDE WINDOW. OPS CHECKS GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
             20081110         2008       11         10         CA080702003      420080701G22974986            FUSE            STEC        012980201   PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6A42      52043NE                              A/P COMPUTER    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       500  500                                                       (CAN) MANUAL ELECTRIC & AUTO TRIM UNSERVICEABLE - REPLACED FUSE F2 IN ACCORDANCE WITH S-TEC SERVICE BULLETIN SB08-004.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O4  TRTA25SO   E4EA                 
             20081110     NE  2008       11         10         CA080702004      220080602G7250                TURBINE BLADES                          BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              ENGINE          DAMAGED         W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA                                                                      (CAN) DURING T/O A LOUD NOISE WAS HEARD FROM THE ENGINE AND THE T/O WAS REJECTED. THE ACFT WAS STOPPED ON THE RUNWAY AND BOTH ENGINES WERE SHUT DOWN. INSPECTION REVEALED TURBINE BLADE DAMAGE, THE ENGINE WILL BE REMOVED AND FORWARDED TO P&WC FOR INVESTIGATION AND REPAIR. THE ENGINE IS A P&WC RENTAL.   P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA24CE   E26NE                
             20081118     NE  2008       11         18         CA080702005      220080626G7250                TURBINE                                 BELL  205   205B               SW  LYC   T53   T5313B      41549NE                              ENGINE          DAMAGED         W      R   AUTOROTATION                                                                                    Y  ENGINE STOPPAGE                                                               APAPPROACH       1                      CA                                                                      (CAN) PILOT CONDUCTED TAKE-OFF SCHEDULED TO CONDUCT LONGLINE OPERATIONS. APPROX 2 MINS AFTER TAKE-OFF THE PILOT HEARD A LOUD BANG FOLLOWED BY TORQUE YAWING. THE PILOT ENTERED AN AUTOROTATION AND LANDED THE ACFT ON A LOGGING ROAD. THE ACFT SUSTAINED MINOR DAMAGE DUE TO HARD LANDING. SUBSEQUENT INVESTIGATION REVEALED APPROX 3 INCHES EXIT HOLE IN THE COMBUSTOR ASSY FROM TURBINE BLADE/DISC FAILURE. INSPECTION OF THE LT ACFT COWLING REVEALED APPROX 2 FT OF ENGINE INTERNAL PART SCATTER DAMAGE. INSPECTION OF THE TAILPIPE AREA REVEALED EXTENSIVE DAMAGE TO ALL WHEEL AND DISC ASSEMBLIES.  ACFT INSPECTED AS UN-AIRWORTHY.                                                                                                       1G71 4U4  U  H1SW    E17EA                
             20081118     NE  2008       11         18         CA080702006      220080612G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 ZJ SIGNIFICANT FAILURE REPORTWARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) THE PILOT REPORTED WHILE AT 3000FT AGL, 2-3 MINUTES AFTER TAKEOFF, HE HEARD A LOUD BANG AND OBSERVED THE PROP TORQUE HAD DROPPED TO ZERO. THE PILOT LANDED THE ACFT SAFELY. THE ENGINE WILL BE FORWARDED FOR INVESTIGATION. MFG WILL HAVE A REPRESENTATIVE ON SITE AND REPORT FINDINGS AS AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3T3  T  A37CE   E4EA                 
             20081118     CE  2008       11         18         CA080702007      120080624G27200510105207      CONTROL CABLE                           CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160CTM    GL  RUDDER          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5099                                                           (CAN) BOTH RUDDER CABLES WERE FOUND WORN AT STA 142 WHERE THEY TRAVEL OVER PULLEYS WITH MINIMAL CONTACT ANGLE.  BECAUSE THERE IS LITTLE PRESSURE AGAINST THE PULLEYS AT THIS POINT, THEY VIBRATE AND CHAFE AGAINST THE PULLEYS, CAUSING WEAR OF THE STRANDS. AFTER REMOVAL OF THE CABLES, THE STRANDS BROKE EASILY WHEN THE CABLE WAS BENT SHARPLY.  THESE ARE GALVANIZED STEEL CABLES.                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A12    E274    5  NP910     
             20081118     NE  2008       11         18         CA080702008      220080308G7200                BEARING                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              DISTRESSED      W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) WHILE AT CRUISE AT FL70, THE ENGINE TORQUE DROPPED BELOW 600FT-LB WITH ASSOCIATED COCKPIT WARNING LIGHT. THE FLIGHT WAS DIVERTED FROM ITS INTENDED DESTINATION AND AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS FWD WHERE DISASSEMBLY SHOWED A DISTRESSED NR 1 BEARING. THE BEARING WAS FWDED TO MFG FOR INVESTIGATION. THE EXTENT OF DAMAGE TO THE BEARING PREVENTED ASSESSMENT OF THE ROOT CAUSE FOR ITS DISTRESS.                                                                                                                                                                                                                                                                                                                    1H71 3T3  T  A37CE   E4EA                 
             20081118     EA  2008       11         18         CA080702009      220080422G7314                DRIVE SHAFT                             EMB   110   EMB110*            SO  PWA   PT6   PT6A34      52043EA                              FUEL PUMP       DISTRESSED      W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               NRNOT REPORTED   1                      CA                                                                      (CAN) ACCORDING TO REPORTS, CREW DECLARED AN EMERGENCY DUE TO ENGINE DISTRESS. DURING SUBSEQUENT LANDING, A/C EXITED THE RUNWAY BEFORE HITTING A DITCH. THE LANDING GEAR COLLAPSED AND THE NOSE OF THE A/C WAS SEVERELY DAMAGED. THE RUNWAY EXCURSION WAS CAUSED BY A LOSS OF DIRECTIONAL CONTROL DURING LANDING.   DISASSEMBLY (BY THE OPERATOR) OF THE ENGINE ON WHICH THE LOSS OF POWER OCCURRED, SHOWED FUEL PUMP DRIVE SHAFT SPLINE DISTRESS (DE-COUPLE). A LARGE AMOUNT OF CORROSION WAS PRESENT AROUND THE AREA.                                                                                                                                                                                                                         1L72 4T4  TRTA21SO   E4EA                 
             20081118         2008       11         18         CA080702010      420080630G3197EC130B4         WIRE                                    UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B1   60056NE                              WARNING SYSTEM  MISREPAIRED     W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA       1998 1998                                                      (CAN) THIS SNAG APPEARED AS AN INTERMITTENT WARNING (GONG) IN THE PILOTS HEADSET. THIS GONG ALERTS THE PILOT TO ANY OF THE RED WARNING LIGHTS ILLUMINATING ON THE CAUTION LIGHT WARNING PANEL. THE GONG WAS PRESENT BUT VERY LOW AND MAY NOT HAVE BEEN HEARD BY THE PILOT IN CASE OF A RED WARNING INDICATION. WIRE SPLICE TO THE ASU CARD NR1 WAS FOUND TO HAVE AN INTERMITTENT CONNECTION. WIRE WAS REPAIRED AND GONG WARNING WAS RETURNED TO THE PROPER LEVEL.                                                                                                                                                                                                                                                                               1G72 3U3  U  H9EU    E00054EN             
             20081118     EU  2008       11         18         CA080702011      120080627G2121EVAC2423H       COOLING FAN                             AEROSPATR42 ATR42320    8680930EU  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF5       NE  NR 2            FAILED          W      O   OTHER                                                                                           JB WARNING INDICATION        SMOKE/FUMES/ODORS/SPARKS                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE TAXIING FOR DEPARTURE (FAB 820) THE CREW OBSERVED A NR2 PACK VALVE FAULT. THE FAULT RECURRED AFTER RESET ACCOMPANIED BY AN AFT SMOKE INDICATION. THE F/A CONFIRMED THE PRESENCE OF SMOKE/HAZE IN THE AFT LAV. WHILE CONDUCTING THE CHECK LIST THE SMOKE INDICATION EXTINGUISHED BUT THE ASSOCIATED ODOR REMAINED EVIDENT.  MAINT REPLACED THE NR2 GROUND COOLING FAN AND THE ACFT WAS RETURNED TO SERVICE. THE SMELL AND HAZE WAS ATTRIBUTED TO THE DUCT OVERHEAT CONDITION RESULTANT FROM THE FAN FAILURE.                                                                                                                                                                                                                         2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20081118     EU  2008       11         18         CA080702012      120080702G6720ASSB3510127     TUBE                        10543079    BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              TAIL ROTOR      CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSP OF THE TAIL ROTOR CONTROL TUBE IAW CAMPAIGN NOTICE 351-67-10-017, A 7X7MM AREA WAS FOUND TO HAVE BEEN CHAFED TO A DEPTH OF .003 INCHES 15MM FWD OF THE PROTECTIVE SLEEVE INSTALLED ON THE CONTROL ROD IN THE 10 O`CLOCK POSITION LOOKING FWD FROM THE AFT OF THE ACFT. CHAFED AREA TO BE CLEANED UP AND ALODINE APPLIED, AND ON REINSTALLATION OF THE PROTECTIVE BOOT ENSURE NO CONTACT WITH THE CONTROL ROD IS PRESENT.                                                                                                                                                                                                                                                                                                             1G72 3U3  U  H3EU    E4CE                 
             20081118         2008       11         18         CA080702013      420080630G6122                VALVE                                   CVAC                               ALLSN 501D  501D13H     03004GL  ALLSN A6441 A6441FN606  GL  PITCH LOCK VALVEFAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) NR 2 PROPELLER WOULD NOT GO INTO BETA OR REVERSE ON LANDING. PROPELLER GOVERNOR AND PITCH LOCK VALVE REPLACED AND PROP FUNCTION CHECKED SERVICEABLE ON GROUND RUN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               4  T          E282    6  CP898     
             20081118     EA  2008       11         18         CA080703001      220080702G7414M3975           COIL            SLICK       4370        CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  MAGNETO         WORN            W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       1286                                                           (CAN) SB 3-08 DEALS WITH THE PROBLEM OF COIL HIGH-VOLTAGE OUTPUT TABS BEING BENT SLIGHTLY DURING MAGNETO MFG. THE DISTRIBUTOR ROTOR HAS A SPRING-LOADED CARBON BRUSH THAT RIDES ON THIS TAB, AND IF THE TAB IS NOT PERPENDICULAR TO THE ROTOR SHAFT, L THE BRUSH IS THRUST SIDEWAYS IN THE ROTOR SHAFT BORE, WEARING THE SIDES OF THE BRUSH AND CUTTING A HALF-MOON DEPRESSION IN THE COIL TAB.  THIS TAB WAS SLIGHTLY OFF-LEVEL AND WAS WORN AS DESCRIBED. THE BRUSH WAS ALSO SOMEWHAT WORN ON ITS SIDES.                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
             20081105     CE  2008       11         5          CA080703002      120080703G531205120151        BULKHEAD                                CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12861                                                          (CAN) A HALF-INCH CRACK WAS NOTED RADIATING FROM THE FLANGE BEND RELIEF CUTOUT NEAR THE BOTTOM OF THE LT SIDE OF THE BULKHEAD AT STATION 108 (IMMEDIATELY INSIDE THE BAGGAGE DOOR), JUST ABOVE FLOOR LEVEL.  THIS AREA IS NORMALLY COVERED BY PLASTIC INTERIOR PANELS. IT WAS DISCOVERED DURING A 200-HOUR INSPECTION, WHICH REQUIRES REMOVAL OF INTERIOR PANELS AND UPHOLSTERY.                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
             20081105     EU  2008       11         5          CA080703004      120080702G2720                CLEVIS PIN                              STBROSSC7   SC72        8100510EU                                                               RUDDER CONTROL  DETACHED        W      A   UNSCHED LANDING                                                                                 DF INFLIGHT SEPARATION       FLT CONT AFFECTED                                   CLCLIMB          1                      CA                                                                      (CAN) ACFT DEPARTED, APPROXIMATELY 30 MILES EN ROUTE,  PLAY WAS NOTICED IN THE RT RUDDER PEDAL, THERE WAS NO RESISTANCE WHEN DEPRESSED AND WAS INOPERABLE, LT RUDDER WAS STILL FUNCTIONAL.  DECISION WAS MADE TO CONTINUE, ACFT LANDED WITHOUT INCIDENT. AFTER FURTHER INSPECTION OF RUDDER CONTROL SYSTEM, A CLEVIS PIN HAD BECOME DETACHED FROM RUDDER CONTROL TORQUE TUBE ABOVE REAR CARGO DOOR. IT APPEARS THE SAFTY CLIP THAT COVERS THE PIN AT BOTH ENDS IS MISSING.                                                                                                                                                                                                                                                                      1H72 3T      A15EU                        
             20081105     EA  2008       11         5          CA080704002      120080702G5753                ROD                                     DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              TE FLAPS        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA  CFTFX173  173                                                       (CAN) DURING AN INSPECTION ON ACFT, IT WAS DISCOVERED THAT THE LT INBD CHORD-WISE FLAP ROD WAS RUBBING AGAINST THE SPAN-WISE ROD. ONCE THEY WERE REMOVED FROM THE ACFT, IT WAS NOTED THAT THE SPAN-WISE ROD HAD A GROOVE WORN IN IT FROM THE OTHER ROD. A NEW SPAN-WISE ROD WAS INSTALLED. DURING INSTALLATION IT WAS NOTED THAT THE BELL CRANK SUPPORT STRUCTURE WAS POSSIBLY NOT SITUATED CORRECTLY LEADING TO A LACK OF CLEARANCE BETWEEN THE 2 RODS. THESE ARE RE-LIFED WINGS PURCHASED FROM R.W. MARTIN AND INSTALLED BY ROCKY MOUNTAIN ACFT. THE EXACT CAUSE HAS NOT BEEN DETERMINED YET AND AN UPDATE WILL BE PROVIDED WHEN THIS IS DETERMINED.                                                                                          1H72 3T4  TRTA9EA    E4EA                 
             20081105         2008       11         5          CA080704003      420080703G23973042865102      ELECTRICAL BOX                          BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              ROW 8 DEF       ODOR            W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) LIVE TV SCREENS ON SEATS DEF IN ROW 8 NOT DISPLAYING ANY PICTURE (BUT POWER STILL DELIVERED) AND BURNING ELECTRIC/METAL STRONG ODOR OCCURRING IN VICINITY OF ROW 8. LIVETV SYSTEM TURNED OFF WITH FLIGHT ATTENDANT CONTROL PANEL AND ODOR DISSIPATED WITHIN 10-15 MINUTES. THE IFE SYSTEM WAS DEACTIVATED. MX PLACED THE IFE SYSTEM UNDER MEL. SEB AT ROW 8 RT WAS REPLACED, WIRES AND CONNECTORS INSPECTED AND SYSTEM TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E00055EN             
             20081105         2008       11         5          CA080704004      120080704G3246                BEARING                                                                                                                                 MLG WHEEL       LACK OF LUBE    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) EXCESSIVE WHEEL BEARING NOISE WAS NOTED FROM LANDING GEAR DURING TAXIING. INVESTIGATION REVEALED THAT WHEEL BEARING GREASE HAD WASHED OUT OF THE BEARING AND ONTO THE WHEEL HALF.  WATER HAD PERMEATED THE GREASE AND CAUSED EXCESSIVE CORROSION TO THE BEARING AND CUP. U/S PARTS WERE REPLACED. THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM. WE DID NOT REPORT THE FIRST 1 AS WE THOUGHT IT WAS AN ISOLATED CASE. HOWEVER, IT APPEARS IT IS NOT.                                                                                                                                                                                                                                                                                                                                
             20081105     NM  2008       11         5          CA080707002      120080705G2751                INDICATOR                               BOEING727   727225      1384077NM  PWA   JT8   JT8D15A     52051NE                              FLAP SYSTEM     BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKE-OFF WHEN RETRACTING FLAPS THE INBD FLAPS STUCK AT APPROXIMATELY 5 DEGREES WITH AN ASYMMETRY. THE ACFT DECLARED AN EMERGENCY WITH A FLAP PROBLEM AND RETURNED TO CYYC. THE ACFT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING WAS CARRIED OUT AND THE LT INBD FLAP POSITION TRANSMITTER DRUM CABLE WAS FOUND TANGLED AND HAD NO TENSION. THE DRUM ASSEMBLY WAS FOUND TO BE AT FAULT, AND THE TRANSMITTER ASSEMBLY SPRING TENSION HAD FAILED. THE FLAP POSITION TRANSMITTER ASSEMBLY WAS REPLACED AND THE FLAP ADJUSTMENT/TEST PROCEDURES WERE CARRIED OUT WITH NO FURTHER FAULTS. THE ACFT WAS RETURNED TO SERVICE.                                                                                                          2L73 4F4  F  A3WE    E2EA                 
             20081105     GL  2008       11         5          CA080707003      220080706G732123065104        BEARING         HONEYWELL               BELL  206   206B3       1181506SW  ALLSN 250C  250C20B     03013GL                              FCU DRIVESHAFT  FAILED          W      B   EMER. DESCENT                                                                                   XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA            1141                                                      (CAN) PILOT NOTED N1 INCREASE DURING CRUISE.  REDUCED THROTTLE AND N1 DECREASED ACCORDINGLY.  SOME THROTTLE CONTROL WAS POSSIBLE BUT THE ENGINE CONTINUED TO ACCELERATE.  THROTTLE WAS REDUCED UNTIL IDLE STOP WAS REACHED AT WHICH TIME IT CONTINUED TO CLIMB.  AT APPROX 15 FT AGL THE ENGINE WAS SHUT DOWN AND A SUCCESSFUL AUTO ROTATION WAS CARRIED OUT.  NO DAMAGE TO THE ACFT.  MX REMOVED FCU IN THE FIELD.  UPON REMOVAL IT WAS NOTED FCU DRIVESHAFT BEARING FAILED.  ALLOWS AXIAL AND RADIAL PLAY APPROX 1/2" BOTH WAYS.  BALL BEARINGS COMPLETELY DISLODGED.  LUBE FOUND INTACTED (NO WASHOUT) AND NO CORROSION NOTED.  REPLACEMENT FCU INSTALLED AND ACFT WAS RUN UP.  ACFT DEPARTED BACK TO BASE WITH NO FURTHER ISSUES.           1G71 3U3  U  H2SW    E4CE                 
             20081105     CE  2008       11         5          CA080707004      120080526G561099144111        WINDSHIELD                              CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       1114 1114                                                      (CAN) ON DESCENT FOR LANDING THE PILOT NOTED A LT WINDSHIELD INOP ICAS MSG AND SHORTLY AFTER THE PILOTS WINDSHIELD OUTER PANE SHATTERED. THE ACFT LANDED WITHOUT FURTHER PROBLEMS AND THE ACFT WAS FLOWN TO A SERVICE CENTER WHERE THE WINDSHIELD WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRCT00012WIE35NE                
             20081113     CE  2008       11         13         CA080707005      120080407G322012436351        TORQUE LINK                             CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRING INP ON UPPER TORQUE LINK IAW CONTINUED AIRWORTHINESS PROGRAM 32-50-02 THE TORQUE LINK WAS FOUND CRACKED. A NEW LINK WAS INSTALLED WITH NEW BOLTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  A4CE    E5CE    5  CP47GL    
             20081113     SW  2008       11         13         CA080707006      120080616G6510407040416103    SHAFT                                   BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              TAIL ROTOR      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6360 6360                                                      (CAN) WHILE REMOVING THE TAIL ROTOR FROM THE ACFT, THE ENGINEER PERFORMING THE WORK NOTED THAT SEPARATING THE HUB FROM THE OUTPUT DRIVE SHAFT WAS SUBSTATIALLY MORE DIFFICULT THAN NORMAL. ONCE THE TAIL ROTOR WAS REMOVED IT WAS NOTED THAT THE INCORRECT TYPE OF LUBRICANT HAD BEEN APPLIED DURING THE LAST INSTALLATION OF THE TAIL ROTOR. THE TR GEARBOX WAS SENT TO A REPAIR FACILITY FOR A SCHEDULED INSP AND THE TR OUTPUT SHAFT WAS SUBSIQUENTLY SCRAPPED DUE TO CORROSION OF THE TR AND TAIL ROTOR OUTPUT SHAFT DRIVE SPLINES.                                                                                                                                                                                                         1G71 3U3  UO H2SW    E1GL                 
             20081113     CE  2008       11         13         CA080707007      120080422G2730                BEARING                                 CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  CONTROL TUBE    WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16227                                                          (CAN) WHILE INSP IT WAS NOTICE THAT THE LT CONTROL TUBE WAS ROUGH AS IT WAS PULLED OUT AND PUSHED IN. AFTER TAKING IT OFF, IT WAS NOTICED THAT THE BEARINGS HAD WORN THE TUBE TO ITS LIMITS. THE CONTROL TUBE AND THE BEARINGS WERE CHANGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  A4CE    E5CE    5  CP47GL    
             20081113         2008       11         13         CA080707008      420080407G6113TCB43940008     SPINNER                                 PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT PROP         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING AN INSP, PROP SPINNER WAS FOUND CRACKED. THE CRACK STARTED FROM THE THE SCREW HOLES. A NEW SPINNER WAS INSTALLED AND THE PROP WAS BALANCED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081113     NE  2008       11         13         CA080707009      220080703G72300292208260      DIFFUSER                                AEROSPAS355 AS355*             EU  TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING MAINT FOR REPLACEMENT OF THE T2 BLADES AND WHEEL, AFTER REMOVING OUTER CASING OF THE M03 THE OUTSIDE SURFACE OF THE DIFFUSER WAS FOUND CRACKED FROM ONE SIDE TO THE OTHER.  A SERVICEABLE M03 WAS INSTALLED AND THE HELICOPTER WAS RETURN TO SERVICE. DAMAGED M03 WAS SENT TO MFG FOR INVESTIGATION. THE M03 HAD 1479.3 HRS TSO.                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  U  H11EU   E19EU                
             20081113     SO  2008       11         13         CA080707010      120080516G2750                WORM GEAR       CALCO                   PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  FLAP XMSN       WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE INSP, IT WAS NOTICED THAT BOTH FLAP TRANSMISSION WERE WORN OUT OF LIMITS. OVERHAULED FLAP TRANMISSIONS WERE INSTALLED. THEY WERE BOTH WITHIN LIMITS AT THE LAST INSP. ONCE THEY START TO WEAR THEY REALLY WEAR FAST.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081113     CE  2008       11         13         CA080707011      120080528G3020                BUSHING                                 BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  ICE VANE LINK   WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AT THE INSP IT WAS NOTICED THAT THE ICE VANE BUSHINGS WERE WORN CAUSING THE VANE TO MOVE ENOUGH TO ALLOW THE ICE VANE LIGHT TO COME ON.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4T4  T  A24CE   E4EA    6  CP15EA    
             20081113     EU  2008       11         13         CA080707012      120080629G5302                SKIN                                    AEROSPAS355 AS355*             EU  TMECA ARRIELARRIEL1D1   60053NE                              TAILBOOM        DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE HELICOPTER EXPERIENCED A HARD LANDING AFTER BEING PUSHED SIDEWAYS BY A GUST OF WIND. THE RT SKID CAUGHT THE GROUND FIRST AND THE HELICOPTER STARTED TO YAW SEVERLY, PILOT DROPPED COLLECTIVE AND LANDED THE HELICOPTER IMMEDIATELY. THE TAILBOOM SUSTAINED DAMAGE CAUSED BY THE SUDDEN YAW, SERVICEABLE TAILBOOM AND HARD LANDING INSP C/W IAW MM AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                            1G72 3U3  U  H11EU   E19EU                
             20081113     NE  2008       11         13         CA080707013      220080627G7210310830601       SLEEVE                                                                     PWA   PT6   PT6A67D          NE                              NR 5 BRG JOURNALDISLODGED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       175267040                                                      (CAN) THE ASSEMBLY HAD ACCUMULATED IN EXCESS OF 7000 HOURS SINCE THE SLEEVE WAS INSTALLED ON THE NR 5 BEARING JOURNAL, AND THE POWER SECTION WAS BEING RETURNED TO THE SHOP FOR A SCHEDULED OVERHAUL.   DURING INSPECTION OF THE 2ND STAGE REDUCTION CARRIER IAW OHM 3038337, SEC.72-10-00 INSPECTION, PARA.6AM IT WAS FOUND THAT THE NR 5 BEARING JOURNAL SLEEVE HAD MOVED AWAY FROM THE CARRIER SHOULDER BY APPROXIMATELY 0.021. NO OTHER DEFECTS WERE NOTED ON THE SLEEVE.                                                                                                                                                                                                                                                                          4  T          E26NE                
             20081113     SO  2008       11         13         CA080707014      120080606G323042042000        ARM                                     PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              LT MLG RETRACT  BROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING TAKEOFF, COULDN`T GET GEAR UP, LT GREEN LIGHT STAYS ON. UPON INSP AFTER LANDING, LT RETRACTION ARM WAS FOUND BROKEN. CRACK WAS ORIGINATED FROM ONE OF THE BOLT HOLES. NEW PART WAS ORDERED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A20SO   E14EA                
             20081113     SW  2008       11         13         CA080708001      120080622G2820S0310015HT      O-RING          GULSTM                  GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  COUPLING        WORN            W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) AFTER LANDING AND DURING WALK AROUND FLIGHT CREW FOUND FUEL LEAKING FROM RT WING OTBD OF NACELLE. FURTHER INSP BY MAINT FOUND FUEL LEAKING FROM FUEL INTERCONNECT PIPE COUPLING ASSY. NEW O-RINGS INSTALLED, LEAK CHECKS CARRIED OUT AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H72 3T4  T  2A4     E4WE    6  CP8EU     
             20081113     EA  2008       11         13         CA080708002      120080706G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              RT TE FLAP      UNSERVICEABLE   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) ACFT WAS SET UP IN LANDING CONFIGURATION WITH FLAPS AT 45 DEGREES. ON SHORT FINAL, CREW RECEIVED A FLAP FAILURE INDICATION. FLIGHT DID LAND NORMALLY.  HOWEVER, WERE UNABLE TO RETRACT FLAPS ONCE ON THE GROUND.   RT BPSU SHOWN TO BE AT FAULT. BPSU REPLACED AND COMPLETE SYS RIG CARRIED OUT. FUNCTION CHECKED SERVICEABLE WITH NO FURTHER FAULTS FOUND.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20081113     CE  2008       11         13         CA080708004      120080626G3230PDLM60          CIRCUIT BREAKER BEECH                   BEECH 100   100BEECH    1152916CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  LANDING GEAR    FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT DEPARTED, OR AFTER SCHEDULED MAINT WAS COMPLETED. IN THE CLIMB OUT IT WAS NOTICED BY THE CREW THAT THE LANDING GEAR FAILED TO RETRACT. THE ACFT LANDED WITHOUT INCIDENT. UPON INSP IT WAS FOUND THAT THE CIRCUIT BREAKER HAD FAILED BUT HAD NOT ACTUALLY POPPED. THE BREAKER WAS BENCH TEST AND CONTINUED TO NOT ALLOW POWER THOUGH DESPITE BEING PROPERLY DEPRESSED. THE BREAKER WAS REPLACED WITH A NEW ONE AND THE SYS FUNCTION TESTED NORMAL.                                                                                                                                                                                                                                                                                    1L72 3T4  T  A14CE   E2WE    6  CP40EA    
             20081113     CE  2008       11         13         CA080708005      120080708G273155657562        WHEEL                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ELEVATOR TRIM   DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN A SMALL FORCE WAS APPLIED TO THE INDICATOR POINTER AND THE TRIM WHEEL WAS ROTATED THE POINTER JUMPED OUT OF ITS GROOVE. INSPECTION FOUND THAT THE GROOVES WERE NOT WORN AND THE SYSTEM LOOKED NORMAL BUT WHEN THE WHEEL WAS ROTATED WITH 1 FINGER APPLYING PRESSURE TO THE SIDE OF THE WHEEL IT WOBBLED AND ALLOWED THE PIN RIDING IN THE GROOVE TO BECOME DISENGAGED. PINCHING THE WHEEL WITH A THUMB AND FINGER OR TURNING THE WHEEL WITH THE PALM OF THE HAND ON THE TOP DID NOT ALLOW THE PIN TO DISENGAGE.                                                                                                                                                                                                                      1L72 4F4  F  A22CE   E1NE                 
             20081113     NE  2008       11         13         CA080708006      220080621G7314LW15473         PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        LEAKING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       98                                                             (CAN) DURING A GROUND RUN OF THE ACFT THE ENGINE FUEL PUMP WAS LEAKING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  O  H11NM   1E4                  
             20081113     WP  2008       11         13         CA080708007      120080630G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       344                                                            (CAN) STARTER BENDIX IS NOT FUNCTIONING/STARTER WOULD NOT ENGAGE THE RING GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
             20081113     WP  2008       11         13         CA080708008      120080629G6310C0511           ACTUATOR                                ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CLUTCH          LOOSE           W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE CLUTCH ACTUATOR LOWER MOTOR HSG FLANGE TO WORM GEAR FOUND LOOSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
             20081113     SO  2008       11         13         CA080708009      120080620G8011                STARTER                                 PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            641                                                       (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH A SERVICABLE STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081113         2008       11         13         CA080708010      420080708G3452                TRANSPONDER                             CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              ATC             INTERMITTENT    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MODE C ALTITUDE REPORTING INTERMITTENTLY REPORTS FALSE ALTITUDES. VISUAL INSP FOUND A CHAFED MODE C A1 CODE WIRE IN THE ALTITUDE ENCODER WIRING. WIRE WAS CHAFFING (DUE TO VIBRATION) ON THE THROTTLE CABLE DIRECTLY BEHIND THE CENTER RADIO PANEL. WIRE WAS REPAIRED AND CHAFE PROTECTION WAS ADDED TO THE WIRE HARNESS. MODE C DATA INTEGRATION CHECK WAS PERFORMED IAW CARS STD 571 APPENDIX F, ITEM K.                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
             20081113     NM  2008       11         13         CA080708011      120080708G2497                WIRE                                    BOEING737   737400      138449ANM                                                               COCKPIT         CHAFED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA       35061                                                          (CAN) P5 OVERHEAD COCKPIT PANEL WAS OPENED DURING NORMAL MX ACTIVITIES AT THE C2 MX EVENT. ARCING WAS NOTED BETWEEN THE DOOR WARNING MODULE AND ADJACENT WIRE BUNDLES. DAMAGE TO WIRING WAS ALSO FOUND AT THE P5-13, ELECTRICAL METERS AND GALLEY POWER MODULE. INSPECTION REVEALED NO AFFECT TO ACFT STRUCTURE, BUT 6 WIRES WERE FOUND CHAFFED REVEALING THEIR RESPECTIVE CONDUCTORS (REF A AND C). A 7TH WIRE WAS FOUND SEVERED. THE MODULES WILL BE TESTED FOR SERVICEABILITY AS A SMALL BURN MARK WAS FOUND AT THE CORNER OF THE CASE.   THE FOLLOWING WIRES ARE TO BE REPLACED TO CORRECT THE DEFECTS FOUND: 1. W036-650-22, WDM ATA 29-11-01. W036-8769-22, WDM ATA 24-31-11. W036-15A-24, WDM ATA 21-58-03 PG1 4. W036-043-22, WDM ATA 242L72 4F    RTA16WE                        
             20081113     NE  2008       11         13         CA080709001      220080706G73207982133007      EEC                                     DHAV  DHC8  DHC8315     2809010NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ON TAKE OFF, THROUGH 400 FT WITH BLEEDS ON AND CLIMB POWER SET 90% NH + 900 RPM, ENGINE LT EXPERIENCED A SURGE. LT NH WENT 110%, THEN DROPPED TO 70%. RESTABILIZED AT 90%. REDUCED POWER TO BOTH ENGINES. RETURNED FOR LANDING. GROUND RUNS WERE COMPLETED COULD NOT DUPLICATE, THE DATA FROM THE ONBOARD ACFT FLIGHT INFORMATION REPORTING SYSTEM (AFIRS) AND IT WAS FOUND THAT THERE WAS AN INCREASE IN FUEL FLOW TO THE ENGINE CAUSING THE POWER SURGE. THE ENGINE ELECTRONIC CONTROL UNIT (EECU) WAS REPLACED THE ENGINES WERE GROUND RUN AND NO FAULTS WERE FOUND.                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081113     EU  2008       11         13         CA080709002      120080708G32205322012289      DRAG LINK                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6663                                                           (CAN) NLG DRAG LINK FOUND CRACKED DURING PREFLIGHT INSP. DRAG LINK REPLACED WITH NEW. THIS IS THE 3RD ONE FOUND CRACKED ON 3 DIFFERENT ACFT IN THE LAST 6 MONTHS IN THE EXACT SAME SPOT. ALL DRAG BRACES SENT TO MFG FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081113     NM  2008       11         13         CA080709003      120080709G2710                CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERONS        MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       2634                                                           (CAN) FOUND BALL END OF LT AND RT AILERON CONTROL CABLES NOT FULLY ENGAGED IN WW BELLCRANK CABLE SLOT.(FWD CABLE)  BALL END OF LT AND RT AILERON CONTROL CABLES IN WW BELLCRANK CABLE SLOT.(FWD CABLE) REENGAGED PROPERLY IN ACCORDANCE WITH AMM 27-11-03-400-801.  SEE ATTACH PICTURE                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA57NM   E00070EN             
             20081113     NM  2008       11         13         CA080709004      120080709G575319092001405     CARRIAGE                                EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              LT TE FLAP      GROOVED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2634                                                           (CAN) LT INBD FLAP MAIN 1 CARRIAGE ASSY (P/N 190-92001-405) FOUND GROOVED INSIDE BY LOOSE BOLT FROM TRACK ASSY.  ENGINEERING ADVISED THE ROOT CAUSE OF THE DAMAGE OF THE FLAP CARRIAGE IS CAUSE BY THE FLAP TRACK MECHANISM LOOSE BOLT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA57NM   E00070EN             
             20081113     EU  2008       11         13         CA080709005      120080706G2720RS87            RETAINING RING  BRAERO                  BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  RUDDER PEDAL    MISSING         W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       500                                                            (CAN) RUDDER PEDAL BECAME DISENGAGED FROM PEDAL SPIGOT, RS87 RETAINING RING CAME OUT OF RETAINING SLOT. RETAINING RING SEEMED TO HAVE INSUFFICIENT TENSION TO STAY IN SLOT. NEW RING INSTALLED AND NO FURTHER PROBLEMS. FLEETWIDE INSPECTION CARRIED OUT AND NO SIMILAR PROBLEMS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
             20081113     NM  2008       11         13         CA080709006      120080703G271019005549401     CONTROL CABLE                           EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1407                                                           (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401, PN 190-04209-401, PN 190-05549-401, RT PN 190 -05551-401, PN 190-05550-401, PN 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLEAD.    EMBRAER CAME UP WITH 2 SERVICES BULLETIN:  SB190-27-0017 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR  SB170-27-0028 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA57NM   E00070EN             
             20081113     NM  2008       11         13         CA080709007      120080709G322019070150404     BUSHING                                 EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              NLG             MIGRATED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2634                                                           (CAN) DURING INSPECTION FOUND BUSHING MIGRATED ON NLG RETRACK ACTUATOR LOWER ATTACHMENT (PRC BROKEN) AND ON RT MLG SIDE STAY LOWER ATTACHMENT.  NLG SHOCK STUT ASSY PN 190-70453-401 SN 00053  MLG SIDE STAY PN 190-70150-404 SN 00053  AFTER INVESTIGATION FOUND NO CLEARANCE FIT, EMBRAER HAS BEEN ADVISED OF THE PROBLEM. THIS PROBLEM HAS BEEN ALREADY FOUND ON NUMEROUS ACFT                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA57NM   E00070EN             
             20081113     EA  2008       11         13         CA080709008      220080704G8530                EXHAUST VALVE                                                              LYC   O540  O540*       41532EA                              ENGINE          SEIZED          W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              DEDESCENT        1                      CA                                                                      (CAN) DURING A FLIGHT IN THE R44 HELICOPTER, THE PILOT NOTICED A SIGNIFICANT VIBRATION APPROX. 2 HOURS INTO THE FLIGHT. THE VIBRATION LASTED 45 SECONDS. THERE WERE NO AUDIBLE ALARMS & ALL GAUGES READ NORMAL.  THE A/C WAS DESCENDING WITHOUT CONTOL INPUTS,AFTER THE 45 SECOND VIBRATION SUBSIDED.A/C RETURNED TO BASE. THE A/C WAS STARTED THE FOLLOWING DAY THE VIBRATION WAS NOTED @102% IN HOVER ,A/C LANDED,WAS SHUT DOWN AND SB388C(VALVE CLEARANCE CHECK) WAS CARRIED OUT.NUMBER 3 AND NR 6 EXHUAST VALVES WERE SEIZED WITH BENT PUSH RODS.CYLINDER NUMBER 1, 2,,4 VALVES WERE BELOW THE ALLOWABLE CLEARANCE                                                                                                                                 3  O          E295                 
             20081113     NE  2008       11         13         CA080709009      320080703G6111SFA13N1ROA1D    BLADE                                   CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  PROP ASSY       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       10                                                             (CAN) 3 BLADES FOUND LEAKING AFTER 10 HRS OF INSTALLATION. THESE BLADES WERE ALREADY SENT  FOR TEFLON STRIP REPLACEMENT DUE TO THE SAME KIND OF SNAG EARLIER THIS SPRING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
             20081113     NE  2008       11         13         CA080709010      220080706G8550                SCAVENGE PUMP                           DOUG  DC6   DC6B        3021712WP  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA                                                                      (CAN) NR4 BMEP WENT TO 0. OIL TANK QUANTITY DROPPED FROM 25GALS TO 12 GALS IN A FEW MINUTES. ENGINE WAS FEATHERED AND LANDING CARRIED OUT WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L74 4R3  R  6A4     ATC14   6  CP871     
             20081113     GL  2008       11         13         CA080709011      320080709G6111A1851B          BEARING RACE                                                                                                HARTZLHCB3R HCB3R304    GL  PROPELLER       FRACTURED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PROPELLER WAS RECEIVED IN SHOP FOR REMOVAL OF A BROKEN OFF GREASE NIPPLE IN BLADE CLAMP. BLADE CLAMP REQUIRED REMOVAL TO EXTRACT BROKEN GREASE NIPPLE. WHEN THE CLAMP WAS REMOVED A CHIP OF THE OTBD BEARING FELL OUT. AFTER EXAMINING THE BEARING IT WAS DETERMINED THAT THE ENTIRE ASSEMBLY SHOULD BE REPLACED DUE TO EXCESSIVE RACE AND BALL WEAR. IT SHOULD BE NOTED THAT THE GREASE IN THIS CLAMP WAS BLACK FROM METAL WEAR WHEREAS THE GREASE IN THE OTHER 2 BLADE CLAMPS WAS IN NORMAL CONDITION FOR THIS PROP TYPE. BEARING WAS REPLACED AND PROPELLER RETURNED TO SERVICE.                                                                                                                                                                                    5  CP28EA    
             20081113     SW  2008       11         13         CA080710001      120080708G5620412670101       WINDOW                                  BELL  412   412EP       1182205SW  PWA   PT6T  PT6T3       52045EA                              PAX DOOR        MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       5                                                              (CAN) WHILE THE ACFT WAS IN A DIVE, IN ORDER TO REACH VNE FOR RADS READING, AFT RT PASSENGER DOOR WINDOW WAS LOST IN FLIGHT AT 138 KNOTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G72 4U4  U  H4SW    E22EA                
             20081113     SW  2008       11         13         CA080710002      120080618G255026801500        CABLE                                   BELL  427   427         1182207SW  PWC   PW207 PW207D           NE                              CARGO HOOK ASSY BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       284                                                            (CAN) MANUAL RELEASE CABLE BROKE AT CARGO HOOK FITTING CAUSING HOOK TO RELEASE INFLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  R00001RCE42NE                
             20081113     EU  2008       11         13         CA080710003      120080704G2822045004B145A     SWITCH                                  SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B1   60056NE                              FUEL PUMP       FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       435                                                            (CAN) FUEL PUMP WOULD NOT TURN ON                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H9EU    E00054EN             
             20081113     CE  2008       11         13         CA080710004      120080709G7120J124532         MOUNT                                   CESSNA210   210R        2073458CE  CONT  O520  IO520L      17032SO  MCAULYD3A34 D3A34C404   GL  ENGINE          DEFORMED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1863                                                           (CAN) DURING ENGINE INSPECTION NOTED THAT THE LT AND RT FORWARD ENGINE MOUNTS WERE SAGGING TO THE POINT THAT DURING TAKEOFF POWER ON ENGINE AND INTAKE PIPE HOSE CLAMP MADE CONTACT WITH THE UPPER PORTION OF ENGINE MOUNT.  THE LORD MOUNT APPEARED TO BE SAGGING/DROOPING BUT NOT SEPERATED ANYWHERE. BOTH FRONT ENGINE MOUNTS REPLACED WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ORT3A21    E5CE    5  CP47GL    
             20081113     NE  2008       11         13         CA080710005      220080708G8530                EXHAUST VALVE                                                              PWA   R985  R985AN14B   52008NE                              ENGINE          DAMAGED         W      O   OTHER                                                                                           RE PARTIAL RPM/PWR LOSS      VIBRATION/BUFFET                                    CRCRUISE         1                      CA       1513 1513                                                      (CAN) EXHAUST VALVE BROKE/SEPARATED DURING FLIGHT. BASE OF VALVE STAYED IN COMBUSTION SECTION OF CYLINDER AS ENGINE RAN CAUSING DAMAGE TO PISTON, AND UPPER CYLINDER COMBUSTION CHAMBER. PILOT REPORTED DECREASE IN POWER/VIBRATION AND UPON THROTTLING BACK, AN INCREASE IN VIBRATION.  ACFT LANDED WITHOUT INCIDENT. CYLINDER HEAD FOUND TO HAVE BEEN BROKEN OFF, MOST OF CYLINDER PARTS RECOVERED IN COWLING EXCEPT FOR EXHAUST SYSTEM. LOWER EX VALVE BASE SHOWS SIGN OF HAVING BEEN CRUSHED ABOVE PISTON REPEATEDLY UNTIL CYLINDER FAILED. UNKNOWN AS TO IF EXHAUST VALVE WAS REPLACED NEW, WITH SERVICEABLE, OR OVERHAULED AT LAST ENGINE OVERHAUL.                                                                                              3  R          5E1                  
             20081113     SW  2008       11         13         CA080710006      120080709G5410205030195030    BEAM                                    BELL  205   205A1       1181414SW  LYC   T53   T5317BLYC   41616NE                              LT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION, NOTICED A CRACK ON THE LT MAIN BEAM CAP UPPER WEB NEAR THE FORWARD ENGINE FIRE WALL. THE ACFT WAS GROUNDED. THE AIRFRAME TIME 15185 HOURS. THE TIME ON THE MAIN BEAM CAP IS UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 4U4  U  H1SW    E17EA                
             20081113     EU  2008       11         13         CA080711001      120080708G2121BC112A2         FAN                                     SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F26 NE  CABIN           OVERHEATED      W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) ON JULY 8/2008, SHORTLY AFTER TAKEOFF THE CREW NOTICED AN ELECTRICAL ODOR WHICH WAS ALSO CONFIRMED BY THE F/A. THE CREW DECLARED AN EMERGENCY AND PROCEEDED TO LAND WITHOUT INCIDENT. MX WAS DISPATCHED TO THE ACFT WHERE IT WAS NOTICED THAT WHEN THE FLIGHT DECK RECIRCULATION FAN WAS SELECTED THE CONTROL BREAKER POPPED. THE CENTER ISLE FLOOR BOARDS WERE REMOVED AND AN INSPECTION WAS CARRIED OUT ON BOTH FANS. IT WAS DETERMINED THAT THE FLIGHT DECK FAN HAD OVERHEATED AND WAS THE SOURCE OF THE PROBLEM. MX MEL`ED THE FAN AND THE CREW CARRIED OUT A TEST FLIGHT AS AN EXTRA PRECAUTION. THE ACFT WAS RETURNED TO SERVICE.                                                                                                   2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20081113         2008       11         13         CA080711002      420080709G34516221234013      INDICATOR                               SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  DME             BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE CREW REPORTED A LOUD POP WHICH WAS FOLLOWED BY AN ELECTRICAL ODOR AND THE DME WENT OFF LINE. THE CREW SHUT DOWN ALL NON-ESSENTIAL AVIONICS AND CONTINUED WITHOUT INCIDENT. THE ACFT WAS THEN POSITIONED AT THE HANGAR WHERE MX REMOVED AND CARRIED OUT AN INSPECTION ON THE DME INDICATOR. UPON A CLOSER LOOK IT WAS NOTICED THAT THE CAPACITOR HAD FAILED. IT WAS DETERMINED THAT THE INDICATOR WAS THE SOURCE OF THE PROBLEM.                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081113     EA  2008       11         13         CA080711003      120080704G28102156400212      FUEL CELL                               CNDAIRCL215 CL2156B11215       EA                                                                               LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING A FUEL CELL CHANGE DUE TO A LEAK PROBLEM, THE TECHNICIAN DID A LEAK TEST ON THE NEW 1 THAT WAS COMING FROM THE STORE AND RECEIVED FROM DIRAZUR- ZODIAC GROUP ON JULY 2007,(WELL PRESERVE). H E FOUND THAT IT WAS LEAKING FROM THE CENT.  NOTE: WEVE HAD SO MANY PROBLEMS WITH THESE CELLS THAT WE MADE AN INTERNAL PROCEDURE TO TEST THEM BEFORE INSTALLATION                                                                                                                                                                                                                                                                                                                                                                     2H72 4T    RTA14EA                        
             20081113     GL  2008       11         13         CA080711004      120080627G2150347074          BEARING                                 BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              ACM IMPELLER    DRAGGING        W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) CREW REPORTS THEY WERE ON TAXI WAY, HAVING JUST LEFT THE FBO WHEN THICK GREY SMOKE STARTED ROLLING OUT OF THE VENTS. THE CABIN FILLED UP QUICKLY ENOUGH THEY WERE STARTING TO HAVE TROUBLE BREATHING. ONLY THING THEY MANAGED TO DO WAS SHUT DOWN AND GET OUT OF ACFT. RAMP AGENT FOR THE FBO DROVE UP IN A TRUCK, SAW WHAT WAS GOING ON, AND CALLED THE FIRE DEPARTMENT. FD USED THERMAL IMAGING TO DETERMINE THERE WAS NO FIRE AND LEFT. NO EMERGENCY WAS DECLARED.                                                                                                                                                                                                                                                                     2L72 4F4  FRTT00005NYE00010LA             
             20081113     SO  2008       11         13         CA080711005      220080620G8530AEC646263       PISTON                                  CESSNA182   182K        2072724CE  CONT  O470  O470R       17026SO  MCAULY2A34C 2A34C66     GL  SKIRT           BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       517                                                            (CAN) A PIECE OF NR 2 PISTON SKIRT WAS BROKEN OFF AT THE OIL CONTROL RING GROOVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A13    E273    5  CP3EA     
             20081113     NE  2008       11         13         CA080711006      220080701G7230                BLADES                                  PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                              COMPRESSOR      DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL200, THE PILOT NOTED THE ENGINE TEMPERATURE RAPIDLY RAISING TO 850C WITH POWER TURBINE SPEED DECREASING. HE ELECTED TO SHUT THE ENGINE DOWN AND PERFORMED A SUCCESSFUL DEAD STICK LANDING.  POST FLIGHT ENGINE EXAMINATION REVEALED HEAVY RUBBING DAMAGE IN THE COMPRESSOR SECTION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                     1L71 3T4  TRTA78EU   E26NE                
             20081113     CE  2008       11         13         CA080711007      120080626G793230B385103       SENSOR                                  CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              RT ENGINE       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1155 1155                                                      (CAN) DURING MX VISUAL CHECK OF RT ENGINE A SMALL AMOUNT OF OIL WAS NOTED AROUND THE ENGINE LOW LEVEL OIL SENSOR.  FURTHER INVESTIGATION FOUND OIL LEAKING INTERNALLY THROUGH SENSOR AND EXITING OUT OF CANNON PLUG. RT LOW LEVEL OIL SENSOR WAS REPLACED WITH NEW AND NO FURTHER LEAKS WERE DETECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRCT00012WIE35NE                
             20081113     EA  2008       11         13         CA080711008      120080706G3240AE87996E        LINE                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              NR 2 BRAKE ASSY DISCONNECTED    W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      LDLANDING        1                      CA                                                                      (CAN) ACFT HAD A NORMAL LANDING ON ARRIVAL IN IND, HOWEVER WHILE ATTEMPTING TO TAXI OFF THE RUNWAY, EXCESSIVE POWER WAS REQUIRED TO TAXI.  IT WAS SUSPECTED THAT NR 2 BRAKE ASSEMBLY HAD SEIZED AS SMOKE COMING FROM THE NR 2 BRAKE. CONTRACT MX INVESTIGATED THE ACFT AND THE QUICK DISCONNECT HYDRALIC LINE TO THE NR 2 BRAKE OFF. THE QUICK DISCONNECT WAS RESECURED AND THE BRAKES WERE FUNCTION CHECKED SERVICEABLE. THERE HAS BEEN NO FURTHER OCCURANCES TO DATE. IT IS SUSPECTED THAT THE QUICK DISCONNECT CONNECTOR MAY HAVE BACKED OFF CAUSING THE DRAGGING BRAKE CONDITION.                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20081113     NE  2008       11         13         CA080711009      220080629G7261                ENGINE                                  CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                                              OIL CONSUMPTION W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) DURING T/O ROLL, THE PILOT RECEIVED A LOSS OF OIL PRESSURE WARNING AND ABORTED T/O. THE ACFT RETURNED TO THE RAMP WHERE THEY OBSERVED NO OIL ON THE SIGHT GLASS. OIL WAS NOTED IN THE EXHAUST AND A GROUND RUN SHOWED A CONSUMPTION OF 2 QUARTS IN 10 MIN. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA22CE   E00059EN             
             20081113     EU  2008       11         13         CA080711010      120080705G7797                CONNECTOR                               BAG   ATP   ATP                EU  PWA   PW120 PW126A           NE                              ENGINE          CONTAMINATED    W      O   OTHER                                                                                           RX PARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT                                     CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE ENGINE TORQUE STARTED TO FLUCTUATE BETWEEN 60% TO 120% AND THE ENGINE SHUT ITSELF DOWN. TROUBLESHOOTING REVEALED HEAVY CONTAMINATION ON 1 OF THE CONNECTORS OF THE ENGINE ELECTRONIC CONTROL. THE CONNECTOR WAS CLEANED, GROUND RUN PERFORMED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA27NM   E2ONE                
             20081113     NE  2008       11         13         CA080711011      220080706G8530399354          CYLINDER HEAD                           DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              ENGINE          SEPARATED       W      A   UNSCHED LANDING                                                                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA            372                                                       (CAN) IN FLIGHT ENGINE BECAME ROUGH - POPPING/BANGING SOUND PRECAUTION AND LANDING COMPLETED ENGINE INSPECTED - CYL NR 3 HEAD FOUND BROKEN FROM BARREL. REMAINDER OF CYLS VISUALLY INSPECTED WITH NO DAMAGES FOUND. CYL NR 3 ASSY. REPLACED WITH OVERHAULED UNIT. - GROUND RUN SATISFACTORY. RERUN TO AWD 78-08-07 (VISUAL INSP.) CYLINDER FAILURE IS NOT UNHEARD OF ON THESE AIRPLANES                                                                                                                                                                                                                                                                                                                                                         1H71 3R3  RRCA806    5E1                  
             20081113     SO  2008       11         13         CA080711012      120080705G8011MHB4016R        STARTER                                 PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA                                              INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            48                                                        (CAN) THE STARTER WOULD NOT WORK AT ALL, REPLACED WITH A SERVICEABLE STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA                
             20081113     EA  2008       11         13         CA080712001      120080711G32402604141         HOUSING                                 CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE                              BRAKE PISTON    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1057                                                      (CAN) DURING NDT AT OVERHAUL, 2 CRACKS DISCOVERED AT BOTTOM OF PISTON BORE IN BRAKE HOUSING. THESE HOUSINGS ARE NDT`D AT OVERHAUL AND EVERY BRAKE LINING CHANGE PER THE BF GOODRICH MANUAL 32-48-24 PAGE 512.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4R4  RRTA14EA   E231                 
             20081113     CE  2008       11         13         CA080714001      120080708G5343                TRUNNION                                CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              MISINSTALLED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  ATTACHMENT HARDWARE THAT WAS FOUND INSTALLED IN THE CHANNEL-TRUNION BRACE WAS NOT WHAT IS CALLED FOR IN ACFT I.P.C. 53-11-01 01 .THE INSTALLED HARDWARE WAS 4 AN3-5A BOLTS WITH AN960-3 WASHERS UNDER BOTH THE HEAD OF THE BOLTS AND UNDER THE NUTS. THE LENGTH OF THE BOLT AT THE FORWARD LT CORNER OF THE CHANNEL-TRUNION BRACE WAS TOO LONG WHEN INSTALLED AND INTERFERED WITH THE AFT TRAVEL OF THE STEERING ARM LOCATED JUST BELOW THE CHANNEL-TRUNION BRACE SUPPORT ASSEMBLY. THE I.P.C. CALLS FOR 4MS27039-1-07 SCREWS AND 4 MS21042-3 NUTS (NO WASHERS ARE CALLED FOR IN THE INSTALLATION).                                                                                                                                      1L72 4F4  F  A22CE   E1NE                 
             20081113     SO  2008       11         13         CA080714003      120080714G81204091709001      TURBOCHARGER                            PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              ENGINE          FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       800                                                            (CAN) RT TURBOCHARGER FAILED SHORTLY AFTER T/O. ENGINE SHUTDOWN AND ACFT RETURNED TO AIRPORT FOR AN UNEVENTFUL LANDING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A20SO   E14EA                
             20081113     NM  2008       11         13         CA080714004      120080712G8097                WIRE                                    AIRBUSA319  A319114     3930350NM  CFMINTCFM56 CFM565A1         NE                              START VALVE     DAMAGED         W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE FROM TORONTO DURING THE CLIMB, THE CREW STARTED RECEIVING UNEXPECTED ECAM MSGS REGARDING THEIR NR 2 ENGINE. THE CLIMB WAS STOPPED AT FL230 WHERE THE CREW TRIED TO WORK OUT THE ECAM ITEMS WITH MX. THE ENGINE LOST ALL POWER AND WAS SHUT DOWN. THERE WAS NO FIRE WARNING. THE FLIGHT RETURNED TO TORONTO WHERE AN UNEVENTFUL OVERWEIGHT LANDING TOOK PLACE. THERE WAS NO ADVERSE PASSENGER REACTIONS REPORTED BY THE FLIGHT CREW.                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA28NM   E29NE                
             20081113     EA  2008       11         13         CA080714005      120080708G1400TBC6EM106727    BOLT                                    DHAV  DHC6  DHC6        2802606EA                                                               DRAIN VALVE     MISMANUFACTURED W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) TBAL HAD A CUSTOMER REPORT OF THE LOCK WIRE TEARING THROUGH THE LOCK WIRE HOLE DURING INSTALLATION ON 2 OF THE 4 PURCHASED DRAIN VALVE BOLTS.  ALL BOLTS IN STOCK WERE PULLED FROM THE SHELF AND EXAMINED. THE BOLTS CONFORMED TO THE TBAL DRAWING. THE BOLTS THAT WERE ON THE 1 END OF THE TOLERANCE WERE CLOSE TO THE EDGE. AN OEM BOLT WAS PURCHASED AND COMPARED TO TBAL DRAWINGS. THE LOCK WIRE HOLE WAS CLOSER TO THE EDGE OF THE HEAD ON THE TBAL PART WHEN COMPARED AGAINST THE OEM. A TOTAL OF 11 BOLTS WERE SOLD. THE CUSTOMER WITH THE 2 OF 4 BOLTS IS RETURNING 2 BAD ONES AND USING THE 2 GOOD ONES. WE ARE IN THE PROCESS OF CONTACTING THE REMAINING 4 CUSTOMERS WHO HAD PURCHASED THE BOLTS TO ADVISE THEM OF THE PROBLEM.1H72 3T    RTA9EA                         
             20081118         2008       11         18         CA080714006      420080714G2565                LINE            BFGOODRICH                                                                                                              ESCAPE SLIDE    MISROUTED       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) FIRST VISIT IN SLIDE SHOP OF THE ERJ-175 SLIDE S/N ED0522 FTN 4W94YL DURING THE INCOMING INSPECTION IT WAS DISCOVERED THAT THE FOLLOWING PROBLEMS WOULD HAVE PREVENTED THE DEPLOYMENT OF THE SLIDE EITHER MANUALLY OR AUTOMATICALLY.  CORD WAS FORGOTTEN ON THE SPEED LACING LOOP THUS PREVENTING AUTO DEPLOY. PHOTO FIG. 1  THE MANUAL FIRING LINE WAS NOT ROUTED PROPERLY. PHOTOS ARE FIG. 2 AND 3.                                                                                                                                                                                                                                                                                                                                                                               
             20081110     GL  2008       11         10         CA080714007      220080711G72509362M43P02      TURBINE WHEEL                                                              GE    CF6   CF680C2*         GL                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4522213716                                                     (CAN) DURING SHOP INSPECTION CRACKS FOUND ON FWD DOVETAIL SEPARATIONS IN EXCESS OF MANUAL LIMITS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      4  F          E23EA                
             20081110     EA  2008       11         10         CA080714008      120080710G2820                SLEEVE          GE                      CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              WORN            W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DEFECT: ON CLIMB OUT, "L FUEL LO PRESS" MSG WAS ON AS PER DEFECT 309471. THE "L EJECTOR MAIN" EICAS MASTER CAUTION CAME ON AND L ENGINE RUNNING ROUGH. "FUEL IMBALANCE" EICAS CAME ON, CENTER FUEL TANK NOW @ 1600 LBS. LT ENGINE SHUT DOWN CARRIED OUT.  RECTIFICATION: AFTER INVESTIGATION, FOUND A COUPLING DISCONNECTED ON MAIN LT ENGINE FUEL FEED LINE LOCATED IN THE CENTER TANK. REASON WHY THE CENTER TANK WAS @ 1600 LBS AND CAUSED AN IMBALANCE.   FOUND SLEEVE/COUPLING DAMAGED.  NEW COUPLING ASSEMBLY REINSTALLED PROPERLY ON ENGINE FUEL FEED LINE, ENGINE RUNS, LEAK CHECK CARRIED OUT AND ACFT BACK IN SERVICE                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20081110     NM  2008       11         10         CA080715001      120080625G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              HYDRAULIC SYS   FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       4584                                                           (CAN) DURING CRUISE FLIGHT EDP NR 1 FAILED AND HYDRAULIC PRESSURE WAS LOST. SPU TURNED ON THEN TURNED OFF DUE TO LOSS OF HYDRAULIC FLUID NR 1 SYSTEM. ACFT LANDED AT DESTINATION AIRPORT WITHOUT INCIDENT.   GROUND INSPECTIONS REVEALED METAL IN CASE DRAIN FILTER. EDP REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E00062EN             
             20081110     CE  2008       11         10         CA080715002      120080715G534204310093        ATTACH FITTING                          CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL                  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       11005                                                          (CAN) LT ATTACH FITTING CRACKED AT LOWER OUTSIDE RADIUS ADJACENT TO AN 4-6A ATTACH BOLT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081112     CE  2008       11         12         CA080715003      120080702G2421                COMMUTATOR      KELLY                   CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO                              ALTERNATOR      FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        H  ELECT. POWER LOSS-50 PC                                                       DEDESCENT        1                      CA            289                                                       (CAN) FLIGHT CREW NOTICED THE ALTERNATOR WAS NOT CHARGING ON DESCENT. UPON CLOSER INSPECTION IT WAS FOUND THAT THE COMMUTATOR AND BRUSHES WITHIN THE RECENTLY O/H ALTERNATOR SHOWED SIGNS OF SIGNIFICANT ABNORMAL WEAR.  THE ALTERNATOR WAS LOW TIME AND HAD NOT GONE THROUGH ITS 500 HR INSPECTION YET SO IT WAS DETERMINED THAT THE WEAR HAD BEGUN FROM THE TIME OF O/H.  THE ALTERNATOR WAS REPLACED WITH ANOTHER O/H ALTERNATOR & RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                      1H71 3O3  O  A4CE    E5CE                 
             20081112     EU  2008       11         12         CA080715004      120080714G242131342001        SHAFT                                   SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F25 NE  GENERATOR       SHEARED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        J  WARNING INDICATION                                                            CRCRUISE         1                      CA            418                                                       (CAN) RT AC GENERATOR FAIL LIGHT ILLUMINATED IN FLIGHT, SYSTEM WAS DEFERRED AS PER THE MEL. WHEN ACFT WAS AT A MX BASE, THE AC GENERATOR WAS REMOVED AND FOUND TO HAVE A SHEARED SHAFT. GENERATOR WAS REPLACED. NO FURTHER ISSUES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20081112     EU  2008       11         12         CA080715005      120080711G5415417157001       BRACKET                                 SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101*          NE                              FUEL FILTER     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       175                                                            (CAN) DURING THE 100 HRS INSPECTION ON THE ENGINE, THE AME DISCOVERED 2 CRACKS ON THE ENGINE HIGH PRESSURE FUEL FILTER SUPPORT, 1 AT THE TOP AND 1 AT THE BOTTOM ASSEMBLY HOLDING HOLES GOING FROM EACH HOLE TO THE EDGE OF SUPPORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  UNCH9EU    E5NE                 
             20081112     SO  2008       11         12         CA080715006      220080708G8530                STUD            SUPERIOR                CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO                              CYLINDER HEAD   FAILED          W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      CA            735                                                       (CAN) A COMPLETE SEPARATION OF THE CYLINDER HEAD FROM THE BARREL OCCURRED. THE SEPARATION SEEMED TO HAVE STARTED IN THE EXHAUST PORT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  A4CE    E5CE                 
             20081112     SW  2008       11         12         CA080715007      120080715G6410206011809005    PITCH HORN      BELL                    BELL  206   206B        1181511SW  ALLSN 25OC  250C20R          GL                              T/R HUB         DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE PITCH HORN STUD FAILED WHILE INSTALLING A NUT P/N MS14145L5. A "CLICKER-TYPE" TORQUE WRENCH SET TO 60 INCH/LBS WAS USED TO INSTALL THE NUT. THE REQUIRED FINAL TORQUE FOR THIS NUT IS 50-60 INCH/LBS PLUS TARE. THE TIGHTENING TORQUE NEVER REACHED 60 INCH/LBS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
             20081112     CE  2008       11         12         CA080716001      120080715G212199101133        COOLING FAN                             CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              NOISY           W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOOD COOLING FAN NOISY.  FUNCTIONAL CHECK CONFIRMED SNAG, UNIT REMOVED FROM ACFT AND REPLACED WITH OVERHAULED UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 4F4  F  A22CE   E1NE                 
             20081112     EA  2008       11         12         CA080716002      120080710G2810K215T640024     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              NR 4            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) FUEL LEAK FROM RT WING. CHANGED NR4 RT PN-K215 T64002-4 SN 89306.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA14EA   E20NE                
             20081112     EU  2008       11         12         CA080716003      120080714G5415417157001       BRACKET                                 SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101*          NE                              FUEL FILTER     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       790                                                            (CAN) CRACK DISCOVERED DURING ENGINE VISUAL INSPECTION ON THE HIGH PRESSURE FUEL ASSEMBLY SUPPORT, CRACK ON THE TOP HOLDING HOLE, FROM HOLE TO THE EDGE OF SUPPORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  UNCH9EU    E5NE                 
             20081112     EU  2008       11         12         CA080716004      120080624G6220350A31182703    FREQ ADAPTER                            SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              MAIN ROTOR HEAD WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       5299                                                           (CAN) WORN TO SERVICEABLE LIMITS, RUBBER DEBONDING FROM ITS METHC SURFACE. REPLACED WITH A NEW SET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H9EU    E19EU                
             20081112     EU  2008       11         12         CA080716007      120080707G5350                FAIRING                                 AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  FUSELAGE        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FIRST AIR HAS OBSERVED SEVERAL OCCURRENCES OF DEGRADATION IN THE SURFACE PROTECTION COATING ON THE ACFT LOWER CENTER SECTION FAIRING PANELS. THE MATERIAL IS APPLIED IN ACCORDANCE WITH ATR SERVICE BULLETIN ATR42-53-0102. INVESTIGATION HAS FOUND THAT THE DEGRADATION APPEARS TO BE ATTRIBUTED TO FLUID CONTAMINATION FROM THE HYDRAULIC SYSTEMS WHICH ARE HOUSED WITHIN THE LANDING GEAR BAY AREA WHICH IS FAIRED IN BY THE AFFECTED PANELS.                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20081112     NM  2008       11         12         CA080716008      120080714G2781H1010271        POSITION SWITCH                         BOEING727   727243      138408DNM  PWA   JT8   JT8D9A      52048NE                              NR 6 L/E SLAT   MALFUNCTIONED   W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 APAPPROACH       1                      CA            1450                                                      (CAN) ON APPROACH AN IN-TRANSIT INDICATION WAS ILLUMINATED ON THE NR 6 L/E SLAT. THE CREW ELECTED TO RETURN TO VANCOUVER WHERE THEY LANDED WITHOUT INCIDENT. INSPECTION REVEALED THAT THE NR 6 L/E SLAT WAS FUNCTIONING CORRECTLY BUT THE L/E SLAT POSITION SWITCH WAS UNSERVICEABLE. THE SWITCH WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  FRTA3WE    E2EA                 
             20081112         2008       11         12         CA080716009      420080716G2562E01G            G SWITCH                                                                                                                                ELT             STICKING        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ANNUAL BENCH RECERTIFICATION OF ELT, THE OPS OF THE G-SWITCH WAS TESTED AND FOUND TO BE STICKING INTERMITTENTLY.  THE G- SWITCH WAS REPLACED AND OPS WAS TESTED SEVERAL TIMES TO ENSURE NEW G SWITCH IS OPERATING CORRECTLY.  NO FURTHER PROBLEMS NOTED                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      
             20081112     GL  2008       11         12         CA080717001      220080705G732323076061        GOVERNOR                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              TURBINE         MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            246                                                       (CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H2SW    E4CE                 
             20081112     WP  2008       11         12         CA080717002      120080714G6310C0512REVU       ACTUATOR                                ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CLUTCH          INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1067                                                           (CAN) THE CLUTCH WOULD NOT ENGAGE, FERRY FLIGHT PERMIT APPROVED AND ACFT RETURNED TO BASE. THE MICROSWITCH WAS FOUND FAULTY, CLUTCH ACTUATOR R&R WITH A SERVICEABLE ACTUATOR                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
             20081112     NM  2008       11         12         CA080717003      120080716G534717003263001     SEAT TRACK                              EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5800                                                           (CAN) EVIDENCE OF CORROSION FOUND AT SEVERAL AREAS.  REFERENCE: J/C NR Z220-005-U & NON-ROUTINE NR 46, 48 CORROSION FOUND ON FLOOR BEAM LOCATED AT Y = 225.0 AND Z = -490.0 JUNCTION WITH FRAMES 17 AND ON FLOOR BEAM LOCATED AT Y = -255.0 AND Z = -490.0 JUNCTION WITH FRAME NR 19.  SEAT TRACKS AFFECTED: P/N 170-03264-001 AND P/N 170-03263-001                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA56NM   E00063EN             
             20081112     EU  2008       11         12         CA080717005      120080715G6730SC5083SN2353    SERVO                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA       2017                                                           (CAN) ON A EUROCOPTER AS350 B2  DURING HYDRAULIC TEST PROCEDURES FOR FIRST FLIGHT OF THE DAY THE PILOT ENCOUNTERED THE CYCLIC BEING DRIVEN HARD OVER TO THE LT STOP. DURING TROUBLESHOOTING THIS PROBLEM WAS NOT EASILY REPEATABLE EVERYTIME THE TEST WAS COMPLETED. REMOVAL OF THIS COMPONENT HAS SO FAR REMOVED THE ISSUE. THE SERVO HAS BEEN SENT OUT FOR TEST AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H9EU    E19EU                
             20081112     SW  2008       11         12         CA080718001      120080713G6230                BEARING                                 BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              M/R MAST        DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            HOHOVERING       1                      CA       6478 17                                                        (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED AND THE TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. THE PIC DISCONTINUED ANY FURTHER OPS AND PROCEEDED TO LAND NORMALLY IN AN ADJACENT CUT BLOCK. A POST-SHUTDOWN INSPECTION BY THE AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS IN THE OIL SYSTEM AND OIL FILTER. FURTHER DISASSEMBLY AND INSPECTION OF THE OIL SUMP SCREEN AND SUBSEQUENT REMOVAL OF THE OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT THE ORIGIN OF THE MATERIAL COULD NOT DETERMINED.  DURING THE FIELD REMO1G71 4U4  U  H1SW    E17EA                
             20081112     EU  2008       11         12         CA080718002      120080715G32225322012289      DRAG LINK                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  TAIL GEAR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7560                                                           (CAN) THIS IS THE 4TH LINK WE HAVE FOUND CRACKED IN OUR FLEET IN SAME LOCATION. PLEASE SEE PREVIOUS SDR`S FOR PICTURES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081112     EA  2008       11         12         CA080718003      120080712G5610NP139322001     WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) FLT NR 5820, CAPTAINS SIDE WINDSHIELD CRACKED. WINDOW CRACKED FROM LOWER LT CORNER TO UPPER RT CORNER. CALLED AMERICAN EAGLE AND THEY DETERMINED IT WAS THE INNER PLY. ACFT TO FERRY IN THE MORNING TO COS.  CAPTAIN SIDE WINDSHIELD R&R.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
             20081112     EU  2008       11         12         CA080718004      120080717G3251176SF2DT102W0162POTENTIOMETER                           DORNERDO228 DO228202    2992030EU  GARRTTTPE331TPE331*     01514WP                              STEERING        MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 H  ELECT. POWER LOSS-50 PC                                                       TOTAKEOFF        1                      CA       7                                                              (CAN) ON TAKE OFF ACFT ROTATED PILOT FELT SOMETHING ABNORMAL IN RUDDER PEDALS, SELECTED GEAR UP , GEAR HANDLE WOULD NOT MOVE, PILOT OBSERVED GEAR HANDLE LOCK STILL IN PLACE. ACFT FLOWN BACK TO BASE , PILOT DID A LOW FLYBY WHERE IT WAS CONFIRMED THAT THE NOSE GEAR STEERING WAS ALL THE WAY TO THE LT.  ACFT LANDED SAFELY UPON NOSE TOUCHED DOWN IT CENTERED ITSELF AND WAS TAXIED BACK USING ENGINE DIFFERENTIAL POWER. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE STEERING POTENTIOMETER HAD FAILED CAUSING THE NOSE GEAR TO GO LT DISENGAGING THE NOSE GEAR STEERING NOT ALLOWING THE NOSE GEAR CENTERING SWITCH TO CENTER GEAR FOR GEAR RETRACTION.                                                                             2H72 4T3  TRTA16EU   E2WE                 
             20081112     EA  2008       11         12         CA080718005      220080714G731491380003        PUMP                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            3516                                                      (CAN) AFTER REPLACING THE ENGINE, A LEAK CHECK WAS COMPLETED AND IT WAS FOUND THAT THE LP FUEL PUMP WAS LOOSING FUEL OUT THE VENT LINE. THE PUMP WAS REPLACED WITH NO FURTHER PROBLEMS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4T4  T  A24CE   E4EA                 
             20081112     NE  2008       11         12         CA080718006      220080714G8530127951          WASHER                                  CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE                              INTAKE VALVE    BROKEN          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            1188                                                      (CAN) DURING AN OIL LEAK REPAIR ON THE R2800 RT ENGINE, IT WAS DISCOVERED THAT THE ROCKER CAP ON CYLINDER NR 4 WAS CRACKED. CAP WAS REMOVED AND FOUND THAT 1/3 OF THE INTAKE VALVE UPPER WASHER WAS BROKEN OFF AND THE PIECE WAS LAYING IN THE ROCKER BOX AREA. INSPECTION REVEALED THAT THE WASHER PIECE HAD BEEN PUSHED AROUND THE ROCKER BOX AREA, CRACKING THE ROCKER CAP, DAMAGING THE INTAKE VALVE SPRING, AND SCRATCHING THE INTERIOR OF THE ROCKER BOX AREA.  MAIN ENGINE OIL SCREEN WAS CHECKED FOR CONTAMINATION. SMALL AMOUNT OF NON FERROUS METAL FOUND IN SCREEN. SCREEN CLEANED AND RE-INSTALLED. NR 4 CYLINDER WAS REPLACED WITH AN OVERHAULED UNIT. ACFT RUN UP, ENGINES CHECKED FOR POWER AND LEAKS, AND ACFT WAS RETURNED TO S2H72 4R4  RRTA14EA   E231                 
             20081112     SW  2008       11         12         CA080718007      120080717G6320206040184001    PUMP                                    BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              TRANSMISSION    DISLODGED       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  HOHOVERING       1                      CA            28                                                        (CAN) THE SEAL FOR THE TRANSMISSION OIL PUMP BECAME DISLODGED, AND LOSS OF OIL OCCURRED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E4CE                 
             20081112     CE  2008       11         12         CA080721001      120080714G4997                WIRE                                    LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              APU             CHAFED          W      F   ACTIVATE FIRE EXT.                                                                              N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA       30                                                             (CAN) PATS APU INSTALLATION STC SA95-34 FIRE WARNING AFTER 20 MIN OF APU OPERATION PRIOR TO ENGINE START. APU AUTO SHUTDOWN AND FIRE EXT FIRED. VISUAL INSPECTION OF EXTERIOR OF APU ENCLOSURE SHOWED NO EVIDENCE OF FIRE. APU REMOVED AND FOUND WIRES APU2002-20B, APU200-20A AND APU1019-16 CHAFED. APU2000-20A HAD SHORTED TO  FIRE LOOP IN 2 LOCATIONS RESULTING IN ARCING AND OVERHEAT OF THE LOOP IN THAT LOCATION. ALL WIRING REPLACED, HIGH TEMP SPIRAL WRAP INSTALLED TO PROTECT WIRING. BOMBARDIER ADVISED VIA FIELD SERVICE REP.                                                                                                                                                                                                     2L72 4F4  FRTA10CE   E35NE                
             20081112     CE  2008       11         12         CA080721003      120080721G555226340231        FITTING         CESSNA                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              BEARING SUPPORT DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE MOVEMENT OF THE ELEVATOR WAS NOTED AS NOT BEING `SMOOTH`. ON INVESTIGATION IT WAS FOUND THAT THE BEARING IN THE SUPPORT BRACKET WAS SEIZED AND THAT THE SUPPORT BRACKET ALSO HAD CORROSION. THE BRACKET (AND BEARING) WILL BE REPLACED WITH NEW BEFORE NEXT FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3T3  T  A37CE   E4EA                 
             20081112     WP  2008       11         12         CA080721005      120080721G6310C0511           ACTUATOR                                ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CLUTCH          DAMAGED         W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) DURING 100 INSPECTION AND ACTUATOR FUNCTION TEST, 1 OF THE COLUMN SPRINGS SWITCH DID NOT RESPOND. FANWHEEL ASSY REMOVED AND SWITCHES CHECKED MANUALLY AND FOUND SERVICEABLE. IT SEEMS LIKE THE SPRINGS ON 1 SIDE DID NOT PUSH THE SWITCH COMPLETELY AND THERE WAS ONLY 1 SWITCH ACTIVE. ACTUATOR ASSEMBLY SENT TO R.H.C.                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   E295                 
             20081112     SW  2008       11         12         CA080722001      120080713G6320                BEARING                                 BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              M/R MAST        DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            HOHOVERING       1                      CA       6478 17                                                        (CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. A POST-SHUTDOWN INSP BY AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS IN THE OIL SYS AND OIL FILTER. FURTHER DISASSEMBLY AND INSP OF OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT ORIGIN OF THE MATERIAL COULD NOT DETERMINED.  DURING THE FIELD REMOVAL OF THE TRANSMISSION, IT WAS DISCOVERED THAT THE LOWER BEARING RACE RETAINING NUT ON THE MAST ASSY HAD BROKEN FREE OF IS TORQUE AND LOCKING DEVICE. NUT BACKED OFF ALL THE WAY TO LAST THREAD CARVING A ONE INCH DEEP GROO1G71 4U4  U  H1SW    E17EA                
             20081112     EU  2008       11         12         CA080722002      120080707G2731EM40112         ACTUATOR        PIAGIO                  PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A66      52043NE  HARTZLHCE5N HCE5N3      GL  ELEVATOR TRIM   MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA            605                                                       (CAN) THE HORIZONTAL STABILIZER PRIMARY TRIM FAILED IN THE DOWN MODE ONLY. THE ACFT THEN PROCEEDED TO THE NEAREST AIRPORT. MAINT CONFIRMED THE SNAG ON THE GROUND. AFTER REPLACING THE HORIZONTAL TRIM ACTUATOR THE SYS FUNCTIONED NORMAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3O4  TRTA59EU   E26NE   5  CPZONE    
             20081112     EU  2008       11         12         CA080722003      120080716G6310350A351069      GIMBAL PIN                              SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                                              DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ACFT WAS INSPECTED FOLLOWING A HARD LANDING, MAIN AND TAIL ROTOR STRIKES IAW  MET 05.53.00.603, 604 AND 605. GIMBAL PINS (ALL 4 OF THEM) WERE SENT ALONG WITH OTHER PARTS FOR NDT (NO REQUIREMENT TO CHECK THE GIMBAL PINS AFTER AN INCIDENT), AND 3 OF 4 WERE FOUND TO HAVE CRACKS IN THE FLANGED END, CAUSING REJECTION OF THE 3 PINS.  PINS ARE PART OF ENG TO MAIN GEAR BOX COUPLING, HOLDING COUPLING TUBE TO GIMBAL RING AND GIMBAL RING TO ROTOR BRAKE HSG.  DAMAGED ACFT HAS YET TO BE REASSEMBLED TO FLIGHT CONDITION).                                                                                                                                                                                                          1G71 3U3  U  H9EU    E19EU                
             20081112     NE  2008       11         12         CA080722004      220080718G7314                SEAL                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  FUEL PUMP       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       4973                                                           (CAN) ON DAILY INSP, FUEL WAS DISCOVERED IN THE OIL SEAL DRAIN COLLECTOR CAN. FURTHER INVESTIGATION FOUND FUEL LEAKING FROM THE SEAL ON THE FUEL HIGH PRESSURE PUMP. THERE WAS NO INDICATION OF GREASE WASH OUT OF THE FCU BRG. THE FUEL PUMP WAS REPLACED WITH A SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081230     EU  2008       12         30         CA080722005      120080716G6230350A37122021    STOP            TMECA                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              M/R SHAFT       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       6074                                                           (CAN) ON ROUTINE MAST RECONDITIONING AND INSP (6 YEAR INSP REQUIREMENT), THE RING WAS SENT FOR NDT ALONG WITH THE REST OF THE PARTS FROM THE ASSY (NO NDT REQUIREMENT FOR THE RING AT ANY POINT, OR FOR ANY PART OF THE ASSY AT THE 6 YEAR INSP). THERE WAS A STRESS CRACK DURING MPI CHECK, WHICH WAS CAUSE FOR REJECTION OF THE PART.  THE RING IS LOCATED AT THE TOP OF THE MAIN ROTOR SHAFT, WHERE THE ROTOR HEAD ATTACHES, AND ROTATES WITH THE MAIN ROTOR SHAFT/HEAD. THE CUSTOMER WAS NOTIFIED OF THE DEFECT AND THE PART WAS REPLACED.                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
             20081112     EA  2008       11         12         CA080722007      120080718G5700C6FSM244335     BUSHING                                 DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  WING LUG        MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BUSHINGS MISSING FROM WING PICKUP LUGS ON ORIGINAL FRAMES INSTALLED IN ACFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081112         2008       11         12         CA080722008      220080722G7414M3548           ROTOR                                                                                                                                   MAGNETO         BROKEN          W      K   NONE                                                                                            P  NO WARNING INDICATION                                                         ININSP/MAINT     1                      CA       364                                                            (CAN) MAGNETO INSPECTED FOR SB 2-08/3-08 COMPLIANCE. DISTRIBUTOR GEAR FAILED, ROTOR GEAR FAILED, CARBON BRUSH FAILED. DURING REMOVAL OF ROTOR GEAR FOR REPLACEMENT, BROKEN POST LODGED IN GEAR. DISTRIBUTOR GEAR AND ROTOR GEAR WERE HOLDING THE BROKEN POST IN PLACE DURING OPERATION. EDGE OF BROKEN POST WAS WORN INDICATING BREAK OCCURRED SOME TIME AGO.                                                                                                                                                                                                                                                                                                                                                                                                                             
             20081112     NE  2008       11         12         CA080722009      120080722G7603S6130620173     THROTTLE PLATE                          SKRSKYS61   S61A        814210CNE                                                                               FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) S61 ENGINEERS WERE REPLACING A EMERGENCY THROTTLE PLATE P/N S6130-62017-3 WITH A PLATE THAT HAD BEEN RECEIVED. ON INSTALLATION WHEN TIGHTENING THE BOLTS, THE PLATE SHATTERED AT THE FWD BOLT HOLE. ALL 10 PLATES RECEIVED IN FROM THIS VENDOR HAVE BEEN ACCOUNTED FOR AND ARE IN QUARANTINE. PRELIMINARY INSP OF THE PART HAVE REVEALED THE FOLLOWING:  DEFECTIVE PLATE WAS IDENTIFIED WITH THE PROPER P/N IAW THE S61 IPC FIGURE 118 ITEM 25 AND APPEARED TO MEET FIT FORM AND FUNCTION.  A TEST DONE ON ONE OF THE PLATES REMOVED FROM SERVICE WHICH INDICATED THE PART TO BE FERROUS, HOWEVER WAS EXTREMELY BRITTLE AS IT FAILED INSTANTLY UNDER MINIMAL PRESSURE WITHOUT BENDING. SUSPECTED BOGUS PARTS.                             2G72 4U      H2EA                         
             20081112     NM  2008       11         12         CA080723001      120080720G32607002537         CONTROL UNIT                            DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  MLG             MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 LDLANDING        1                      CA       673                                                            (CAN) LANDING GEAR INOPERATIVE CAUTION LIGHT ILLUMINATED DURING DESCENT, LIGHT WAS CONTINUOUS ALL THE WAY BACK TO BASE. REMOVED AND REPLACED ADVISORY CONTROL UNIT IAW AMM 33-13-00. PERFORMED LANDING GEAR RETRACTION TEST-RESULTS SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081112     NE  2008       11         12         CA080723002      220080708G7261                RETAINING NUT                                                              PWC   PW308 PW308C      52182NE                              OIL PUMP ASSY   DISLODGED       W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       791                                                            (CAN) THE LOW OIL PRESSURE WARNING ACTIVATED DURING TAKEOFF ROLL AND TAKEOFF WAS ABORTED. SUBSEQUENT INSP REVEALED THE OIL PUMP GEARSHAFT RETAINING NUT AND TAD WASHER COMPLETELY DISLODGED FROM THE SHAFT. MFG WILL INVESTIGATE TO REVIEW ASSY PROCEDURES AND REPORT ON ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                  4  F          E00065EN             
             20081112     GL  2008       11         12         CA080723003      320080718G6111                SEALANT                                 AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  BLADE CLAMP     FAILED          W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB OUT PILOT EXPERIENCED A BUILD UP OF GREASE ON WINDSHIELD. PILOT ABORTED LOAD IN DESIGNATED AREA AND RETURNED TO BASE. UPON INSP GREASE APPEARED TO BE COMING FROM 1 OR 2 BLADE CLAMPS. BLADE CLAMP SEALS WERE REPLACED IN BOTH UNITS. NO OBVIOUS DAMAGE WAS FOUND ON REMOVED SEALS OR PROP ASSY. SEALANT MAY HAVE FAILED. ACFT WAS RETURNED TO SERVICE AFTER GROUND FUNCTION CHECKS.                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
             20081112     EU  2008       11         12         CA080723004      120080527G6710350A27134320    STOP                                    AEROSPAS355 AS355F2     8680812EU  ALLSN 250C  250C20B     03013GL                              COLLECTIVE      DAMAGED         W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT WAS CLIMBING AT APPROX 6000` ASL. (OAT 1C). COLLECTIVE HIT ITS UPPER STOP DURING A POWER INCREASE. AT THIS POINT TORQUE READING WAS APPROX 65 PERCENT. T4 AND NG WERE WELL WITHIN MAX CONTINUOUS LIMITATIONS.  ON 14 MAY 2006, SB 67.00.12 REV. 2 WAS CARRIED OUT ON THE ACFT. THIS MODIFICATION INVOLVED THE INSTALLATION AND POSITIONING OF A NEW STOP PLATE ON THE UPPER PART OF THE COLLECTIVE QUADRANT. POSITIONING THIS STOP PLATE (P/N 350A27-1343-20) IAW INSTRUCTIONS PROVIDED IN SB 67.00.12 REV. 2 PARAGRAPH 2.B.2 RESULTS IN THE UPPER COLLECTIVE TRAVEL BEING LIMITED. END RESULT WAS THE SERVO INPUT RODS UPWARD TRAVEL BEING LIMITED BY APPROX 6MM AT FULL COLLECTIVE. PARAGRAPH 2.B.3. OF SB 67.00.12 REQUIRES THAT 1G72 3U3  U  H11EU   E4CE                 
             20081112     EU  2008       11         12         CA080723005      120080722G2730Z4244120000     CABLE                                   ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA  MUHBR MTV   MTV9*       EU  ELEV TRIM TAB   FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1899                                                           (CAN) CABLE WAS DISCOVERED FRAYED DURING REGULARY SCHEDULED MAINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O0 A76EU   1E10    5  CP24NE    
             20081112     CE  2008       11         12         CA080723006      120080721G2421                ALTERNATOR                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL                  FAILED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, PILOT NOTICED KX155 NAV/COM FLASHING ITS DISPLAY AND VOR NEEDLE ERATIC. PILOT DECLARED NORDO AND LANDED SAFELY WITHOUT FURTHER INCIDENCE. MAINT ATTEPTED TO START ACFT AND DISCOVERED BATTERY ALMOST DEAD. ACFT CHARGING SYS HAD MALFUNCTIONED DURING FLIGHT AND PILOTS WERE UNAWARE OF THE PROBLEM. MFG INSTALLED AMMETER SHOWS VERY LITTLE NEEDLE DEFLECTION WHEN SYS IS OPERATING NORMALLY, EVEN UNDER HEAVY LOAD. ALSO, EARLIER 152`S WERE PROVIDED WITH AN OVERVOLT RED LIGHT ONLY. LATER 152S INCORPORATE AN UNDERVOLT LIGHT WHICH IS MORE USEFULL. MAINTENANCE CHARGED BATTERY AND REPAIRED BROKEN RING TERMINAL ON ALTERNATOR FIELD WIRE, ACFT RETURNED TO SERVICE.                                                1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081112     WP  2008       11         12         CA080724001      120080707G2822C81878          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL BOOST      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       610                                                            (CAN) FUEL PUMP WARNING LIGHT ILLUMINATED IN FLIGHT. AUX. PUMP HAD FAILED. ENGINE CONTINUED RUNNING ON MECHANICAL PUMP. A/C FLOWN TO MAINT BASE, ELECTRIC PUMP REPLACED. FUNCTION AND LEAK CHECK PERFORMED. CAUSE OF PUMP FAILURE UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
             20081112     WP  2008       11         12         CA080724003      220080717G723031037081        BEARING                                 SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33110UG  01514WP  MCAULY4HFR344HFR34C652  NE  COMPRESSOR      SPALLED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1917                                                           (CAN) SN OF THE PART IS MS030633106124 WAS UNABLE TO PUT THIS INTO SN FIELD.  A/C WAS DOWN FOR A ROUTINE OIL SAMPLE. AT THIS TIME THE OIL SAMPLE WAS NOTED TO HAVE A UNUSUAL AMOUNT OF METAL IN THE OIL SAMPLE. THE ENGINE SHOP WAS INFORMED TO HAVE A LOOK AT THE METAL AND IT WAS DETERMINED FROM ENGINE SHOP THAT THE ENGINE NEEDED REPAIR AT THAT TIME. UPON DISSASEMBLY OF THE ENGINE GEAR BOX IT WAS FOUND THAT THE COMPRESSOR BALL BEARING WAS STARTING TO HAVE METAL SPAWLING COMING FROM THE INNER RACE. THE ENGINE WAS REPAIRED ON WING AND WITH A NEW COMPRESSOR BEARING ALL METAL FLUSHED FROM ENGINE AND THE A/C WAS RETURNED TO SERVICE WITH NO MORE ISSUES.                                                                      2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081112     CE  2008       11         12         CA080724004      120080721G7720                INDICATOR                               BEECH 100   100BEECH    1152916CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ITT             MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) WHILE RETURNING TO HOME BASE AT CRUISE FLIGHT, FLIGHT CREW NOTICED THAT THE LT ITT GAUGE WAS ERRATIC. THERE WAS NO NOTICE IN ENGINE PERFORMANCE NOR WERE ANY OF THE REMAINING ENGINE INSTRUMENTS SUPPORTING ENGINE PERFORMANCE ISSUES. UPON RETURN TO BASE, MAINT TROUBLESHOT THE ITT SYS AND DISCOVERED THAT THE ITT HARNESS HAS 3000 OHMS TO GROUND WHERE THE MINIMUM LIMITS ARE 100000 OHMS. A NEW HARNESS HAS BEEN ORDERED AND WILL BE INSTALLED. THIS SDR HAS BEEN REPORTED PREVIOUSLY UNDER SDRS 20080103005 AND 20070223002. SUPPLEMENTARY SDR TO FOLLOW WITH ASSY AND PART FAILURE INFORMATION.                                                                                                                                  1L72 3T4  T  A14CE   E2WE    6  CP40EA    
             20081112     NE  2008       11         12         CA080724006      220080717G73210164548250      FUEL CONTROL                                                               TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       561                                                            (CAN) MAIN ROTOR RPM KEPT DECREASING AFTER ADJUSTMENT, OIL ALSO FOUND IN THE INPUT SEAL DRAIN TUBE. NO LONGER ABLE TO ADJUST IAW MM. UNIT REPLACED WITH SERVICEABLE FCU AND DEFECTIVE UNIT SENT TO MFG FOR INVESTIGATION AND WARRANTY REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          3  U          E19EU                
             20081112     WP  2008       11         12         CA080724007      120080722G3411                PITOT SYSTEM                            DOUG  DC6   DC6B        3021712WP  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  NR 2            CLOGGED         W      C   ABORTED TAKEOFF                                                                                 G  MULTIPLE FAILURE                                                              TOTAKEOFF        1                      CA                                                                      (CAN) BOTH NR 1 AND NR 2 PITOT SYS INDICATED NO AIRSPEED ON TAKEOFF RUN. TAKEOFF WAS ABORTED. BUGS AND SIMILAR DEBRIS FOUND IN BOTH PITOT SYS. APAR LINES BLOWN OUT, PITOT SYS FUNCTION CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L74 4R3  R  6A4     ATC14   6  CP871     
             20081113         2008       11         13         CA080724008      420080628G61221219310         PLUG            WOODWARD                DIAMONDA40  DA40        2990002GL                                   HARTZLHCC2Y HCC2YR1     GL  PROP GOVERNOR   FAILED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CLCLIMB          1                      CA       300                                                            (CAN) WE WERE CLIMBING OUT OF KSBM GOING THRU 4,000 FEET MSL, WHEN THE ENGINE/PROP OVER SPEEDED. IT TOPPED OUT AT SOMETHING OVER 3,100 RPM. IT TOOK ABOUT 5 TO 10 SECONDS TO GET THE POWER PULLED OFF. BY CAREFUL USE OF THE THROTTLE (2650 RPM MAX), WE WERE ABLE TO MAINTAIN FLYING SPEED, LEVEL FLIGHT AT ABOUT 80 TO 85 KTS.  DIVERTED AND DECLARED AN EMERGENCY. THE LANDING WAS ACCOMPLISHED WITHOUT ANY PROBLEMS AND NO FURTHER DAMAGE WAS SUSTAINED TO THE ACFT.   BEGAN THE INVESTIGATION INTO WHAT CAUSED THE FAILURE. AFTER ELIMINATING SOME OTHER PROBABLE CAUSES WE CAME TO THE PROPELLER GOVERNOR.  IT LOOKS AS IF A SCREW PLUG BACKED OUT OF AN INTERNAL PASSAGE WITHIN THE GOVERNOR, DUMPING THE OIL PRESSURE AND CAUSING THE PR1L71 3O    NTA47CE           5  CP920     
             20081112     CE  2008       11         12         CA080725001      120080709G246070002450        CIRCUIT BREAKER                         CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                              LT POWER FEED   TRIPPED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       261                                                            (CAN) LT POWER FEED CIRCUIT BREAKER (ONE OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA22CE   E00059EN             
             20081112     NE  2008       11         12         CA080725002      120080716G291366WAP2001       BOLT                                    SKRSKYS61   S61N        8142104NE  GE    CT58  CT581401    30011NE                              HYD PUMP        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON POST FLIGHT INSP, ONE BOLT HEAD WAS FOUND DETACHED FROM THE PUMP ASSY.  HAVE EXPERIENCED ONE PREVIOUS OCCURENCE, SEE SDR20060818006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2G72 4U4  U  1H15    1E3                  
             20090102     EU  2009       1          2          CA080725003      120080720G2910                HYDRAULIC SYSTEM                        UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                                              MALFUNCTIONED   W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      (CAN) AT GROUND IDLE, THE NORMAL PROCEDURE IS TO TEST ACCUMULATORS BY PUSHING THE ACCUMULATORS BUTTON ON, AND THE HYD LIGHT ILLUMINATES , AND PROCEED TO TEST THE ACTUATORS BY MOVING THE CYCLIC FWD AND AFT, ABOUT 4-5 INCHES TRAVEL, EIGHT TIMES, THEN RT AND LT, THE SAME. NORMAL (NORMALLY,  DO NOT TOTALLY DEPLETE THE ACCUMULATORS PRESSURE). THIS WAS NORMAL, NO PROBLEM ANY OF THE TEST OF THIS SYS AT ANY TIME. PUSH THE SWITCH AGAIN, AND THE ACCUMULATORS BACK ON, HYD LIGHT OUT.  THE HYD CUT OFF TEST. STILL OPERATING AT GROUND IDLE. COLLECTIVE LOCKED DOWN, SWITCHING OFF THE HYD SWITCH ON COLLECTIVE, HYD LIGHT ILLUMINATES, AND WHAT THE CYCLIC IS SUPPOSED TO DO IS PULL IT SELF TO THE CENTER NEUTRAL POSITION, WITH RESIS1G72 3U3  UNCR0001RD E34NE                
             20081112     NM  2008       11         12         CA080728001      120080723G243220412           BATTERY                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  MASTER          OVERTEMP        W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       14134594                                                       (CAN) DURING CRUISE THE CREW RECEIVED A MAIN BATTERY HOT WARNING MESSAGE. THE HIGH TEMP WAS CONFIRMED ON THE BATTERY TEMP MONITOR. THE CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT.  THE BATTERY TEMPERATURE WAS EVALUATED AT 180C. THE BATTERY COMPARTMENT WAS CLEANED, THE BATTERY REPLACED. ACFT WAS RELEASED AND RETURNED INTO SERVICE.  BATTERY HAS BEEN RETURNED TO THE COMPANY IN-HOUSE COMPONENT SHOP TO DETERMINE THE CAUSE OF THE THERMAL RUN-AWAY.                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081112     NM  2008       11         12         CA080728003      120080725G2710                PCU                                     BOEING727   727243      138408DNM  PWA   JT8   JT8D9A      52048NE                              AILERONS        FAILED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ENROUTE, CREW NOTICED HYD SYS (A) QUANTITY DECREASING RAPIDLY. SYS (A) HYDR WERE SHUTOFF AND EMERGENCY DECLARED. UPON ARRIVAL AT DESTINATION, A/C REQUIRED TOWING TO RAMP WHERE MAINT DISCOVERED THE AILERON PCU HAD FAILED. THE AILERON PCU WAS REPLACED AND A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L73 4F4  FRTA3WE    E2EA                 
             20081112     EU  2008       11         12         CA080728004      120080708G25308001060000LH    OVEN                                    AIRBUS310   A310304     3930339EU                                                                               DIRTY           W      A   UNSCHED LANDING                                                                                 WB INADEQUATE Q C            SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      CA       7873 5582                                                      (CAN) FLIGHT RETURNED TO THE STATION DUE TO CABIN SMOKE FROM FWD OVEN (DARK SMOKE). CABIN DETECTOR ACTIVATED. BOTH FWD OVENS INSPECTED AND ELECTRICAL CONNECTION CHECKED AND FOUND SERVICEABLE. LT OVEN INSERTS FOUND DIRTY (FOOD RESIDUE). OVEN REPLACED AND SERVICEABLE IAW MM25-30-00. OVEN ROUTED TO REPAIR SHOP FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA35EU                        
             20081112     EU  2008       11         12         CA080728005      120080721G2897NSA931322100    CIRCUIT BREAKER                         AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2A5        NE                              FUEL PUMP       BURNED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING TROUBLESHOOTING OF THE INOPERATIVE LT OUTER TANK FUEL PUMP (DEACTIVATED IAW MEL) THE CIRCUIT BREAKER 3QA WAS FOUND BURNED, BODY CRACKED AND ONE LEG MISSING. CIRCUIT BREAKER WAS REPLACED AND SYS TESTED SERVICEABLE. A DETAILED VISUAL INSPECTION CAMPAIN WAS INITIATED TO INSPECT ALL CIRCUIT BREAKERS IN THE 101VU ELECTRICAL PANEL.                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA35EU   E13NE                
             20081112     NM  2008       11         12         CA080728006      120080725G2897F759857SC       WIRE                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  SWITCH          CHAFED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA       4050140501                                                     (CAN) DURING TAXI, NR2 TANK FUEL LOW LEVEL CAUTION LIGHT ILLUMINATED. MAINT GROUND RUN AND NR2 TANK LOW LEVEL LIGHT INTERMITTENT. ACFT DISPATCHED UNDER MEL FOR FUEL LOW LEVEL INDICATION. LATER MAINT INSP DURING SWITCH REPLACEMENT, FOUND SWITCH WIRE CHAFED ON CONDUIT. SWITCH ASSY REPLACED. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND PART TIMES NOT TRACKED. TIME PROVIDED ARE ACFT TIMES).                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081112     SW  2008       11         12         CA080728007      120080722G5280                STRUCTURE                               SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  MLG DOOR        BENT            W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH PILOT EXTENDED GEAR AND HAD GREEN INDICATION FOR NOSE AND LT MAIN GEAR ONLY, INTRANSIT LIGHT WAS ON FOR RT GEAR. PILOT RECYCLED GEAR AND ALL 3 GREEN INDICATIONS WERE NOW PRESENT. ACFT LANDED WITHOUT FURTHER PROBLEMS. MAINT WAS CALLED AS THE RT GEAR DOORS WERE BENT JUST AFT OF THE FRONT HINGE. IT APPEARED THAT THE DOOR WAS HUNG UP ON THE FRONT EDGE OF THE GEAR DOOR AND WAS BENT WHEN THE GEAR WAS SELECTED DOWN.                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081112         2008       11         12         CA080728008      420080722G612231039391        FITTING                                 SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  PROP GOVERNOR   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON INSPECTION, IT WAS DISCOVERED THAT THERE WAS AN OIL LEAK AROUND THE RT ENGINE PROP GOVERNOR. UPON FURTHER INSPECTION IT WAS FOUND THAT THE FITTING WAS CRACKED HALF WAY AROUND THE FITTING.   FITTING REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081112     EU  2008       11         12         CA080728009      120080719G6410355A12004008    BLADE                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              TAIL ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2989 2989                                                      (CAN) FOUND T/R BLADE CRACKED NEAR TIP OF BLADE AND TRAILING EDGE ON DAILY INSPECTION. BLADE REMOVED FOR EVALUATION BY MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E19EU                
             20081112     SW  2008       11         12         CA080728010      120080704G6730212076005011    PILOT VALVE                             BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              LT CYCLIC       CHATTERING      W      A   UNSCHED LANDING                                                                                 EF VIBRATION/BUFFET          FLT CONT AFFECTED                                   CRCRUISE         1                      CA                                                                      (CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON ARRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCOMMANDED CYCLIC INPUTS. ACFT WAS GROUNDED. CYCLIC SERVO REPLACED, A/C TEST FLOWN AND WAS RELEASED FOR RETURN TO SERVICE. SUSPECT SERVO WAS SENT TO O/H FACILITY FOR EVALUATION, FOUND EXCESSIVE WEAR ON PILOT VALVE ASSY.                                                                                                                                                                                                                                                                        1G71 4U4  U  H4SW    E22EA                
             20081112     EU  2008       11         12         CA080729001      120080718G2120                GUARD                                   PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  REEFER PACK     CUT             W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) THE REFRIGERATION PACK MOTOR BELT SLIPPED ON THE MOTOR GEAR CAUSING THE WEAR ON THE GEAR. THE MOTOR GEAR LIP TO STOP THE BELT FROM GOING OUT OF THE GEAR IS WORN OUT ALSO, CHAFING THE BELT PLASTIC GUARD. THE GUARD IS CUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 4T4  TRTA78EU   E26NE   5  CP210NE   
             20081112     SO  2008       11         12         CA080729003      120080724G5310MS212505        BOLT                                    LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  FUSELAGE        FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       5040                                                           (CAN) ENROUTE, THE LOAD MASTER OBSERVED AN UNUSUAL SOUND FROM THE CARGO BAY AREA. UPON INVESTIGATION AN UNUSUAL GAP WAS NOTICED BETWEEN THE LANDING GEAR BAY WEB AND THE BOTTOM EDGE OF THE DRAG ANGLE VERTICAL FLANGE. THE GAP WAS ESTIMATED AT .125 FROM STA 570 TO 580. THE CREW ELECTED TO RETURN  WHERE THE ACFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED THAT AN APPARENT FASTENER FAILURE COMMON TO THE STA 577 BEAM AND THE DRAG ANGLE GENERATED THE GAP. THE ACFT WAS REPOSITIONED UNDER PERMIT WHERE FURTHER ASSESSMENT IS ONGOING.                                                                                                                                                                                            2H74 4T4  T  A1SO    E282    6  CP906     
             20081113     EU  2008       11         13         CA080729006      120080727G2913AIR29804        COVER           LKHEED                  BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU                              HYDRAULIC PUMP  LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) WHILE ENROUTE FROM YBK TO YTH FAMO EXPERIENCED LOSS OF HYDRAULIC PRESSURE. AN EMERGENCY WAS DECLARED AND THE ACFT DIVERTED TO YTH WHERE AN UNEVENTFUL LANDING WAS MADE. DURING THE FLIGHT HYDRAULIC PRESSURE WAS SEEN TO RISE AND FALL A NR OF TIMES. EMERGENCY U/C ACTUATION WAS NOT REQUIRED. UNDER INSPECTION THE RT HYDRAULIC PUMP WAS FOUND TO BE LEAKING. THE PUMP WAS CHANGED AND THE SYSTEM EXHIBITED NO DEFECTS DURING FUNCTION TESTING. THE PUMP WAS INSPECTED AND THE LEAK WAS FOUND TO BE FROM THE TOP EDGE OF THE END COVER THROUGH A NR OF PIN HOLES IN THE CASTING. THERE WERE NO LEAKS THROUGH THE PUMP FIXTURES AND FITTINGS. THE PUMP WILL BE SENT FOR STRIP EVALUATION.                                                2L72 3T4  T  A24EU   A196                 
             20081112     GL  2008       11         12         CA080729007      120080725G5730                SKIN                                    DIAMONDA40  DA40        2990002GL                                                               WING            DEBONDED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) A INSP CARRIED OUT ON WING, SHOWED GAPS IN THE SPAR TO SKIN BOND LINES. DO NOT BELIEVE THIS TO BE AN IMMEDIATE SAFETY ISSUE BUT ARE WORKING QUICKLY AND DILIGENTLY TO GET TO ROOT CAUSE AND CORRECTIVE ACTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O    NTA47CE                        
             20081112     NE  2008       11         12         CA080730001      220080623G72204037T84P03      NUT                                                                        GE    CF34  CF343B1     30070NE                              ENGINE          MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SHOP VISIT, ONE VARIABLE VANE SPINDLE NUT WAS FOUND MISSING ON STAGE 5 VANE. THE LEVER ARM REMAINED ENGAGED. A NUT WAS INSTALLED IAW THE ENGINE MANUAL 72-32-00 AS RECOMMENDED IAW SB 72-0184.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            4  F          E15NE                
             20081112     NM  2008       11         12         CA080730002      120080730G2611774001          SMOKE DETECTOR                          BOEING727   727225      1384077NM  PWA   JT8   JT8D15      52051NE                              NR 6            FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA            2774                                                      (CAN) ON CLIMB THROUGH FL290 CARGO SMOKE 6TH POSITION LIGHT ILLUMINATED AND FIRE WARNING BELL SOUNDED. ACFT RETURNED. ON ARRIVAL, NO SMOKE DETECTION LIGHTS WERE ILLUMINATED ON FE PANEL. CARGO AREA INSPECTED FOR SMOKE. NONE FOUND. SUSPECTED FAILURE OF NR 6 SMOKE DETECTOR. PART REMOVED AND REPLACED. SYSTEM FUNCTION CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F4  F  A3WE    E2EA                 
             20081112     SO  2008       11         12         CA080730003      220080730G8530                SPRING          ECI                                                        CONT  O520  IO520F      17032SO                              EXHAUST VALVE   BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13                                                             (CAN) CYLINDER WAS PULLED DUE TO LOW COMPRESSION. WHEN THE ROCKER COVER WAS REMOVED IT WAS DISCOVERED THAT BOTH THE INNER AND OUTER EXHAUST VALVE SPRINGS WERE BROKEN INTO MANY PIECES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                3  O          E5CE                 
             20081112     EA  2008       11         12         CA080730004      120080714G552285520056        SKIN                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4061940619                                                     (CAN) DURING MAINT, VISUAL INSP OF VERTICAL FIN/HORIZONTAL STABILIZER , A CRACK 2.25 INCHES LONG ENCOMPASSING (2) RIVETS AT RIB YH 13.80 EXTENDING FWD FROM A POINT3.5 INCHES FROM THE AFT T/E, WAS NOTED. DAMAGE REPAIR IAW REPAIR DRAWING RD8-55-1968 AND SRM PRACTICES.  AIRCRAFT RETURNED TO SERVICE. DAMAGE BELIEVED TO BE FATIGUE RELATED AS NO NOTED IMPACT DAMAGE.                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081112     NE  2008       11         12         CA080730005      220080728G73210164548540      FUEL CONTROL                            SNIAS 350   AS350*             EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENGINE          FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) FLUCTUATION OF NG (+/- 2 PERCENT) IN CRUISE FLIGHT. ACFT LANDED AT THE BASE NORMALLY. ENGINE INSPECTED. RUN-UP CARRIED OUT, NG FLUCTUATION CONFIRMED ON THE GROUND (82.5 TO 84.5 PERCENT), NR FLUCTUATION ON THE GROUND (374 - 380). FCU REPLACED (PART REMOVED WAS 1369.6 HOURS TSO). TEST FLIGHT CONDUCTED AFTER FCU REPLACEMENT AND FOUND SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E19EU                
             20081112     EA  2008       11         12         CA080730006      220080713G7200                ENGINE                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                                              FAILED          W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) 10 MINUTES AFTER TAKEOFF, THE ENGINE OIL PRESSURE AND TORQUE INDICATION DECREASED BELOW ALLOWABLE LIMITS. THE ENGINE WAS SHUTDOWN AND SECURED BY THE FLIGHT CREW.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E00062EN             
             20081112     EA  2008       11         12         CA080730007      220080706G7250                ENGINE                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NR 1            ERRATIC         W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKEOFF ROLL THE NR 1 ITT DROPPED TO 230 DEGREES AND WAS ERRATIC. THE PILOT ELECTED TO ABORT THE TAKEOFF AND RETURNED TO THE GATE. TROUBLESHOOTING DISCLOSED FAULT CODE (FC) 973 T6 OPEN CIRCUIT. FURTHER INTERROGATION OF FC CONFIRMED 973 PRESENT ON BOTH A&B CHANNELS. THE T6 HARNESS WAS REPLACED AND THE ACFT RETURNED TO SERVICE. ERRATIC ITT INDICATION WAS NOTED BY THE CREW DURING THE PREVIOUS FLIGHT.                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E00062EN             
             20081112     NE  2008       11         12         CA080730008      220080503G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              POWER LOSS      W      BA  EMER. DESCENT           UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB AT APPROX 3,000 FEET ABOVE GROUND LEVEL, PILOT HEARD A LOUD BANG AND EXPERIENCED COMPLETE LOSS OF POWER . PILOT DECLARED EMERGENCY AND PERFORMED A DEAD STICK LANDING. AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST INSP REVEALED CT BLADE DISTRESS. ENGINE WAS REMOVED AND SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                    1H71 3T3  T  A37CE   E4EA                 
             20081112     CE  2008       11         12         CA080730009      120080424G7930                OIL SYSTEM                              CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          LOW PRESSURE    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING TAXI, THE CHIP DETECTOR LIGHT CAME ON ACCOMPANIED BY A RAPID LOSS OF OIL PRESSURE AND RAPID RAISE IN OIL TEMPERATURE. THE PILOT IMMEDIATELY SHUTDOWN THE ENGINE. ON-GROUND INSP, REVEALED METAL IN OIL FILTER AND ON THE CHIP DETECTOR. THE ENGINE WAS REMOVED AND SHIPPED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                1H71 3T3  T  A37CE   E4EA                 
             20081112     SW  2008       11         12         CA080731001      120080727G322255010011        DRAG BRACE                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A DAILY INSP BY MAINT PERSONNEL, THE NR 3 LUG SECURING THE UPLOCK HOOK TORQUE SHAFT TO THE DRAG BRACE WAS FOUND CRACKED IN HALF AND SEPARATED FROM THE DRAG BRACE.  REPLACED WITH A SERVICEABLE DRAG BRACE, RIGGED AND ADJUSTED WITH NO FURTHER ISSUES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
             20081112     SW  2008       11         12         CA080731002      120080729G6320212040143001    BEARING         BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              TRANSMISSION    ROUGH           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            875                                                       (CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THERE HAD BEEN NO METAL FOUND ON THE CHIP DETECTOR OR IN THE COURSE INLET SCREEN. A SWEEP OF THE SUMP WITH A MAGNET FOUND NO METAL. AFTER DISSASEMBLY AND INSPECTION OF THE TRANSMISSION, GEARS, AND BEARINGS, THE BEARING SET P/N 212-040-143-001 IN THE HYDRAULIC PUMP AND TACHOMETER DRIVE ASSEMBLY OFFSET QUILL WAS FOUND TO BE ROUGH.                                                                                                                                                                                                                                                                                  1G71 4U4  U  H1SW    E17EA                
             20081112     EU  2008       11         12         CA080801001      120080726G2910                FLEX LINE                               BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  HYD SYSTEM      CHAFED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, THE CREW OBSERVED A LOSS OF HYDRAULIC PRESS AFTER GEAR WAS SELECTED DOWN. THE ACFT LANDED WITHOUT FURTHER INCIDENT.  MAINT IDENTIFIED THE HYDRAULIC LINE FROM THE PUMP THE HIGH PRESSURE FILTER AS THE SOURCE OF THE LEAK. THE LINE WAS REPLACED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 3T4  T  A24EU   A196    6  CP899     
             20081112     EU  2008       11         12         CA080801002      120080728G2460SM400D30        CONTACT                                 AEROSPATR42 ATR42320    8680930EU  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF5       NE  DC BUSS         FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DEPARTING, CREW OBSERVED A NR 1 DC BUSS FAIL INDICATION WITH NO GENERATOR FAULT INDICATION. THE CREW OBSERVED THAT THE NR 1 DC BUS WAS RECOVERED WHEN THE NR 1 GENERATOR WAS SELECTED OFF. THE ACFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR 1 GENERATOR CONTACTOR (12PU) AND THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20081112     NE  2008       11         12         CA080801003      220080728G7200                ENGINE                                  BOEING727   727233      138408ANM  PWA   JT8   JT8D15      52051NE                                              POWER LOSS      W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) WHILE AIRCRAFT WAS IN CRUISE ENROUTE, THE ACFT EXPERIENCED AN UNCOMMANDED POWER LOSS, DECELERATING TO FLIGHT IDLE. THE CREW SELECTED NR 2 THRUST TO IDLE AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. THE ACFT FERRIED FOR ENGINE REPLACEMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L73 4F4  FRTA3WE    E2EA                 
             20081112     EU  2008       11         12         CA080801004      120080723G5754A5724853200000  ACCESS PANEL                            AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              SLAT TRACK      MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON ARRIVAL, LEADING EDGE SLAT TRACK ACCESS PANEL 512HB FOUND MISSING. ADJACENT PANEL 512JB ALSO FOUND DAMAGED. LOST IN FLIGHT.  PANEL 512HB REPLACED AND PANEL 512JB REPAIRED IAW SRM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA35EU   E23EA                
             20081112     CE  2008       11         12         CA080801005      120080729G2750C1452501        MOTOR                                   CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  TE FLAPS        UNSERVICEABLE   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       238  238                                                       (CAN) AFTER TAKEOFF THE CREW SELECTED FLAP UP AND THE CIRCUIT BREAKER POPPED. AIRCRAFT FLEW TO MAINT BASE WERE THE CREW SELECTED PROPER FLAP WITH THE STANBY FLAP SYS AND LANDED WITHOUT INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081112     NE  2008       11         12         CA080801007      220080801G7414                BEARING                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       487                                                            (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP BEFORE DISASSEMBLY THE ROTOR BEARING END PLAY WAS MEASURED AT 0.003 INCH. THE ALLOWABLE END PLAY IS 0.0005 TO 0.0015 INCH. WHEN DISASSEMBLED THE COIL WAS FOUND TO BE SLIGHTLY LOOSE IN THE MAG HOUSING. THE BEARINGS WERE RESHIMMED AND INSPECTED, THE COIL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081112     NE  2008       11         12         CA080801008      220080801G7414                COIL                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       487                                                            (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. WHEN DISASSEMBLED THE COIL WAS FOUND SLIGHTLY LOOSE IN THE MAG HOUSING. THE COIL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081112     EU  2008       11         12         CA080804001      120080731G3340RG1007AA03      FLASHER                                 AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2A5        NE                              EXTERIOR LIGHT  BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPPER SLOWER BEACON AND STROBE LIGHTS INOP. FOUND FLASHER UNIT U/S (RECEPTACLE CONNECTOR BURNED & PARTIALLY MELTED INSIDE). CONNECTING ELECTRICAL PLUG INSULATION SLIGHTLY BURNED AND PINS DAMAGED. CONNECTOR P/N E0052R14B15SNE AND TIMER UNIT REPLACED. PARTS ROUTED TO ENGINEERING FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA35EU   E13NE                
             20081112     EU  2008       11         12         CA080804002      120080801G2131                CONTROLLER                              AIRBUS330   A330342            EU  RROYCERB211 RB211TRENT77     NE                              CABIN PRESSURE  MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) CREW DID AN EMERGENCY DESCENT DUE ECAM WARNING EXCESSIVE CABIN ALTITUDE WITH CPC NR 1 FAULT. THE EMERGENCY DESCENT STARTED FROM FL320 TO FL090. THE CABIN ALTITUDE REACHED 12000 FT.  DURING THE DESCENT THEY GOT MESSAGE "CABIN PR SAFETY VALVE OPEN". DURING TROUBLESHOOTING NR 1 CPC INTERROGATION WAS SHOWING NR 1 DELTAP SYS.  SYS RESET AND ALL INDICATION TESTED SERVICEABLE. AFTER RETURN FLIGHT TO BASE, BOTH SAFETY VALVES WERE REPLACED AS PRECAUTIONARY.                                                                                                                                                                                                                                                                      1L72 4F4  FRTA46NM   E39NE                
             20081112     CE  2008       11         12         CA080804003      120080718G7931                OIL SYSTEM                              CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ENGINE          LOW PRESSURE    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE FLIGHT, THE MASTER CAUTION WARNING SYS CAME ON IN CONJUNCTION WITH THE LOW OIL PRESSURE ANNUNCIATOR. THE CREW ELECTED TO SHUT THE ENGINE DOWN WHEN THE OIL PRESSURE WAS AT OR BELOW 30 PSI. AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. TROUBLESHOOTING COULD NOT IDENTIFY THE PROBLEM AND THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                    1L72 4F4  F  A22CE   E1NE                 
             20081113     GL  2008       11         13         CA080805001      120080707G3246                FLOAT                                   AMTR  TUNDRATUNDRA      05607NZGL                                                               LEFT NOSE       BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) ON RETRACTING LANDING GEAR AFTER TAKEOFF IT WAS NOTICED THAT THE LT NOSE GEAR ONLY PARTIALLY RETRACTED. GEAR WAS CYCLED 3 TIMES BUT LT NOSE GEAR STAYED IN A SEMI RETRACTED STATE. DECISION WAS MADE TO LAND ON RUNWAY WITH GEAR RETRACTED - NO DAMAGE, NO INJURY. INVESTIGATION BY OWNER REVEALED THE ROD WHICH ACTIVATES NOSE GEAR ONLEFT FLOAT BROKE. MONTANA FLOAT COMPANY, THE MANUFACTURER WILL SUPPLY 2 NEW RODS 7/16" THICK - OLD RODS 3/8" THICK.                                                                                                                                                                                                                                                                                1H71 3O    NTEXPA1H71                     
             20081113     EA  2008       11         13         CA080805002      220080728G7313311991901       SLEEVE                                  BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              FUEL NOZZLE     WRONG PART      W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRYING OUT A SCHEDULED HOT SECTION INSPECTION ON THE ABOVE ENGINE, IT WAS DISCOVERED THAT 2 NOZZLE SHEATHS WERE OF AN INCORRECT PART NR FOR THE MODEL OF ENGINE INSTALLED. THE PART NRS ARE BOTH FOR A PT6A-50 ENGINE. EVEN THOUGH WE OPERATE THIS MODEL OF ENGINE, OUR INVENTORY RECORDS DO NOT SHOW THIS PART EVER BEING ISSUED TO THIS ACFT. THERE IS A POSSIBILITY THAT THESE 2 SHEATHS HAD BEEN INSTALLED AT ENGINE OVERHAUL, T.S.O. 3522 HRS. 2 REPLACEMENT SHEATHS OF THE CORRECT PART NR WERE INSTALLED AND THE ENGINE RETURNED TO SERVICE.                                                                                                                                                                               1L72 3T4  TRT3A20    E4EA                 
             20081112     SW  2008       11         12         CA080805003      120080803G5302                SKIN                                    BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2798                                                           (CAN) CRACK FOUND BETWEEN THE TAIL ROTOR SUPPORT AND TAILBOOM AT FUSELAGE STA 375 APPROX. ALSO SEVERAL RIVETS WERE FOUND SMOKING. THE HELICOPTER WAS USED TO MOVE DRILL ON A REGULAR BASIS WITHOUT EXCEEDING THE LOAD CAPACITY. TAILBOOM REMOVED P/N407-530-014-101 S/N 53037 AND SERVICEABLE TAILBOOM INSTALLED P/N 407-030-801-205D PROCURED FROM MFG.                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  UO H2SW    E1GL                 
             20081119     NM  2008       11         19         CA080805005      120080731G3231483025          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  MLG DOOR        INOPERATIVE     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE, THE LANDING GEAR WAS SELECTED UP, THE RT MLG DOOR WAS SLOW TO CLOSE (APPROX 10 MINUTES). THE F/A VERIFIED THE DOOR WAS OPEN. THE DOOR THEN CLOSED WITHOUT ACTION FROM THE PILOT. PSEU FAULT CODE RGDCL UNREASONABLE FAR.   RT MLG SOLENOID SEQUENCE VALVE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081119     NM  2008       11         19         CA080805006      120080801G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              HYD SYSTEM      DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH, NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON SO ALL SYSTEMS OPERATED NORMAL FOR ROUTINE LANDING.   EDP CASE HALVES LOOSE AND PUMP NOT MAKING PRESSURE. PUMP REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E00062EN             
             20081119     EA  2008       11         19         CA080805007      220080801G853065678           BOLT            CURTIS                  GRUMANTS2   TS2ACALFORST3951102WP  WRIGHTR1820 982C9HE2    67020EA                              EXAUST ROCKER   SHEARED         W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE FLIGHT, THE NR 1 ENGINE LOST POWER AND BEGAN TO BACKFIRE. ENGINE SHUT DOWN AND FEATHERED. UPON INSPECTION OF ENGINE NR 9 CYLINDER EXHAUST ROCKER BOLT FOUND SHEARED AT NUT AND BOLT HAD DISENGAGED FROM CYLINDER EAR ASSEMBLY. NEW BOLT AND NUT ASSEMBLY INSTALLED, VALVE CLEARENCES ADJUSTED, MAIN OIL SCREEN AND NO CONTAMINATION FOUND. ENGINE GROUND RUN SERVICEABLE AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                               2H72 4R4  R  A25WE   E259                 
             20081119     NE  2008       11         19         CA080805008      220080805G7414106006169       MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       608                                                            (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH END PLAY WAS NOTICED ON THE ROTOR BEARINGS (0.0015 INCH IS MAX. ALLOWABLE). WHEN DISASSEMBLED THE WASHER THAT RETAINS THE DISTRIBUTOR GEAR ON THE SHAFT WAS SLIGHTLY LOOSE. MFG HAS BEEN CONTACTED IN THE PAST ABOUT THIS ISSUE AND HAS INSTRUCTED US TO USE A PRESS ON THE END OF THE SHAFT TO REFLARE IT TO RETAIN THE WASHER. THE COIL WAS ALSO FOUND MOVING SLIGHTLY AGAINST THE HOUSING POLES AND WHEN THE COIL CLAMP SCREWS WERE REMOVED TO INSPECT THIS THE SCREWS WERE FOUND TO BE NOT VERY TIGHT. THE ROTOR BEARINGS WERE RESHIMMED, THE DIST. GEAR SHAFT WAS REFLARED, AND THE COIL CLAMP SCREWS WERE TIGHTENED. THE REST OF THE 500 HOUR INSP. WAS CARRIED OU1G71 3O3  O  H11NM   1E4                  
             20081119     NE  2008       11         19         CA080805009      220080805G741410160858        HOUSING                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       608                                                            (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. A CRACK WAS NOTICED IN ONE OF THE MOUNTING EARS OF THE MAG HSG. THIS IS A NEW STYLE OF HSG CASTING FROM MFG WITH THE LARGE RAISED LETTERS ON THE OUTSIDE OF THE HSG AND THE WORD "EMPIRE" INSIDE THE HSG NEXT TO THE BRG AREA. WE HAVE NOTICED A HIGHER NR OF THESE NEW STYLE HSGS CRACKING AT THIS LOCATION. OLDER CASTINGS WOULD OCCASIONALLY CRACK IF THE MOUNTING NUTS WERE OVERTORQUED, WHEREAS THESE NEW ONES SEEM TO BE WEAKER AND CRACK MORE OFTEN. THE MAG WAS REMOVED FROM SERVICE.                                                                                                                                                                                                         1G71 3O3  O  H11NM   1E4                  
             20081119     NM  2008       11         19         CA080805010      120080802G3060                HEATER          HAMSTD                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  PROP BLADE      BURNED          W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA       1031610316                                                     (CAN) THE CREW OBSERVED SPARKS COMING FROM THE FRONT OF THE RT ENGINE. THE CREW SHUTDOWN THE ENGINE IN FLIGHT AND DECLARED AN EMERGENCY. THE ACFT LANDED SHORTLY AFTER WITHOUT INCIDENT. INVESTIGATION REVEALED THAT THE RT PROPELLER BLADE NR2 ELECTRICAL HEATER BURNED CAUSING THE HEATING ELEMENT TO PRODUCE ELECTRICAL SPARKS. THE BLADE ASSY WAS REPLACED, THE BLADE ANTI-ICING SYS TESTED AND THE ACFT RETURNED INTO SERVICE. THE BLADE WAS SENT TO AN EXTERNAL SHOP FOR REPAIR.                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081119     GL  2008       11         19         CA080805011      220080801G72303896888M        SCROLL                                  BELL  206   206L1       1182107SW  ALLSN 250C  250C30P     03013GL                              COMPRESSOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       21976                                                          (CAN) WHILE CARRYING OUT A DAILY CHECK, A CRACK WAS FOUND ON THE COMPRESSOR SCROLL ON TOP, PARALLEL TO SHROUD HSG AND NEAR THE RT ELBOW. ACFT WAS GROUNDED. COMPRESSOR ASSY IS AN ON-CONDITION ITEM BUT THERE IS AN INSP EVERY 2000 HOURS. AS YOU CAN SEE THIS SCROLL WAS VERY HIGH TIME. SINCE LAST 2000 HOUR INSP 374.8 HOURS.  TO THE 2000 HR INSP INVOLVES INSPECTING THE SPUR ADAPTER GEAR AND ITS MATING GEAR. BELIEVE THAT THE SCROLL IS THE SAME TIME AS THE COMPRESSOR ASSY.                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E1GL                 
             20081117     CE  2008       11         17         CA080805012      120080730G32341013841377      SELECTOR                                BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE                              LANDING GEAR    DEFECTIVE       W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) UPON APPROACH THE CREW WAS UNABLE TO EXTEND THE GEAR NORMALLY AND HAD TO PERFORM AN EMERGENCY EXTENSION. A SUCCESSFUL LANDING WAS CARRIED. UPON INVESTIGATION, IT WAS DETERMINED THE PROBLEM WAS IN THE LANDING GEAR SELECTOR ASSY. THE PIVOT SCREW FOR THE MICROSWITCH ACTUATING LEVER HAD BACKED OUT SEVERAL THREADS. THIS ALLOWED THE LEVER TO MIGRATE OUT WITH THE SCREW. WHEN THE GEAR WAS SELECTED UP THE ACTUATING LEVER CAME TO REST ON PART OF THE GEAR SELECTOR HSG. AS SUCH, WHEN THE CREW SELECTED GEAR DOWN THE SWITCHES WERE NOT RELEASED AND THE GEAR REMAINED IN THE RETRACTED POSITION. THREAD LOCKING COMPOUND WAS APPLIED TO THE PIVOT SCREW AND THE SCREW WAS TIGHTENED. SEVERAL GEAR SWINGS WERE SUCCESSFULLY COMPLET1L72 4T4  T  A24CE   E4EA                 
             20081117         2008       11         17         CA080805013      420080805G611335323012        BULKHEAD                                PIPER PA28  PA28151     7102805SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ANNUAL INSP FWD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AT SCREW ATTACHMENT HOLE.  NEW PART WAS ORDERED FROM MFG IAW APPLICABLE PARTS CATALOGUE.  NEW PART RECEIVED WAS STAMPED WITH CORRECT PN AS ORDERED, BUT WAS PHYSICALLY DIFFERENT IN DEPTH AND WOULD NOT FIT.   MFG WAS CONTACTED (VIA AVIATION UNLIMITED AND A SECOND SPINNER BACK PLATE IS BEING SHIPPED).                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    E274    5  NP88614   
             20081117     SO  2008       11         17         CA080805014      220080709G8530                CAMSHAFT                                CESSNA185   A185F       2072821CE  CONT  O550  IO550D      17042SO  MCAULYD3A34 D3A34C401   GL  ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSP , NR2 CYL WAS REMOVED DUE TO LOW COMPRESSION. DISCOVERED LIFTERS ON NR1 CYL HAD PITTING AND SPALLING. FURTHER INVESTIGATION REVEALED THE CAMSHAFT WAS CORRODED AND WORN ALSO. ENGINE REMOVED FOR REPAIR. ENGINE HAS 670 HOUR TSOH. UPON TEARDOWN, CRANKSHAFT HAD CORROSION, AND THE OIL PUMP WAS DAMAGED DUE TO METAL CONTAMINATION IN ENGINE, AND MORE LIFTERS HAD DAMAGE. THE ACFT HAS ALWAYS BEEN HANGERED, OUT OF THE COLD. WHEN IT WAS OUT IN THE COLD, A PREHEAT SYS WAS UTILIZED. ACFT FLEW ON THE AVERAGE 3 TO 4 HOURS PER WEEK WITH APPROX 2 HOUR DURATION PER FLIGHT. CANNOT DETERMINE WHAT THE CAUSE OF THE CORROSION IS WHICH CAUSED THE METAL CONTAMINATION.                                                     1H71 3O3  O  3A24    E3SO    5  CP47GL    
             20081117     NE  2008       11         17         CA080806001      220080723G7321                FUEL CONTROL                            BEECH 200   200CBEECH   1152926CE  PWA   PT6   PT642A           NE                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) DURING LANDING, THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION WHICH CAUSED THE PILOT TO HAVE DIFFICULTY CONTROLLING THE ACFT, CAUSING IT TO SKID IN THE GRASS AND MUD AT THE SIDE OF THE RUNWAY. THE FUEL CONTROL WAS REPLACED AND THE RIGGING WAS ADJUSTED. THE FUEL CONTROL WILL BE INVESTIGATED AND UPDATES PROVIDED.                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4T4  T  A24CE   E4EA                 
             20081117         2008       11         17         CA080806002      420080729G31608221577012      DISPLAY                                 BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              COCKPIT         MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) PILOT REPORTED, DURING PREFLIGHT. THEY STARTED THE APU. AFTERWARDS, PILOT SELECTED THE AIR SOURCE TO (NORMAL) THEN SMOKE BEGAN EMITTING FROM THE RT SIDE OF THE COCKPIT BETWEEN THE GLARESHIELD AND WINDOW. PILOT SELECTED THE AIR SOURCE TO (OFF) THEN SHUTDOWN THE APU. FOUND COPILOT`S MFD AS THE SOURCE OF THE SMOKE.  REMOVED AND REPLACED COPILOT`S MFD. OPS GOOD. EXTENSIVE GROUND TESTING INCLUDING OPS OR AIR COND SYS WAS CARRIED OUT AND ALL WAS FOUND TO BE NORMAL.                                                                                                                                                                                                                                                           2L72 4F4  FRTT00005NYE00010LA             
             20081117     EA  2008       11         17         CA080806003      220080726G7260                GEARBOX                                 BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ENGINE          DISCONNECTED    W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               APAPPROACH       1                      CA                                                                      (CAN) DURING FINAL APPROACH, THE ENGINE FLAMED OUT. RELIGHT ATTEMPT WAS UNSUCCESSFUL. AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. POST EVENT TROUBLESHOOTING, FOUND THAT THE ENGINE COULD NOT BE RE-STARTED. ACCESSORIES GEARBOX DE-COUPLE IS CONFIRMED. THE AFFECTED COMPONENTS WILL BE REMOVED AND FWDED FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA24CE   E4EA                 
             20081117     NE  2008       11         17         CA080806004      220080729G7200                ENGINE                                  PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) DURING T/O, THE ENGINE STARTED TO SURGE FOLLOWED BY A RISE IN INDICATED TEMPERATURE. THE PILOT ELECTED TO RETURN TO HIS POINT OF DEPARTURE, WHERE A SAFE LANDING WAS PERFORMED. THE ENGINE TEMP REACHED 970C FOR ONE MINUTE. THE ENGINE WILL BE REMOVED AND FWDED FOR INVESTIGATION AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3T4  TRTA78EU   E26NE                
             20081117     CE  2008       11         17         CA080806005      120080801G8120                TURBOCHARGER                            BEECH 60    B60         1153605CE  LYC   O541  TIO541E1C4  41536EA  HARTZLHCF3Y HCF3YR2     GL  LT ENGINE       MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) PILOT REPORTED LOW MANIFOLD PRESSURE ON LT ENG IN CLIMB OUT, ACFT RETURNED TO THE AIRPORT. MAINT BACK FLUSHED THE LT TURBO WASTEGATE AND CONTROLLER, GROUND RUN OK. NO OTHER DEFECTS NOTED, ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A12CE   E10EA   5  CP31EA    
             20081117     EA  2008       11         17         CA080806006      120080804G7110                COWLING                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              NR 2 ENGINE     DEPARTED        W      K   NONE                                                                                            P  NO WARNING INDICATION                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AS INDICATED BY MAINT CONTROL, ACFT DEPARTED. MISSING COWLING FROM NR2 ENGINE WAS DISCOVERED DURING WALKAROUND INSP BY GROUND MAINT. IT WAS ALSO APPARENT THAT PORTIONS OF THE COWLING THAT DEPARTED ENGINE, STRUCK THE LEADING EDGES OF THE LT AND RT HORIZONTAL STAB.  CREW DID NOT HAVE ANY ABNORMAL INDICATIONS DURING FLIGHT, IAW MAINT CONTROL COMMENT TO FSR. PLEASE REFER TO ADR RRAD-C08-21754681.                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20081117     NE  2008       11         17         CA080806007      220080805G7260                GEARBOX                                 CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF348E5A1   30062NE                              NR 1 ENGINE     DEFECTIVE       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, CREW NOTICED THEY LOST THE NR1 ENGINE OIL INDICATION AND GOT THE RED LED.  SHUTDOWN ENGINE AND MADE AN UNEVENTFUL LANDING. CREW NOTICED A PUDDLE OF OIL UNDER THE NR1 ENGINE AFTER LANDING.  DURING THE TROUBLESHOOTING, THEY REMOVED THE DRAIN MAST AND INSTALL PLASTIC BAG TO THE DIFFERENT DRAIN LINES. AFTER STARTING THE ENGINE, THE PLASTIC BAG FOR THE ACCESSORY GEAR BOX DRAIN WAS FULL OF OIL.  SHUTDOWN THE ENGINE, THEY ARE NOW WAITING FOR THE MRP TO CHANGE THE AGB.                                                                                                                                                                                                                                          2L72 4F4  FRTA21AE   E00063EN             
             20081117     NM  2008       11         17         CA080806008      120080730G213388060B010003    OUTFLOW VALVE                           BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  CABIN PRESSURE  FAILED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) ACFT RETURNED DUE TO DEPRESSURIZATION AND BURNING ODOR IN THE COCKPIT. ATC CALLED LOCAL STANDBY, NO PAN/MAYDAY DECLARED. ACFT LANDED SAFELY AND WITHOUT INCIDENT.   MAINT INTEROGATEED THE CDS, THE FOLLOWING CODES IDENTIFIED: AFT OUTFLOW VALVE FAIL CPC/OFF VALVE DATA FAIL.  AFT OUTFLOW VALVE REPLACED. FUNCTION CHECKS OF ECS SYSTEM CARRIED OUT COULD NOT IDENTIFY ANY ODORS. AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081117     EA  2008       11         17         CA080806009      120080718G2730C6CTM102827     DRIVE ASSY      DHAV        C6CT10103   DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              ELEVATOR        STRIPPED        W      A   UNSCHED LANDING                                                                                 ZE SIGNIFICANT FAILURE REPORTVIBRATION/BUFFET                                    CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB OUT AT 800 FEET ALTITUDE THE ACFT SUDDENLY STARTED TO SHAKE VIOLENTLY. THE PILOT ABORTED THE CLIMB, PROCEEDED STRAIGHT AHEAD FOR 4 MILES TO A LANDING STRIP AND LANDED SAFELY WITH NO INJURIES TO PERSONS ON BOARD. UPON INVESTIGATION AS TO THE CAUSE OF THE SHAKING IT WAS DISCOVERED THAT THE CLEVIS END P/N C4CM1956-11 HAD PULLED COMPLETELY OUT OF THE SCREW DRIVE P/N C6CTM1028-27 IN THE ELEVATOR SCREW JACK ASSY P/N C6CT1010-3. THIS ALLOWED THE TRIM TAP TO FLUTTER WHICH IN TURN CAUSED THE ELEVATOR TO FLUTTER INDUCING A VIOLENT SHAKING OF THE ACFT.                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
             20081117     EA  2008       11         17         CA080806010      120080705G760374491147        CABLE ASSY                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              THROTLE         BROKEN          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       18500                                                          (CAN) WHILE ATTEMPTING TO REDUCE RT ENGINE PWR AFTER TAKEOFF AND CLIMB, FLT CREW REPORTED THAT THE RT ENG WOULD NOT RESPOND TO THROTTLE LEVER INPUTS. THE RT ENGT WAS SHUTDOWN VIA FIRE PUSH SWITCH/LIGHT, ACFT DIVERTED TO IAD AND LANDED WITHOUT FURTHER INCIDENT.   PRIOR TO TAKEOFF (ON TAXI OUT), THE FLT CREW NOTICED THAT THE RT THROTTLE LEVER WAS VERY STIFF THAT THEY ATTRIBUTED TO FRICTION LOCKS. UPON ADDING POWER FOR TAKEOFF, THEY NOTICED THAT THE THROTTLE LEVERS WERE VERY STIFF AT FIRST, THEN THERE WAS A DEFINITE "POP" AND THEN THE LEVERS ADVANCED EASILY TO THE FLEX THRUST SETTING (87 PERCENT). THE REMAINDER OF THE TAKEOFF WAS NORMAL. WHEN ADVANCING PWR LEVERS TO CLIMB THRUST (92 PERCENT N1), BOTH ENGINES RESPO2L72 4F4  FRTA21EA   E15NE                
             20081117     CE  2008       11         17         CA080806011      120080716G2550D2010103        ARM             DART        D500560041  DART  G     G           2700102CE                                                               CARGO BAY       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         UKUNKNOWN        1                      CA                                                                      (CAN) MFG HAS RECEIVED A REPORT THAT UNDER CERTAIN CIRCUMSTANCES ON THE D500-560-041 CARGO MIRROR INSTALLATION AT CHG001 THE D2010-103 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM THE ASSY. SB08-3 IS BEING ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED ASSEMBLIES.                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3R      TC674                        
             20081117     EA  2008       11         17         CA080806012      220080801G8530SL360000WA20P   CYLINDER HEAD                           BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA       1854                                                           (CAN) DURING CLIMB OUT WITH GLIDER IN TOW, THE PILOT REPORTED AN ENGINE VIBRATION. THEY IMMEDIATELY INSTRUCTED THE GLIDER TO RELEASE AND THEN PREFORMED A DOWN WIND LANDING AND RETURN TO HANGER. UPON SHUTDOWN AND INSP IT WAS FOUND THAT CYL NR1 HEAD HAD CRACKED AND SEPARATED FROM THE REMAINDER OF THE CYL.                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  A21CE   E286    5  NP874     
             20081117     SW  2008       11         17         CA080806013      120080728G3244280250          TIRE                                    BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  TAIL WHEEL      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       125                                                            (CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT THE TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  A21CE   E286    5  NP874     
             20081117     SW  2008       11         17         CA080806014      120080727G3244280250          TIRE                                    BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  TAIL WHEEL      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       124                                                            (CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT THE TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  A21CE   E286    5  NP874     
             20081117     SW  2008       11         17         CA080806015      120080728G3244280250          TIRE                                    BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2A     41514EA  MCAULY1A200 1A200*      GL  TAIL WHEEL      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       160                                                            (CAN) TAIL WHEEL TIRE FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT THE TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  A21CE   E286    5  NP874     
             20081117     SW  2008       11         17         CA080806016      120080625G571131692           SPAR                                    BBAVIA8     8GCBC       1220803SW                                                               WING            CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       976                                                            (CAN) PART FOUND CORRODED AT SPAR ATTACHMENT BOLT HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O      A21CE                        
             20081117     SW  2008       11         17         CA080806017      120080625G571131692           SPAR                                    BBAVIA8     8GCBC       1220803SW                                                               WING            CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       976                                                            (CAN) PART FOUND CORODED AT SPAR ATTACHMENT BOLT HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O      A21CE                        
             20081117     NM  2008       11         17         CA080807001      120080729G25205045802158003   SEAT BELT                               EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              CABIN           FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3059                                                           (CAN) F/A SEAT LAP BELTS AT DOOR LT NR1 AND DOOR RT NR2 FRAYED SEVERAL PLACES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA57NM   E00070EN             
             20081117     NM  2008       11         17         CA080807002      120080806G25205045802158003   SEAT BELT                   5045804078  EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              CABIN           FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5704                                                           (CAN) F/A SEAT LAP BELT AT DOOR LT NR1, NR2 AND DOOR RT NT2 FRAYED SEVERAL PLACES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA57NM   E00070EN             
             20081119     NE  2008       11         19         CA080807003      320080718G61107149A0          THRUST WASHER   HAMSTD                                                                                      HAMSTD23E   23E50       NE  BLADE SHANK     CRACKED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA            471                                                       (CAN) THE CRACKED BLADE RING IS PART OF THE BLADE ASSEMBLY. A CRACKED RING TYPICALLY RESTRICTS BLADE ROTATION AND CAN SET UP A VIBRATION. PROPELLER WAS REMOVED AND AFTER TEAR DOWN AND INSPECTION A CRACKED BLADE RING (THRUST WASHER) WAS DETERMINED AND OTHER DAMAGE TO THE BARREL ASSEMBLY. REPLACED BLADE THAT HAD THE BROKEN BLADE RING AND OTHER DAMAGED PARTS. PROPELLER ASSEMBLED BALANCED AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                 6  CP603     
             20081119     NM  2008       11         19         CA080807004      120080806G2761                HOUSING         SMITHSIND               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ACTUATOR        FRACTURED       W      D   RETURN TO BLOCK                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       44413                                                          (CAN) WHEN THE FLIGHT/TAXI SWITCH WAS SELECTED TO FLIGHT IN PREPARATION FOR TAKE OFF, THE CREW RECEIVED SOME HYDRAULIC CAUTION LIGHTS ASSOCIATED WITH A LOW HYDRAULIC LEVEL INDICATION ON THE NR 1 SYSTEM . THE ACFT RETURNED TO THE GATE AND A MAJOR HYDRAULIC LEAK WAS OBSERVED AT THE RT WING. MX FOUND THE INBD FLIGHT SPOILER ACTUATOR CASING CRACKED. THE ACTUATOR WAS REPLACED, LEAK CHECKED, TESTED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081117     EA  2008       11         17         CA080807005      120080807G5520C6TEM101229     HINGE FITTING                           DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              ELEVATOR        MISMANUFACTURED W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) THE HINGE ARM ASSY WAS RECEIVED FROM THE OEM WITH THE BONDING STRAP AND TAB INSTALLED ON THE UPPER ARM OF THE ASSY WHICH IF INSTALLED WOULD RESTRICT TRAVEL OF THE ELEVATOR. THE BONDING STRAP IS A FIXED LENGTH AND RIVETED IN PLACE. ADDITIONALLY TO MAKE THE TAB BOND PROPERLY TO THE ARM PAINT WAS REMOVED FROM THE ASSY AND NOT REFINISHED. THE AREA THIS PART IS INSTALLED IN IS EXPOSED TO THE ENGINE GAS PATH THEREBY MAKING IT A HIGH CORROSION AREA. ALSO UPON FURTHER EXAMINATION THE BONDING TAB WAS FOUND LOOSE DUE TO THE COUNTER SINK(S) SIZE. THIS PART HAS BEEN SENT BACK TO THE OEM FOR REPLACEMENT.                                                                                                                    1H72 3T4  TRTA9EA    E4EA                 
             20081117     EU  2008       11         17         CA080807006      120080701G71601350P5103       SEAL                                    SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101750A1 41560NE                              ENGINE          DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 X  ENGINE FLAMEOUT                                                               ININSP/MAINT     1                      CA                                                                      (CAN) CONVERTED LAST FEB, AT THE SAME TIME INSTALLED AN FDC ENGINE AIR FILTER. JULY 1ST 2008 THE PILOT WAS STARTING THE ENGINE GOT TO AROUND 60 PERCENT TORQUE WHEN COMPRESSOR STALLS OCCURRED. HE SHUTDOWN. UPON INSP FOR COMPRESSOR STALLS IT WAS FOUND THE COMPRESSOR WAS FOD.  FOUND THAT A PIECE OF THE SEAL P/N 1350P5-103 HAD COME OFF AND FOD THE ENGINE.                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH9EU    E5NE                 
             20081117         2008       11         17         CA080807007      420080805G6113C4383           SUPPORT                                 CESSNA180   180C        2072608CE  CONT  O470  O470K       17026SO  MCAULY2A34C 2A34C203    GL  SPINNER         BROKEN          W      C   ABORTED TAKEOFF                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      CA       215                                                            (CAN) PLASTIC SPINNER SUPPORT CRACKS AND BREAKS INSIDE SPINNER CAUSING VIBRATION, SEEMS PLASTIC IS SOFTER DURING THE HOT SUMMER MONTHS AND FLEXES MORE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  5A6     E273    5  CP3EA     
             20081117     EU  2008       11         17         CA080808001      120080807G3233A5341130500200  ATTACH FITTING                          AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2*         GL                              NLG ACTUATOR    BROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) ON LDG GEAR UP SELECTION NOSE GEAR SHOWED UNSAFE DOOR NOT UP. ECAM/QRH CARRIED OUT.  ACFT RETURNED TO THE STATION.  FOUND NLG UP LOCK ACTUATOR ATTACHMENT FITTING ASSY P/N A5341130500200 WITH BROKEN LUGS. NEW ATTACHMENT FITTING INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA35EU   E23EA                
             20081117     CE  2008       11         17         CA080808002      120080731G8011534685          BEARING         CONT        643259A18   CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  STARTER         WORN            W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL PRESSURE STARTED TO FLUCTUATE. A PRECAUTIONARY LANDING WAS MADE. IT WAS OBSERVED THAT THE OIL LEVEL WAS LOW AND AN EXCESSIVE AMOUNT OF OIL WAS IN THE ENGINE COMPARTMENT AND IN THE BELLY OF THE ACFT. UPON MAINT INSP, IT WAS FOUND THAT THE STARTER ADAPTER PULLEY BEARING WAS BADLY WORN, DAMAGING THE OIL SEAL ALLOWING FOR AN OIL LEAK. THE STARTER ADAPTER WAS REPLACED, OIL FILTER CHECKED FOR FOREIGN MATERIAL, OIL REPLENISHED, AND A LEAK CHECK WAS CARRIED OUT. THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                         1H71 3O3  O  A4CE    E5CE    5  CP36EA    
             20081119         2008       11         19         CA080808004      120080722G291025W711008171    LINE                                                                       GARRTTTFE731TFE73140    29001NE                              HYD SYSTEM      CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA       1219                                                           (CAN) ON APPROACH INTO TORONTO PEARSON THE CREW NOTICED THAT THE AUX HYDRAULIC LOW PRESSURE ANNUNCIATOR AND FLUID LOW LEVEL LIGHT ILLUMINATED ON THE ACFT. AFTER STABILIZING THEIR APPROACH, ALL LIGHTS WENT OUT. AFTER LANDING THE LOW LEVEL LIGHT CAME ON ONCE AGAIN WITH NO FURTHER LOW AUX HYD PRESSURE NOTED. AN INVESTIGATION FOUND THE RESERVOIR TANK LOW AND THE LINE FROM THE AUX PUMP AREA TO THE HYDRAULIC FILTER HAD A VERY FINE CRACK THAT HAD ORIGINATED ALONG A TOOLING MARK, THAT WAS ONLY VISIBLE WHEN RUNNING AND UNDER A 10 POWER MAGNIFYING GLASS. THE LINE WAS REPLACED AND RESERVOIR SERVICED WITH NO FURTHER PROBLEMS.                                                                                                          4  F          E1NM                 
             20081117     WP  2008       11         17         CA080808005      220080805G7321                VALVE           WOODWARD                SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  FUEL CONTROL    INOPERATIVE     W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA            1162                                                      (CAN) CREW REPORTED MINOR ISSUE WITH STIFF POWER LEVER ON ONE ENGINE. MAINT EXAMINED THE CONTROL LINKAGE AND FOUND THAT THE FUEL CONTROL`S MANUAL FUEL VALVE (MFV) WOULD NOT REACH FULL TRAVEL (APPROX 85 PERCENT OF TRAVEL)  REMOVED THE UNIT FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
             20081117     SO  2008       11         17         CA080811001      120080729G24342CM353C1H       ALTERNATOR                              LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 2            FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) ON DESCENT, CREW OBSERVED THE NR 2 GENERATOR FAIL WAS ILLUMINATED. THE NR2 ENGINE WAS SHUTDOWN AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR2 GENERATOR AND THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H74 4T4  T  A1SO    E282    6  CP906     
             20081117     NE  2008       11         17         CA080811002      220080806G8530                CYLINDER                                CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  NR 1 ENGINE     DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 Z  SIGNIFICANT FAILURE REPORT                                                    CRCRUISE         1                      CA                                                                      (CAN) NR 1 ENGINE BACKFIRED IN FLIGHT.  ENGINE WAS SHUTDOWN AND PROP FEATHERED.  NR 2 CYLINDER EXHAUST EAR WAS FOUND CRACKED.  CYLINDER WAS REPLACED AND ENGINE GROUND RUNS SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4R3  RRTA14EA   ATC14   6  CP871     
             20081117     NM  2008       11         17         CA080811003      120080810G3242214664          BRAKE ASSY                  214664      DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  LANDING GEAR    DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            986                                                       (CAN) WHILE THE ACFT WAS BEING TOWED OFF THE RAMP A STRANGE NOISE WAS HEARD IN THE RT WHEEL AREA.  UPON INVESTIGATION IT WAS FOUND THAT 3 OF THE 6 TORQUE PLATE TO PISTON HSG RETAINING BOLTS ON THE RT INBD BRAKE UNIT HAD SHEARED. NO OTHER DAMAGE WAS NOTICED. THE BRAKE UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081117     SW  2008       11         17         CA080811004      120080808G2910205076302001    TUNING UNIT                             BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              HYDRAULIC SYS   CRACKED         W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         KF FLUID LOSS                FLT CONT AFFECTED                                   CRCRUISE         1                      CA       13967                                                          (CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITEMS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WAS NOTICED AT THIS TIME. PART HAD 79 HRS SINCE INSTALLATION WHEN FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 4U4  U  H1SW    E17EA                
             20081119     SW  2008       11         19         CA080811006      120080807G76032761000009      ROD END                                 SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              RT POWER LEVER  WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE FUEL CONTROL WAS BEING REPLACED ON THE RT ENGINE. WHEN THE STARTER GENERATOR WAS REMOVED IT WAS APPARENT THAT THE POWER LEVER, WHERE IT ATTACHES TO THE PROP PITCH CONTROL BY A ROD END, WAS SEVERELY WORN. THE TIME SINCE INSTALL IS NOT KNOWN, HOWEVER THE ROD END DID NOT LOOK PARTICULARLY OLD. THE CAD PLATING WAS STILL ON THE PART. IT HAD BEEN APPROX 80-90 HOURS SINCE THE LAST SCHEDULED INSPECTION. THIS IS THE THIRD INSTANCE IN RECENT MONTHS WITH THE SAME PART NR ROD END. (SOME WORSE THAN OTHERS) THE PART APPEARS TO BE FINE AT INSPECTION THEN FAILS SUDDENLY. AT A CERTAIN POINT IN THE LAST FEW YEARS THE PART CHANGED, THE NR IS THE SAME BUT THE PART WAS PHYSICALLY DIFFERENT. THE NEWER ONES ARE THE PROBLEM 2L72 4T4  TRTA8SW    E4WE                 
             20081118     EA  2008       11         18         CA080811007      220080807G7322383493          PLUG                        25245009    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  FUEL SERVO      LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE ACCOMPLISHING REPETITIVE INSP (50HR) FOR AD2008-08-14, FOUND BOTH ENGINE FUEL SERVO PLUGS LOOSE. BOTH PLUGS REMOVED, INSPECTED, RETORQUED AND SAFETIED IAW AD REQUIREMENTS. NO ENGINE PERFORMANCE SNAGS REPORTED. LT ENGINE: TIO-540-J2BD S/N: L6203-61A, SERVO P/N: 2524500-9 S/N: 83731, TSO: 345.5 HRS RT ENGINE: LTIO-540-J2BD S/N: L2363-68A, SERVO P/N 2524500-9 S/N: 52869, TSO: 345.5 HRS.                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081117     CE  2008       11         17         CA080812001      120080716G3340S21601          SWITCH                                  CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              STROBE LIGHT    FAULTY          W      A   UNSCHED LANDING                                                                                 BB SMOKE/FUMES/ODORS/SPARKS  SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      CA                                                                      (CAN) ON JULY 16, 2008 AT APPROX. 13:00, PILOT REPORTED SMOKE IN COCKPIT AND PLASTIC BURNING SMELL. ACFT ELECTRONICS WERE SHUTDOWN AND SMOKE DISSIPATED.  DURING POST FLIGHT INSP, MAINT DISCOVERED A FAULTY STROBE LIGHT SWITCH, AND REPLACED THE DEFECTIVE SWITCH. ACFT SYS TESTED WITH NO FURTHER DEFECTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E274                 
             20081117     CE  2008       11         17         CA080812002      120080808G325222430211        CLEVIS          CESSNA      24421141    CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C220   GL  SHIMMY DAMPER   BROKEN          W      D   RETURN TO BLOCK                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       9102                                                           (CAN) DAMPER SHAFT CLEVIS BROKE AT NOSE STRUT ATTACHMENT ALLOWING UNRESTRAINED MOTION OF SHIMMY DAMPER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  3A17    E286    5  CP7EA     
             20081117     EA  2008       11         17         CA080812003      220080808G8530LW13623         PISTON                                  CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  ENGINE          DAMAGED         W      D   RETURN TO BLOCK                                                                                 R  PARTIAL RPM/PWR LOSS                                                          ININSP/MAINT     1                      CA       244                                                            (CAN) TOP COMPRESSION RING BROKEN, OIL RING SEIZED, PISTON BURNED FROM BLOWBY, CONNECTING ROD UPPER BRG LOOSE, BRG BORE OUTSIDE SERVICE LIMITS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081124     NE  2008       11         24         CA080812004      220080721G7261MS920807        BOLT                                    DHAV  DHC8  DHC8314            NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  ENGINE OIL LINE LOOSE           W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) SHORTLY AFTER TAKEOFF, THE NR 1 ENGINE LOST OIL PRESSURE AND WAS SUBSEQUENTLY SHUTDOWN. THE ACFT RETURNED TO THE AIRPORT FOR AN APPROACH, HOWEVER, THE VISIBILITY WAS TOO LOW, A MISSED APPROACH WAS EXECUTED FOLLOWED BY A NR OF HOLDS UNTIL THE WEATHER WAS APPROPRIATE TO TRY A SECOND APPROACH. THE ACFT LANDED SAFELY AFTER A SECOND APPROACH. FURTHER INSPECTION FOUND THE OIL LINE FLANGE BOLTS LOOSE ON THE NR 1 ENGINE, ALLOWING ALL THE OIL TO BE PUMPED OUT OF THE ENGINE. THESE BOLTS ARE NOT DRILLED AND THEREFORE CANNOT BE SAFETY WIRED. PRATT SB 21178 REPLACES THE INSERTS WITH SELF LOCKING INSERTS. THE BOLTS WERE RETORQUED, OIL REPLENISHED AND THE ACFT WAS RETURNED TO SERVICE.                                    2H72 4T4  TRT        E20NE   6  CP7NE     
             20081117     NE  2008       11         17         CA080812005      220080803G853071167           EXHAUST VALVE   PWA         399359      DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R1340*      52016NE  HAMSTD23D   23D40       NE  CYLINDER        BROKEN          W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA       6862 1070                                                      (CAN) EXHAUST VALVE BROKE IN CRUISE FLIGHT 15 MIN AFTER DEPARTURE. PARTIAL POWER LOSS - ENGINE VIBRATION. PRECAUTIONARY LANDING EXECUTED.  SERVICEABLE CYL COMPLETE INSTALLED AFTER LOCATING THE DEFECT/FAILURE. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3R3  R  A815    5E2     6  CP719     
             20081119     SW  2008       11         19         CA080813002      120080813G6410206011809109    PITCH HORN                              BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              TAIL ROTOR      LOOSE           W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA                                                                      (CAN) THE STUD WHICH HOLDS THE PITCH LINKS ONTO THE PITCH HORN CAME LOOSE. THIS CAUSED A VIBRATION FELT IN THE PEDALS. THE TAILROTOR HUB WAS 2400 HOURS TSO AND BLADES WERE 2300 TSN. THERE IS NO REQUIREMENT TO OVERHAUL THE PITCH HORNS SO NO RECORD AS TO TOTAL TIME SINCE NEW ON THE PITCH HORNS. IF LEFT UNATTENDED THIS MAY HAVE CAUSED FURTHER FLIGHT SAFETY AND UNCONTROL OF THE TAIL ROTOR.                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H2SW    E4CE                 
             20081117     EA  2008       11         17         CA080813003      120080812G2910AE4760H0592055  HYDRAULIC LINE                          CNDAIRCL601 CL6013A     8070802EA  GE    CF34  CF343A2     30067NE                              HYDRAULIC SYS   BURST           W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA       4785                                                           (CAN) IN FLIGHT NR 2 HYDR "LO PRESS" CAME ON, FWD BY "LO LEVEL".  NR 2 HYDR FLUID COMPLETLY LOST THROUGH A BURST HYDR PRESSURE HOSE IN RT NACELLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20081117     CE  2008       11         17         CA080813004      120080806G325055656195        ARM                                     CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              NLG STEERING    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      CA       6500                                                           (CAN) CAMPAIGN NOTICE 851-53-11-047 WAS BEING ACCOMPLISHED WHEN DAMAGE TO THE NOSE GEAR STEERING ARM WAS DISCOVERED. THE FWD ATTACHMENT HARDWARE REMOVED FROM THE CHANNEL-TRUNION BRACE WAS FOUND TO BE MS27039-1-10 AND AN960-3 WASHERS, WHEN MS27039-1-07 AND NIL WASHERS ARE CALLED FOR IN THE MFG IPC. THE LENGTH OF THE INSTALLED SCREWS WERE SUCH THAT WHEN FULL NOSE WHEEL DEFLECTION WAS ACHIEVED THERE WAS INTERFERENCE BETWEEN THE SCREW AND THE STEERING ARM CAUSING THE DAMAGE.  STEERING ARM P/N 5565619-5 REPAIRED IAW ASEO 851-32-50-0212 BLEND REPAIR.  CORRECT HARDWARE (MS27039-1-07 SCREWS AND MS21042-3 NUTS) INSTALLED ON CHANNEL-TRUNION BRACE.                                                                           1L72 4F4  F  A22CE   E1NE                 
             20081117     EA  2008       11         17         CA080813005      120080812G2751756158          TORQUE SENSOR                           DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  TE FLAP         INOPERATIVE     W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) FLAP DRIVE CAUTION LIGHT IN CRUISE. ELECTED TO RETURN A/C TO DEPARTURE FOR REPAIR.  CONFIRMED FAULT TO TORQUE SENSOR ASSY S/N:0570 (ROGUE UNIT).  WHEN LT SWITCH IS COLD SPRAYED "FLAP DRIVE" CAUTION LIGHT COMES ON WITH TQ SENSOR CENTERED.  TORQUE SENSOR ASSY P/N:756158 REQUIRES REPLACEMENT.  (RESOLVED ON W/O: 27127 TASKCARD: NR-00001)  FLAP DRIVE TORQUE SENSOR ASSY REPLACED. RII INSPECTION COMPLETED.                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081119     EA  2008       11         19         CA080813006      220080801G8520SL18840         CAMSHAFT                                CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              ENGINE          WORN            W      K   NONE                                                                                            R  PARTIAL RPM/PWR LOSS                                                          ININSP/MAINT     1                      CA       1150                                                           (CAN) NR 3 AND NR 4 INTAKE LOBE IS ROUNDED OFF AND SUBSEQUENTLY METAL WAS FOUND IN THE OIL FILTER DURING ROUTINE MX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
             20081117     EU  2008       11         17         CA080813007      120080812G55445554012215      COVER PLATE                 5554012038  PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  RUDDER          DAMAGED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TOTAKEOFF        1                      CA       19069                                                          (CAN) PILOT INDICATES RUDDER MOVEMENT STIFF.  MORE RT RUDDER REQUIRED AT TAKE-OFF. INSP BY MAINT REVEALED THAT THE COVER PLATE AT THE BOTTOM OF THE RUDDER WAS BENT OUT OF SHAPE CAUSING INTERFERENCE WITH THE RUDDER MOVEMENT. INSP OF OTHER ACFT REVEALS THAT THIS COVER PLATE CAN RUB ON THE RUDDER STOP OVER TIME AND MAY BE THE BEGINNING OF THE CAUSE OF THIS PROBLEM.                                                                                                                                                                                                                                                                                                                                                                    1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081117     CE  2008       11         17         CA080813008      120080813G3097                WIRE                                    CESSNA208   208         2073702CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  DEICE SYS       CHAFED          W      K   NONE                                                                                            N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) PILOT REPORTED INTERMITTENT "DE-ICE PRESSURE" ANNUNCIATOR ILLUMINATION WHEN DE-ICE WAS NOT SELECTED. ON INVESTIGATION A CHAFED WIRE WAS FOUND IN ZONE 527. THE WIRE HAD CHAFED ON THE LT CABIN ENTRY LIGHT FIXTURE CAUSING AN INTERMITTENT SHORT TO GROUND ACTIVATING THE LIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3T3  TNTA37CE   E4EA    5  CP60GL    
             20081118     SW  2008       11         18         CA080813009      120080320G6420212011701       BELLCRANK       BELL        212011701   BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              TAIL ROTOR      IMPROPER PART   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIGHT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WERE INSTALLED FOR THE PARTICULAR P/N OF THE T/R HUB ASSY. THIS A/C HAS T/R HUB ASSY P/N 212-011-701-125 INSTALLED AT THIS TIME.                                                                                                                                                                                                                                                                                                                                                                   1G71 4U4  U  H4SW    E22EA                
             20081118     SW  2008       11         18         CA080813011      120080526G6410                BLADE                                   BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              TIAL ROTOR      UNKNOWN         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSP OF T/R HUB AND BLADE ASSY REVEALED AN INTERFERENCE BETWEEN BOTH T/R BLADES AND T/R YOKE AT THE LEADING EDGE/ROOT. T/R BLADES REMOVED AND DRESSED OUT TO PROVIDE .010" CLEARANCE BETWEEN YOKE AND BLADES (IAW PSE). YOKE INSPECTED FOR DAMAGE, NONE FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 4U4  U  H4SW    E22EA                
             20081119     NE  2008       11         19         CA080813012      220080811G7250                TURBINE                                 SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              ENGINE          FAILED          W      BR  EMER. DESCENT           AUTOROTATION                                                            KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) HELICOPTER WAS RETURNING TO AIRPORT, ENGINE CHIP LIGHT CAME ON, FOLLOWED SHORTLY BY A POPPING SOUND FROM ENGINE, A VIBRATION IN AIRFRAME & LOW ROTOR HORN. AN AUTOROTATION INITIATED & WHEN PILOT FLARED TO LAND, NOTICED ENGINE STILL DEVELOPING POWER.  ACFT LANDED UNDER POWER WITH NO FURTHER INCIDENT.  INITIAL INVESTIGATION SHOWED MANY BIG CHUNKS OF METAL ON CHIP PLUGS & IN OIL STRAINERS. METAL ALSO FOUND ON ENGINE DECK. REAR BEARING VENT LINE FOUND OFF THE 2 OCLOCK VENT STRUT & A LARGE AMOUNT OF OIL BLOWN OUT VENT ONTO ENGINE, ENGINE DECK & TAILBOOM (APPROX. 2 QUARTS LOST). THIS WOULD EXPLAIN INTENSE SMOKE OBSERVED COMING FROM ENGINE DURING AUTOROTATION & LANDING. RUBBING NOISES CAN BE HEARD WHEN TURNING C1G71 3U3  U  H9EU    E19EU                
             20081118     NE  2008       11         18         CA080814001      220080703G7200                ENGINE                                  BAG   ATP   ATP                EU  PWA   PW120 PW126A           NE                                              FLAMED OUT      W      K   NONE                                                                                            XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT AND THEN RELIT (AUTO RELIGHT) WITHIN 2 SEC. THE OCCURRENCE HAPPENED APPROXIMATELY 10 MIN. AFTER ENCOUNTERING SEVERE WEATHER INCLUDING HAIL AND MODERATE TURBULENCE. THE FLIGHT CONTINUED TO DESTINATION WITHOUT FURTHER PROBLEMS. POST FLIGHT INSPECTION SHOWED NO DAMAGE AND THE A/C CONTINUED IN SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA27NM   E2ONE                
             20081118     NE  2008       11         18         CA080814002      220080428G7200                PLANETARY GEAR                          CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          DISTRESSED      W      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER T/O, THE PILOT NOTED ENGINE VIBRATION FOLLOWED BY AN OIL PRESSURE DROP. HE RETURNED TO THE POINT OF DEPARTURE WHERE AN UNEVENTFUL LANDING WAS PERFORMED UNDER POWER. THE ENGINE WAS FWDED TO MFG WHERE 1ST STAGE PLANET GEAR DISTRESS WAS FOUND. THE AFFECTED HARDWARE WILL BE RETURNED TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA                 
             20081118     NE  2008       11         18         CA080814003      220080730G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FOD             W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      (CAN) PILOT ABORTED TAKE-OFF DUE TO ENGINE POWER LOSS. POST FLIGHT INSP REVEALED POWER TURBINE AND 1ST STAGE COMPRESSOR FOD. ENGINE WAS REMOVED AND SENT FOR EVALUATION AND REPAIR. SUSPECT HARDWARE WILL BE FWDED TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA                 
             20081119     NE  2008       11         19         CA080814004      220080809G7261                LINE                                    BOEING767   7673Y0             NM  GE    CF6   CF680C2B6F  30025NE                              ENGINE OIL SYS  CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) NR 1 ENGINE DUE HOC OCCURRED AUG 8/9. ON INVESTIGATION IT APPEARS THERE IS A LEAK FROM THE TAIL BEARING HOUSING FEED TUBE NEAR THE AFT SUMP HOUSING &  REPLACED THE OIL FEED LINE. ACTUAL ROOT CAUSE IS NOT YET KNOWN (CRACKED LINE LOOSE OR DAMAGED FITTING). OIL TRENDING DID NOT SHOW ANY CONSUMPTION OR PRESSURE ANOMALIES PRIOR TO THE EVENT.                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA1NM    E13NE                
             20081118     NE  2008       11         18         CA080814005      220080730G7200                ENGINE                                  CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              LEFT            POWER LOSS      W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKE-OFF, THE LT ENGINE POWER ROLLED BACK ABOUT 8-10 PERCENT. WHILE ON CLIMB AND WHILE LEVELING-OFF AT 6,000 FT, SEVERAL OTHER ROLL-BACKS WERE NOTED. ACCORDING TO THE PIC, THESE SEEMED TO OCCUR AFTER A TLA ADJUSTMENT. CREW STABILIZED ACFT AT 6,000 FT AND DECIDED TO DIVERT. AN UNEVENTFUL DUAL ENGINE LANDING WAS ACCOMPLISHED. TROUBLESHOOTING REVEALED POSSIBLE ISSUE WITH LT ENGINE FCU. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                             2L72 4F4  FRCT00012WIE35NE                
             20081118     EA  2008       11         18         CA080814006      120080812G77326233M30A        TRANSDUCER                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              VIBRATION ANLYZRUNSERVICEABLE   W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      (CAN) ON THE TAKE-OFF ROLL AT APRX 60KTS, THE FLIGHT CREW REJECTED TAKE-OFF DUE TO AN N2 ENGINE VIBRATION CAUTION MESSAGE.   VIBE ICON ON LT ENG APPROX 87 PERCENT. SECOND RUN REVEALED NO VIBE RISE ON INDICATOR BUT GETTING VIBE AMBER MESSAGE. CREW DID NOT FEEL ANYTHING BUT WANTED INSP BEFORE APPLYING MEL.   LT N2 VIBE `VIB` ICON INDICATES CORE HAS EXCEEDED 1.7 MILS. N1 VIBE INDICATION AND NEEDLES WILL NOT CORRELATE TO AN N2 VIBE INDICATION. NO CHIP FLAGS NOTED. BORESCOPE INSP OF COMPRESSOR AND HP TURBINE CARRIED OUT AND FOUND WITHIN LIMITS.  NR1 ENGINE VIBE TRANSDUCER REPLACED. HIGH POWERED RUNS CARRIED OUT AND VIBE INDICATIONS ALL CHECK OK. SYSTEM CHECKED SERVICEABLE.                                            2L72 4F4  FRTA21EA   E15NE                
             20081118     EU  2008       11         18         CA080814007      120080814G3246Z0DN6068757295  WHEEL HALF                  PARKER40270 SOCATATBM   TBM700      8682000EU                                                               RT MLG          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) DURING LANDING ROLL, PILOT NOTICED ABNORMAL "FEEL" OF ACFT AND STEERING.  DISCOVERED FLAT TIRE ON RT MAIN WHEEL. ACFT RECOVERED FROM RUNWAY. DISASSEMBLED WHEEL AND PERFORMED DYE PENETRANT INSP ON WHEEL HALVES. CRACK INDICATION VERY EVIDENT IN INNER BEAD RADIUS OF OUTER WHEEL HALF SUB-ASSEMBLY, AND ALSO VISIBLE ON OUTER SURFACE. PART IS SUBJECT TO REPETITIVE NDT INSPECTIONS. WHEEL HALF SUB-ASSEMBLY REPLACED.                                                                                                                                                                                                                                                                                                                1L71 3T    RTA60EU                        
             20081118     NE  2008       11         18         CA080814008      220080802G7200                ENGINE                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              LEFT            MALFUNCTIONED   W      K   NONE                                                                                            Y  ENGINE STOPPAGE                                                               APAPPROACH       1                      CA                                                                      (CAN) WHILE ON APPROACH, THE LT ENGINE ROLLED BACK AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. WHILE CREW WAS PERFORMING EMERGENCY CHECKLIST FOR ENGINE SHUTDOWN.  THE LT ENGINE SHUTDOWN ON ITS OWN.  ACFT LANDED WITHOUT INCIDENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA22CE   E00053EN             
             20081118     NE  2008       11         18         CA080814009      220080804G7200                ENGINE                                  EMB   120   EMB120      3260201SO  PWA   PW118 PW118B           NE                                              MALFUNCTIONED   W      EC  ENGINE SHUTDOWN         ABORTED TAKEOFF                                                         J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) WHILE ON INITIAL TAKEOFF ROLL PHASE, PILOT APPLIED POWER ON BOTH ENGINES BUT NOTICED FUEL AND OIL PRESSURE DECREASING ON ONE ENGINE. PILOTS DECIDED TO ABORT TAKEOFF, SHUTDOWN THE AFFECTED ENGINE AND RETURN TO GATE.   MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA31SO   E20NE                
             20081118     NE  2008       11         18         CA080814010      220080804G7200                ENGINE                                  CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              NR 1            SHUTDOWN        W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA                                                                      (CAN) THE ACFT WAS ON A FIREFIGHTING MISSION. JUST AFTER A WATER DROP, AS THE PILOT APPLIED FOR POWER, THE NR1 ENGINE WENT INTO AUTOFEATHER AND SHUTDOWN BY ITSELF. THE PILOT FOLLOWED PROCEDURES AND RESTARTED THE ENGINE. THE ACFT LANDED SAFELY. TROUBLESHOOTING IS FOCUSING ON ELECTRICAL HARNESS AND POSSIBLE OVERTORQUE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA14EA   E20NE                
             20081119     NM  2008       11         19         CA080814011      120080806G5330                LAP JOINT                               EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FUSELAGE        LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7037                                                           (CAN) INITIALLY SNAGGED BY A FAA INSPECTOR FOR TRACES OF AIR LEAK AT THE LAP JOINT BELOW THE 7TH WINDOW ON THE LT SIDE (NEAR FR74, STR12L). FURTHER INVESTIGATION IN YYZ DISCOVERED THAT THERE WAS A TOTAL OF 12 LEAK POINTS ON THE LT AND 11 ON THE RT SIDE. THE ACFT DID PASS THE AMM CABIN PRESSURIZATION LEAKAGE TEST (21-31-00).                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA56NM   E00063EN             
             20081119     NE  2008       11         19         CA080814012      220080804G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 MBJOVER TEMP                 SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        TOTAKEOFF        1                      CA                                                                      (CAN) AT THE BEGINNING OF THE TAKE-OFF ROLL, PILOT REPORTED NO RESPONSE TO THROTTLE LEVER MOVEMENT, WITH T4.5 INDICATED TEMPERATURE PEAKING AT 870 TO 900 C. THE TAKE-OFF WAS SAFELY ABORTED. THE ENGINE TEMPERATURE REMAINED HIGHER THAN THE SISTER ENGINE AFTER SHUTDOWN AND A BURNED ODOR WAS NOTICED, WITH SOME SMOKE COMING FROM THE EXHAUST. ENGINE IS BEING REMOVED AND SENT FOR INVESTIGATION.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                           2L72 4F4  FRTA10CE   E35NE                
             20081119     EA  2008       11         19         CA080814013      220080812G7200                ENGINE                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              LEFT            FAILED          W      C   ABORTED TAKEOFF                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKE OFF ROLL AT AROUND 60 KNOTS, LT ENGINE ITT ENGINE WARNING ILLUMINATED AND CREW FELT THE ACFT YAW. ENGINE WAS SECURED AND ACFT RETURNED TO GATE WITHOUT INCIDENT. METALLIC DEBRIS OBSERVED ON THE RUNWAY AND IN ENGINE EXHAUST DUCT. ENGINE TO BE REMOVED AND SENT TO PWC FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN             
             20081119     WP  2008       11         19         CA080815001      220080811G7321                FUEL CONTROL                            DORNERDO228 DO228202    2992030EU  GARRTTTPE331TPE3315     01514WP                              NR 1 ENGINE     MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT WAS RELEASED TO A SATISFACTORY TEST FLIGHT FOLLOWING NR 1 ENGINE CHANGE.  A NTS IN FLIGHT SHUT DOWN WAS TO BE PERFORMED BEFORE ACFT COULD BE RELEASED BACK TO SERVICE. ACFT DEPARTED AND HAD A NORMAL TAKE OFF AND PROCEED WITH NTS SHUT DOWN. PILOT PROCEEDED TO PULL SPEED LEVER BACK FOR FUEL SHUT AND THEN TO FEATHER POSITION AND THEN ENGINE SHUT DOWN AND FEATHERED & ALL WAS NORMAL. PILOT THEN PROCEEDED TO TAKE SPEED LEVER OUT OF FEATHER TO SPEEDS LOW TO RESTART ENGINE AND FOUND THE SPEED LEVER WAS JAMMED AND WOULD NOT MOVE. PILOT THEN LANDED ACFT SINGLE ENGINE WITH NO PROBLEMS. SPEED LEVER CONTROLS WERE CHECKED AND FOUND THAT THE LEVER ON THE FCU WAS OVERCENTERING CAUSING THE JAMMING OF THE CONTROLS. ENG2H72 4T4  TRTA16EU   E4WE                 
             20081119     NM  2008       11         19         CA080815002      120080813G24324011769         BATTERY                                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MASTER          OVERHEATED      W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         MJ OVER TEMP                 WARNING INDICATION                                  CLCLIMB          1                      CA       21080478                                                       (CAN) DURING CLIMB OUT FROM YWK, THE CREW RECEIVED A "MAIN BAT HOT" RED WARNING MSG ASSOCIATED WITH A HIGH TEMPERATURE ON THE BATTERY TEMPERATURE MONITOR. THE ACFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX CONFIRMED THE BATTERY SUFFERED FROM A THERMAL RUN-AWAY. THE MAIN BATTERY WAS REPLACED AND THE ACFT RETURNED INTO SERVICE. THE BATTERY TEMPERATURE WAS NOT RECORDED.                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081119     NE  2008       11         19         CA080815004      220080812G7200                ENGINE                                  CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              RIGHT           FIRE            W      A   UNSCHED LANDING                                                                                 A  FLAME/FIRE                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) DURING A FIRE FIGHTING MISSION, RT ENGINE WAS SHUT DOWN DUE TO A FIRE WARNING. AN EMERGENCY WAS DECLARED, ACFT DIVERTED AND LANDED SAFELY. POST FLIGHT INSPECTION REVEALED EVIDENCE OF A FIRE EXTERNAL TO THE ENGINE CASING WITH DAMAGE TO FIREWALL. A MANUFACTURER FIELD SUPPORT REPRESENTATIVE WILL BE ON SITE 14 AUG TO SUPPORT ON SITE INVESTIGATION.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA14EA   E20NE                
             20081119     EA  2008       11         19         CA080815005      220080803G7314                SPLINE                                  BEECH STC   STC90BEECH             PWA   PT6   PT6A20      52043EA                              FUEL PUMP       WORN            W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) DURING SKYDIVING OPS, SHORTLY AFTER TAKE-OFF ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. IT WAS REPORTED THAT PILOT WAS ATTEMPTING TO RETURN TO THE POINT OF DEPARTURE WHEN THE ACCIDENT OCCURRED. PRELIMINARY ASSESSMENT OF ENGINES REVEALED LT ENGINE WITH SEVERELY WORN FUEL PUMP SPLINE. ENGINES WILL BE FORWARDED TO MANUFACTURER MONTREAL FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                            1L72 3O3  T  3A20    E4EA                 
             20081119     EA  2008       11         19         CA080815006      220080713G8520LW15288         CONNECTING ROD                          PIPER PA44  PA44180     7104402SO  LYC   O360  LO360E1A6   41514EA                              NR 4 CYLINDER   BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE FAILED DUE TO FAILURE OF NR 3-4 CONNECTING RODS. I WAS NOT ABLE TO REMOVE NR 3 OR 4 CYLINDER DUE TO FLANGES BENT OVER ON INSIDE OF CRANK CASE CRANK SHAFT MAY HAVE FAILED.  FOR FURTHER INFO CONTACT: FRANK FILION                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A19S0   E286                 
             20081112     NM  2008       11         12         CA080815009      120080117G3240                BRAKE                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              MLG             CHATTERING      W      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AS REPORTED BY FLIGHT CREW: LT BRAKE CHATTERS WHEN PRESSED, VERY PRONOUNCED AT TIMES CARBON DISK FAILURE CONFIRMED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA56NM   E00063EN             
             20081112     NM  2008       11         12         CA080818001      120080814G2913661733          PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       4815                                                           (CAN) DURING CRUISE OPERATION FLIGHT CREW OBSERVED NR 1 HYDR SYS CAUTION LIGHT ON, FLIGHT DIVERTED TO BASE. CREW CONFIRMED NO PRESSURE FROM NR 1 EDP SELECTED SPU CONFIRMED PRESSURE 3000 PSI AND NO QUANTITY LOSS. ON GROUND TROUBLESHOOTING REVEALED EDP HAD 5 PUNCTURES THROUGH CASING & SOURCE OF SMALL AMOUNT OF HYDR FLUID LOSS. NR 1 ENGINE DRIVEN PUMP REPLACED.                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081113     CE  2008       11         13         CA080818002      120080707G2730                CONTROLLER                              BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  ELEVATOR        FROZEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) APPROXIMATELY 50 MIN OUT, AUTOPILOT BEGAN TO CLIMB, THE A/P WAS DISCONNECTED AND ACFT MANUALLY BROUGHT BACK TO ALTITUDE. A/P WAS REENGAGED AND THEN BEGAN TO DESCEND FOLLOWED BY THE AP TRIM FAIL ANN. A/P DISCONNECTED, ELECTRIC TRIM CHECK AND APPEARED SERVICEABLE FLIGHT WAS CONTINUED. ON DESCENT, TRIM WAS NOTED TO HAVE LITTLE EFFECT AND EXCESSIVE CONTROL FORCES WERE REQUIRED. AFTER LANDING THE TRIM WAS INSPECTED AND THE ELEVATOR WAS FOUND TO BE FROZEN IN A NOSE UP POSITION. AN AME WAS DISPATCHED TO INSPECT THE FLIGHT CONTROLS AFFECTED. THE ENTIRE ELEVATOR AND TRIM SYS WAS INSPECTED WITH NO DISCREPANCIES NOTED. AUTOPILOT SYS AND SERVOS INSPECTED AND TESTED WITH NO FAULTS NOTED. ELEVATOR AND TRIM JACKS WERE L2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20081113     EU  2008       11         13         CA080818003      120080806G750032156281        O-RING                                  ISRAEL1125  ASTRASPX    4500205EU  GARRTTTFE731TFE73140    29001NE                              BLEED SYSTEM    FAILED          W      A   UNSCHED LANDING                                                                                 MJ OVER TEMP                 WARNING INDICATION                                  CLCLIMB          1                      CA       3008 3008                                                      (CAN) RT BLEED LEAK LIGHT ILLUMINATED IN CLIMB OUT. AC RETURNED TO BASE. CONFIRMED LT BLEED LEAK ON GROUND DURING HIGH POWER ENGINE RUNS. COULD NOT DUPLICATE RT BLEED LEAK ON GROUND. FOUND BOTH BLEED SWITCHING VALVES LEAKING FROM REGULATOR FITTING ASSY.  DUE TO BAKED O-RINGS ALLOWING HIGH PRESSURE BLEED AIR INTO AFT EQUIPMENT BAY AREA. THIS CAUSED THE SUBSEQUENT ACTIVATION OF BLEED LEAK WARNING ILLUMINATION AT 250 DEG F. BOTH VALVES REPLACED O-RING NOT FIELD REPLACEABLE.                                                                                                                                                                                                                                                     2L72 4F4  FRTA16NM   E1NM                 
             20081113     CE  2008       11         13         CA080819001      120080814G25105055301401      CABLE ASSY                              CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              SEAT            BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       325                                                            (CAN) ON AUGUST 14, 2008, PILOT REPORTED "PILOT SEAT DOESN`T MOVE BACK, COULD NOT GET OUT". INVESTIGATION BY MAINT FOUND THAT THE CABLE ASSEMBLY FOR THE PILOT SEAT SECONDARY SEAT STOP HAD FAILED PREVENTING THE INERTIAL REEL FROM RELEASING TO ALLOW THE SEAT TO MOVE. THE CABLE HAD BROKEN IMMEDIATELY AFTER THE SWAGED END.                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274                 
             20081113     EA  2008       11         13         CA080819002      120080715G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) "F/O SIDE WINDOW SHATTERED JUST AFTER TAKE OFF (RETURNED), DETERMINED TO BE CENTER PANE". REMOVED AND REPLACED THE F/O`S SIDE WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
             20081113     EA  2008       11         13         CA080819003      120080715G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) "F/O WINDSHIELD SHATTERED ENROUTE, DIVERTED ". REMOVED AND REPLACED THE F/O`S WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
             20081113     EA  2008       11         13         CA080819004      120080815G5610NP1393215       WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       14795                                                          (CAN) "DISC - AFTER TAKEOFF CAPTAIN`S WINDSHIELD CRACKED. NO OTHER PROBLEMS NOTED. REMOVED AND REPLACED PILOTS WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E00063EN             
             20081113     EA  2008       11         13         CA080819005      120080816G5610NP13932210      WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       12265                                                          (CAN) DISC - IN CRUISE FLIGHT, F/O SIDE WINDSHIELD CRACKED AND WINDSHIELD HEAT ON RT SIDE FAILED.. ACFT RETURNED. NO PRESS PROBLEM. ALL OTHER SYS NORMAL. REMOVED AND REPLACED F/O SIDE WINDOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E00063EN             
             20081113     NM  2008       11         13         CA080819006      120080818G29135116403         PUMP                                    EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              HYD SYSTEM      FAILED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) WHILE ENROUTE, THE NR 1 HYD SYS FAILED. AFTER CONSULTATION WITH MAINT, FLIGHT CONTINUED AND LANDED WITHOUT INCIDENT.  NR 1 EDP REPLACED REF AMM 29-11-01 PB 401,-422 AND TESTED REF AMM 29-11-01 P 501-5  12.  NO FAULTS OR LEAKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA57NM   E00070EN             
             20081118     EU  2008       11         18         CA080819008      120080805G6230                NUT                                     BOLKMS117   BK117B2     5626013EU  LYC   LTS101LTS101750B1 41560NE                              MAIN ROTOR      LOOSE           W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA                                                                      (CAN) VIBRATION NOTICEABLE ON COLLECTIVE CONTROL PWR CHANGES. FURTHER INVESTIGATION REVEALED THAT THE MAIN ROTOR MAST HAD .2500 INCH VERTICAL PLAY. ON THE REMOVAL PROCEDURE OF THE MAIN ROTOR MAST FROM THE GEARBOX IT WAS NOTED THAT THE MAST NUT HAD NO TORQUE. A THOROUGH INSPECTION OF THE ACCESSIBLE GEARBOX COMPONENTS WAS CONDUCTED WITH NO FAULTS DETECTED, THE MAIN ROTOR MAST WAS REINSTALLED AND THE ACFT FLOWN WITH NO FURTHER VIBRATION DETECTED.                                                                                                                                                                                                                                                                                 1G72 3U3  UNCH13EU   E5NE10               
             20081118     GL  2008       11         18         CA080819009      120080815G323417C17616A3      VALVE                                   BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              LANDING GEAR    UNKNOWN         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) DURING FINAL APPROACH THE PILOT SELECTED THE LANDING GEAR DOWN AND THERE WAS NO MOVEMENT. MOMENTARILY THE PROX SYS FAULT CYAN CAS POSTED, BUT CLEARED WITHIN SECONDS. THE PILOT PUT THE GEAR HANDLE BACK UP. THEN SELECTED IT BACK DOWN. AGAIN THE GEAR DID NOT MOVE.  HE THEN GRABBED THE QRH AND CARRIED OUT THE EMER PROCEDURES TO DEPLOY THE GEAR. WHEN THE EMER LG HANDLE WAS PULLED THE GEAR DEPLOYED AND ACHIEVED 3 GREEN IN A FEW SECONDS. THE LANDING WENT SMOOTHLY.                                                                                                                                                                                                                                                             2L72 4F4  FRTT00005NYE00010LA             
             20081118     SW  2008       11         18         CA080819010      120080808G243523079010        STARTER GEN                             FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR 29081NE  MCAULY4HFR344HFR34C652  NE  RIGHT           FAILED          W      K   NONE                                                                                            J  WARNING INDICATION                                                            DEDESCENT        1                      CA            710                                                       (CAN) UPON DESCENT, THE RT GENERATOR FAILED AND COULD NOT BE RESET. MAINT WAS CALLED UPON LANDING AND FOUND THE AFT PART OF THE STARTER GENERATOR HAD FAILED. REAR COVER WAS DESTROYED, REAR FAN BLADES WERE ALL BROKEN AND REAR BEARING WAS DESTROYED. UNIT REPLACED AND ACFT CHECKED SERVICEABLE. INVESTIGATION INTO FAILURE PENDING.                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081124     SW  2008       11         24         CA080819011      120080810G75008943825         TUBE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE3311     01514WP  MCAULY4HFR344HFR34C652  NE  LT ENGINE BLEED FRACTURED       W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) TUBE HAD BROKEN AT WELDMENT THAT ATTACHES THE TUBE TO THE FLANGE THAT BOLTS IT TO THE ENGINE BLEED.  AIR PORT WAS CRACKED 90% OF THE WAY AROUND WELD.  THIS CAUSED THE ENGINE TO NOT REACH TARGET TORQUES UNLESS WATER METH WAS USED.  UNIT WAS REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T3  TRTA8SW    E3WE    6  C3PNE     
             20081118     EU  2008       11         18         CA080819012      120080817G2750945020220       DRIVE SHAFT                             PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  TE FLAP         SHEARED         W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       6330                                                           (CAN) LT INBD FLAP FLEXABLE DRIVE SHAFT SHEARED AT INBD DRIVE END.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081120         2008       11         20         CA080819013      420080812G612210185           COTTER PIN                              DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  GOVERNOR        MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ENG INSP, TWO COTTER PIN TAILS WERE FOUND IN ENG ACCY SUMP. INVESTIGATION INTO SOURCE OF PIN TAILS REVEALED THAT COTTER PIN (P/N 10185) SECURING NUT (P/N 23212) FOR GOVERNOR DRIVE GEAR SHAFT (P/N 2715) IN ACCY SECTION WAS MISSING. THERE WAS EVIDENCE OF PIN HAVING GONE THROUGH THE GEARS AND REDUCED TO METAL PARTICLES. OVERHAUL SHOP WAS CONTACTED AND REVEALED THAT THEY HAD A NEW EMPLOYEE ASSEMBLING THIS SECTION OF ENG, AND WAS USING STANDARD COTTER PIN INSTALLATION PROCEDURE. IN THIS LOCATION, IF THE PIN IS INSTALLED WITH  TAIL FOLDED BACK OVER END OF SHAFT, IT WILL CONTACT INSIDE OF GOVERNOR BASE AND BREAK OFF. ONCE THIS HAPPENS, THE SHORT END OF COTTER PIN CAN ROTATE AND ALSO CONTACT THE INSIDE OF 1H71 3R3  RRCA806    5E1     5  CP28EA    
             20081118     EA  2008       11         18         CA080820001      220080817G7261766859C         SCAVENGE PUMP                           BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 ENGINE     LOOSE           W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            DEDESCENT        1                      CA       3083                                                           (CAN) AT 15000 FT IN THE DESCENT, THERE WAS A SUDDEN LOSS OF OIL PRESSURE ON THE NR 2 ENG. GAUGE INSTANTLY SHOWED ZERO WITH THE NR 2 OIL PRESS WARNING AND CHIME. CREW IMMEDIATELY SHUT DOWN THE NR 2 ENG, TAKING ABOUT 5 TO 10 SECONDS TO COMPLETE MEMORY ITEMS. AFTER ENGINE/PROP FEATHERED, THERE SEEMED TO BE NO OTHER PROBLEMS.   CASTELLATED NUT ON THE OIL SCAVENGE PUMP FOUND LOOSE. WITH INPUT SHAFT ROTATING THE SPUR GEAR WAS NOT ROTATING WHICH WAS DRIVE FOR THE ADJACENT SHAFT.  RGB SCAVENGE IS LOCATED ON THIS SHAFT WHICH WAS NOT ROTATING. OIL SCAVENGE PUMP BEING REPLACED.                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081118         2008       11         18         CA080820002      420080815G5301                RELEASE MECH                            BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                                              MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         HOHOVERING       1                      CA                                                                      (CAN) HELI BASKET D407-663-011 INSTALLED IAW INSTRUCTIONS. DURING TRAINING (SLING OPERATION) MANUAL RELEASE WAS USED AND FUNCTIONED AS NORMAL DURING THE TRAINING SEQUENCE. ON THE NEXT PICK UP, THE LOAD WAS HOOKED UP ON THE HOOK AND THE PILOT PULLED INTO AN HOVER AND THEN THE CABLE RELEASED WITHOUT ANY ACTION FROM THE PILOT. HE LANDED IMMEDIATELY.  FURTHER INVESTIGATION FOUND THE MANUAL RELEASE CABLE SNAG ON THE OUTSIDE OF THE HOLE CENTER FRAME P/N D2796 STATION 115.75 WHICH PREVENTED THE HOOK TO CLOSE SECURELY. MFG HAS BEEN INFORMED ABOUT THE INCIDENT AND PICTURES WERE FORWARDED AS WELL.                                                                                                                              1G71 3U3  UO H2SW    E1GL                 
             20081118     NM  2008       11         18         CA080821001      120080215G3242900005831PR     BRAKE                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 1 BRAKE      MALFUNCTIONED   W      K   NONE                                                                                            J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) NUMEROUS LANDING GEAR NO DISPATCH AND EMERGENCY BRAKE FAULT MESSAGES AFTER TOUCHDOWN NR1 BRAKE REPLACED. CONSIDERED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA56NM   E00063EN             
             20081118     NM  2008       11         18         CA080821002      120080704G3242900005832PR     DISK                                    EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 4 BRAKE      DETERIORATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NR 4 MAIN WHEEL BRAKE CARBON DISK BADLY DETERIORATED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA56NM   E00063EN             
             20081118     NM  2008       11         18         CA080821003      120080714G3242900005832PR     BRAKE                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 1            DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BRAKE ASSY BREAKING UP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA56NM   E00063EN             
             20081118     NM  2008       11         18         CA080821004      120080719G3242900005831PR     BRAKE ASSY                              EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 4            FAILED          W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON PUSHBACK REPORT OF NR 4 BRAKE ASSY FAILURE, AS REPORTED BY STATION SERVICES CREW  BRAKE ASSY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA56NM   E00063EN             
             20081118     NM  2008       11         18         CA080821005      120080802G3242900005831PR     BRAKE ASSY                              EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 2            FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI OUT TO THE RUNWAY, ECAS MESSAGE "BRK LT FAULT" CAME ON. FOUND NR 2 BRAKE ASSY FAILED. (CARBON FAILURE)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA56NM   E00063EN             
             20081118     CE  2008       11         18         CA080821006      120080818G3221030A311201      ATTACH FITTING                          MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE33110    29053NE  HARTZLHCB4T HCB4TN5     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1594915949                                                     (CAN) DURING ROUTINE INSP, THE NOSE LANDING GEAR TRUNNION ATTACH FITTING WAS FOUND TO BE CRACKED. THE CRACK WAS MEASURED AT .3125 OF AN INCH. FITTING REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
             20081118     NM  2008       11         18         CA080821007      120080809G3242900005831PR     BRAKE                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              LT MLG          DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) LT MAIN BRAKE TEMPS OB 365/IB149, RT BRAKES IB 148/OB130, BRAKES FELT SOFT,  BRAKES REPLACED.  CAUSE: CARBON OXIDATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA56NM   E00063EN             
             20081120     SW  2008       11         20         CA080821008      120080820G5311                FRAME                                   BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                              FUSELAGE        CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) HYDR SERVO PILOT VALVE SUPPORT RUBBING AGAINST MAIN FRAME. WEAR MARK IS APPARENT ON LT SUPPORT. PICTURES AVAILABLE ON REQUEST AND INFO FWD TO MFG CUSTOMER SUPPORT FOR ACTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  UNCH2SW    E1GL                 
             20081118     NM  2008       11         18         CA080821009      120080809G324290000582WT      BRAKE                                   EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 1            DISINTEGRATED   W      K   NONE                                                                                            J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) BRAKE NR 1 DISINTEGRATED AND M/W CHANGED DUE TO BRAKE STUCK IN TIRE. BRAKE NR 1 CHANGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA56NM   E00063EN             
             20081118     EU  2008       11         18         CA080821010      120080821G3040320570          SPLICE                                  PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67      52043NE  HARTZLHCE4A HCE4A3D     GL  WINDSHIELD HEAT BURNED          W      O   OTHER                                                                                           MW OVER TEMP                 INADEQUATE Q C                                      ININSP/MAINT     1                      CA       19                                                             (CAN) DURING AN UNRELATED INSTALLATION OF A SATPHONE SYS AN AMP TYPE SPLICE IN THE EXISTING ACFT WIRING WAS NOTED TO BE BURNED AND DISCOLORED. FURTHER INSP INDICATED THAT THE WIRING WAS FOR THE WINDSHIELD HEAT SYS. THE WIRE, NR 1H81A12 AS WAS ALSO DISCOLORED AND BURNED. THERE WERE NO INDICATIONS OF BURNING IN THE SURROUNDING AREA. THE BURNED SPLICE WAS FOUND TO BE POORLY CRIMPED TO THE WIRE. WHEN THE WIRE WAS UNTIED FOR REPAIR IT FELL OUT OF THE SPLICE. THE ADJACENT SPLICE AS DAMAGED AND REQUIRED REPLACEMENT. A FURTHER INSP FOUND ALL 4 SPLICES WERE IMPROPERLY CRIMPED. REMAINDER OF THE WINDSHIELD HEAT WIRING WAS COMPLETED AND NO FAULTS FOUND. THE WIRES 1H83A12,1H85A12,1H80B12,1H81A12 AND SPLICES WERE ALL REPLACE1L71 4T4  TRTA78EU   E26NE   5  CP210NE   
             20081118     SW  2008       11         18         CA080821011      120080215G6210206010200133    BALANCE WEIGHT              206010200133BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              BLADE           DEBONDED        W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              APAPPROACH       1                      CA       3104                                                           (CAN) IT WAS THOUGHT THAT THE BLADE TIE DOWN WAS LEFT ON THE ACFT. THIS WAS NOT THE CASE IAW A REPORT. THE FOLLOWING OCCURRED. INSP AND SCRAPPED THE M/R BLADE DUE TO WEIGHT POCKET RETAINING HOLES DAMAGED BEYOND LIMITS. DAMAGE CAUSED BY TELL TALE LEAD COUPON (SIZE 1.0`X1.0`X.5`) BONDED TO THE TOP SIDE OF INNER SPAR AT STN. 113.5 DEBONDED INFLIGHT AND BEING FLUNG BY CENTRIFUGAL FORCE OUT THE TIP CAP OF BLADE. THE CENTRIFUGAL FORCE OUT THE TIP CAP OF COUPON HAD ENOUGH INERTIA TO PUSH OUT THE WEIGHT POCKET ON THE T/E SIDE AND TEAR THE SCREWS OUT OF THE SPAR RETAINING HOLES OF TOP AND BOTTOM SPAR AT T/E SIDE OF SPAR. TIP CAP WAS BENT ON L/E AND T/E UNTIL THEIR WAS SUFFIENT OPENING TO ALLOW THE LEAD COUPON TO EXIT BL1G71 3U3  U  H2SW    E4CE                 
             20081118     CE  2008       11         18         CA080821012      120080817G561066561000010     WINDSHIELD                              LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              COCKPIT         BROKEN          W      O   OTHER                                                                                           Z  SIGNIFICANT FAILURE REPORT                                                    CRCRUISE         1                      CA                                                                      (CAN) WHILE IN CRUISE AT FLT 400 ENROUTE, THE RT WINDSHIELD OUTTER PLY SHATTERED, CAUSING A LOUD BANG. NO DEPRESSURISATION OCCUR, RT WINDSHILED HEAT BECAME INOPERATIVE. RT WINDSHIELD REPLACED WITH NEW ONE. ACFT RETURN TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTT00008WIE6WE                 
             20081118         2008       11         18         CA080821013      420080818G3416066030620010    ALTIMETER                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL                  DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA            466                                                       (CAN) PILOT REPORTED THAT AUTOPILOT CAUSING ACFT TO PORPOISE ON DESCENT FROM 18,000 FT (WHEN BARO RESET), THEN GOES AWAY. REPLACED ENCODING ALTIMETER AND PROBLEM SOLVED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081118     WP  2008       11         18         CA080822001      120080728G6310C0511           ACTUATOR                                ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CLUTCH          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      CA       788                                                            (CAN) THE CLUTCH ACTUATOR WOULD NOT FULLY ENGAGE, SERVICABLE ACTUATOR INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   E295                 
             20081118     NE  2008       11         18         CA080822002      220080731G732225766304        SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       1595                                                           (CAN) THE ENGINE HAD ROUGH IDLING, TROUBLESHOOTING REVEALED AN EXCESSIVE AMOUNT OF FUEL WAS BEING INJECTED OUT OF THE FUEL INJECTORS. INSTALLED A SERVICABLE FUEL SERVO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
             20081118     WP  2008       11         18         CA080822003      120080803G6310C0511           ACTUATOR                                ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CLUTCH          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THE CLUTCH WOULD NOT ENGAGE DURING ACFT START. REPLACED CLUTCH ACTUATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   E295                 
             20081118     WP  2008       11         18         CA080822004      120080804G2435BC3151004       STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            372                                                       (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH SERVICABLE STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20081118     SW  2008       11         18         CA080822005      120080805G2432RG206           BATTERY                                 BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              MAIN            DISCHARGED      W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       157                                                            (CAN) DURING ACFT START, THE BATTERY WAS FOUND WITH NO CHARGE, BATTERY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E4CE                 
             20081118     WP  2008       11         18         CA080822006      120080715G6310C0512           CLUTCH ACTUATOR                         ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       667                                                            (CAN) CLUTCH WOULD NOT ENGAGE, SERVICABLE CLUTCH ACTUATOR INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081118     WP  2008       11         18         CA080822007      120080730G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       623                                                            (CAN) THE STARTER WAS GRINDING DURING START, STARTER REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081118     WP  2008       11         18         CA080822008      120080729G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      CA                                                                      (CAN) THER STARTER WOULD NOT START.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081118     WP  2008       11         18         CA080822009      120080727G2435BC3151004       STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            687                                                       (CAN) STARTER FAILED ON START UP, STARTER REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081118     NE  2008       11         18         CA080822010      220080714G732225766304        FCU                                     ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       1996                                                           (CAN) THE ENGINE WAS RUNNING TOO RICH, TROUBLESHOOTING REVEALED COULD NOT ADJUST FUEL INJECTOR SERVO, REPLACED FCU.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081118     SO  2008       11         18         CA080822011      120080725G3710441CC7          PUMP                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  VACUUM SYS      SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       452                                                            (CAN) DURING INSPECTION THE LT ENGINE VACUUM PUMP FOUND SEIZED, REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081118     WP  2008       11         18         CA080822012      120080718G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      CA       55                                                             (CAN) THE STARTER WAS INTERMITTENT, ON INSPECTION WAS FOUND TO HAVE TEETH MISSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
             20081118     NE  2008       11         18         CA080822013      220080703G732225766304        FCU                                     ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION THE MIXTURE CONTROL FOUND TO BE BINDING IN THE RICH POSITION, REMOVED DUE TO STIFF MIXTURE LEVER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
             20081118     GL  2008       11         18         CA080822014      220080707G7261                LABYRINTH SEAL                          BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H2SW    E4CE                 
             20081124     CE  2008       11         24         CA080822015      120080822G3060                WIRE                                    CESSNA441   441         2076020CE  GARRTTTPE331TPE33110N   29062NE  MCAULY4HFR344HFR34C660  NE  PROP DE-ICE BOOTSHORTED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) AFTER LANDING, THE ACFT EXPERIENCED A SMALL AMOUNT OF SMOKE IN THE COCKPIT, FOLLOWED IMMEDIATELY BY THE SWITCH CIRCUIT BREAKER POPPING.  THE AMMETER FOR THE PROP DE-ICE WAS PEGGED TO THE FULL RT, ONCE THE SYSTEM WAS SWITCHED OFF THE METER STILL INDICATED IN THE GREEN.  MX INSPECTION REVEALED THE WIRE LEAD OFF THE PROP DE-ICE BOOT WAS TOO LONG AND WAS RUBBING AGAINST THE INSIDE OF THE SPINNE.  THE SHORT TO GROUND WENT THROUGH THE BRUSH BLOCK ASSEMBLY TO THE AMMETER IN THE COCKPIT.                                                                                                                                                                                                                                      1L72 3T4  TRTA28CE   E4WE    5  C3PNE     
             20081118         2008       11         18         CA080822016      420080820G34211013800803      GYRO                                    BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  ATTITUDE        FAILED          W      O   OTHER                                                                                           I  FLT. ATTITUDE INST.                                                           UKUNKNOWN        1                      CA                                                                      (CAN) THE RT ATTITUDE INDICATOR IS AN AIR DRIVEN UNIT. THIS ACFT HAS HAD NUMEROUS FAILURES. INTERVALS RANGE FROM SEVERAL MONTHS OR MORE TO A FEW DAYS. GENERALLY IF ONE FAILS, THE NEXT ONE FAILS, AND THEN MAY LAST FOR MONTHS. THESE UNITS HAVE TYPICALLY COME FROM SEVERAL DIFFERENT VENDORS.  THE ACFT SYSTEMS HAVE BEEN CHECKED THOROUGHLY WITH NO FAULTS FOUND. IT RUNS ON VACUUM, AND THE SUCTION IS EXACTLY IN THE MIDDLE OF MM SPECS.  CONTINUING TO MONITOR AND INVESTIGATE THE DEFECT. THERE HAVE BEEN FAILURES ON OTHER ACFT AS WELL, BUT NOT AT THE SAME RATE AS THIS ONE.                                                                                                                                                         2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20081118     NM  2008       11         18         CA080825001      120080825G6120666000459       CONTROL UNIT                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 ENGINE     SHORTED         W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      (CAN) DURING FLIGHT THE PROP SPEED SHOWED 1070 RPM IN DESCENT WITH PEC CAUTION. CREW PREFORMED NR2 ENGINE IFSD AND RETURNED TO BASE.  MAINT REVIEWED CDS AND FOUND FC 160 CH A&B. FIM TASK FOLLOWED AND FOUND MPU SHORTED TO GROUND. MPU REPLACED AND EGR C/O SATIS. ACFT RELEASED FOR SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081118     EU  2008       11         18         CA080825002      120080822G2913993378          PUMP            VICKERS     PPEV3008EA  PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYDRAULIC SYS   CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    APAPPROACH       1                      CA       2220 2220                                                      (CAN) ON LANDING, HYDR PUMP CONTINUED TO CYCLE, AFTER LANDING WHEN ACFT PARKED, HYDR FLUID DRIPPING FROM FUSELAGE NEAR HYDR PUMP LOCATION. WHEN PUMP OPERATED FLUID SPRAYED FROM CRACK IN END PLATE OF PUMP, PUMP ASSY REPLACED WITH SERVICABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081120     SO  2008       11         20         CA080825003      120080814G2750487084          SOLENOID                    4018542     PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  TE FLAP         FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) FLIGHT CREW REPORTED DURING SHORT FINAL, SELECTING THE FLAPS FROM 25 DEGREES TO 40 DEGREES, THE ACFT YAWED SEVERELY. VISUAL CHECK OF THE FLAP REVEALED THE LT FLAP AT FULL DOWN AND THE RT FLAP AT APPROX 25 DEGREES. THE ACFT LANDED WITHOUT FURTHER INCIDENT. MAINT CONFIRMED THE ASYMMETRIC CONDITION AND FOUND THE LT FLAP DRIVING PAST THE "DOWN" LIMIT SWITCH ACTUATION POINT AND THE LT FLAP L/E ALSO BUCKLED AT THE MID-FLAP TRACK AREA. LT AND RT FLAP TRANSMISSIONS, MOTOR AND DRIVE CABLES WERE INSPECTED. SUSPECT THE ASYMMETRIC CONDITION DUE TO LT FLAP DRIVING PAST THE DOWN LIMIT AND THE EXCESSIVE DRIVING TORQUE CAUSED THE INTERNAL DRIVE CABLE SPLINES TO SKIP CAUSING THE SPLIT FLAP CONDITION.  THE FOLLOWING MAINT 1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081118     SO  2008       11         18         CA080825004      120080820G24604817102         CLAMP                                   PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL                  FAULTY          W      O   OTHER                                                                                           G  MULTIPLE FAILURE                                                              ININSP/MAINT     1                      CA                                                                      (CAN) FLIGHT CREW REPORTED ALL FLIGHT CONTROL TRIM AND BOTH ENGINE COWL FLAP INDICATORS INOP. MAINT INVESTIGATION ISOLATED THE VOLTAGE CLAMPER AT FAULT. AFTER REMOVAL OF FAULTY CLAMPER FOUND THE INTERNAL RESISTOR BADLY BURNED AND PARTIALLY MELTED. VOLTAGE CLAMPER P/N 48171-02 REPLACED AND ALL INDICATIONS CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081201     CE  2008       12         1          CA080826001      120080812G32603086070843004   LIGHT                                   BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  MLG INDICATOR   INOPERATIVE     W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         DEDESCENT        1                      CA                                                                      (CAN) LANDING GEAR MOTOR CONTROL CIRCUIT BREAKER FOUND POPPED WHEN THE GEAR WAS SELECTED DOWN FOR LANDING. GEAR WAS LOWERED BY EMERGENCY EXTENSION INDICATING (3) GREEN BUT THE IN TRANSIT LIGHT WAS STILL ON.  ACFT EXPERIENCED A NOSE GEAR COLLAPSE ON LANDING. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THERE WERE NO DIVIDERS IN THE HEAD OF THE GEAR DOWN LIGHT BLOCK. THIS ALLOWED LIGHT FROM THE MAIN GEAR DOWN AND LOCK LIGHT TO ILLUMINATE THE NOSE INDICATOR. IT GAVE A FALSE INDICATION THAT ALL 3 GEAR WERE IN THE DOWN AND LOCK POSITION.   A NEW INDICATOR WAS INSTALLED SHOWING A POSITIVE INDICATION OF THE NOSE NOT LOCKED.                                                                                           2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20081118     EA  2008       11         18         CA080826002      220080824G7321252444057       FCU                                     BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  LT ENGINE       FAILED          W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA            2545                                                      (CAN) WHEN POWER WAS APPLIED TO ENGINE AFTER A TOUCHDOWN, A CONSIDERABLE YAW TO THE LT WAS FELT BY THE PILOTS. ACFT WAS MOVED OFF THE RUNWAY AND A MAINT RUN-UP OF ENGINES INDICATED A POWER LOSS IN THE LT ENGINE.  AFTER TROUBLESHOOTING THE ENGINE A REPLACEMENT FCU WAS INSTALLED. ENG RUNS AND FLIGHTS WERE COMPLETED WITH NO FURTHER PROBLEMS.                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  T  A14CE   E4EA    6  CP15EA    
             20081124     EU  2008       11         24         CA080826003      120080815G2440                UNKNOWN                                 SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE                              GROUND POWER    UNKNOWN         W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) GPU VOLTAGE SPIKED WHILE PROVIDING POWER FOR ENGINE START.  GROUND POWER WAS SHUT OFF AND ENGINES STARTED USING INTERNAL BATTERIES.  BOTH ESSENTIAL DC ELECTRICAL CBS FOUND TRIPPED WHILE PERFORMING TAXI CHECK LIST. RETURNED TO GATE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA52EU   E8NE6                
             20081118     EU  2008       11         18         CA080826004      120080819G3213                STRUT                                   SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE                              LT MLG          CONTAMINATED    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF CHECKS COMPLETED AND CONDITION LEVER RETARDED, RESULTING IN CONFIG WARNING AND OAT LIGHT ILLUMINATING. THIRD OCCURANCE. UNSCHEDULED LANDING MADE. (FUEL BURNED OFF TO ACCOMODATE LANDING WEIGHT) THE LT MLG WAS NOT FULLY EXTENDED DUE TO AIR REMAINING IN THE OLEO. THE LG SERVICING WAS REPEATED USING A POWER SERVICING CART, NO FURTHER FAULTS FOUND ON SUBSEQUENT GEAR SWINGS.                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA52EU   E8NE6                
             20081120     EU  2008       11         20         CA080826005      120080818G3260                SQUAT SWITCH                            SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE                              LANDING GEAR    OUT OF RIG      W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF CHECKS WERE COMPLETED AND CONDITION LEVERS RETARDED, CONFIG WARNING AND OAT LIGHT CAME ON. UNSCHEDULED LANDING COMPLETED, RETURNED TO BASE. GEAR SWING COMPLETED, FAULT NOT DUPLICATED. LANDING GEAR HAD BEEN SERVICED PRIOR TO FLIGHT. RE-SERVICED MLG,  GEAR SWING COMPLETED, NO FAULT FOUND. SECOND TAKEOFF COMPLETED WITH THE SAME RESULTS AS THE FIRST. SECOND UNSCHEDULED LANDING MADE. FLIGHT CANCELLED. LG POSITION WARNING SYS INSP INDICATED A PROBLEM WITH THE LT INBD SQUAT SWITCH RIGGING. SWITCH RE-RIGGED LG SWING COMPLETED, NO FURTHER FAULTS FOUND.                                                                                                                                                       2L72 4T4  TRTA52EU   E8NE6                
             20081118         2008       11         18         CA080826006      120080825G541485410587        SKIN                                                                       PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  LT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A WALKAROUND, THE LT NACELLE SKIN PANEL 85410587 DISPLAYS A SMALL CRACK FROM ONE OF THE UPPER AFT FASTENERS TO THE SKIN EDGE, AND A LARGE 4 INCH+ CRACK RUNNING ALONG THE LENGTH OF THE SKIN PANEL. AS THE SKIN PANEL IS NOTED AS BEING BULGED OVER APPROX .6666 OF ITS LENGTH IT IS PROBABLE THAT THE LONG CRACK IS DUE TO THIS SKIN DEFECT. THE SKIN WILL BE REMOVED AND THIS SDR WILL BE UPDATED.                                                                                                                                                                                                                                                                                                                                      4  T          E20NE   6  CP7NE     
             20081120     CE  2008       11         20         CA080826007      120080826G793126060154RX      INDICATOR                               CESSNA208   208         2073702CE  PWA   PT6   PT6A114     52043NE  HARTZLHCB3T HCB3TN3     GL  OIL PRESSURE    DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            107                                                       (CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENGINE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  TNTA37CE   E4EA    6  CP15EA    
             20081120     CE  2008       11         20         CA080826008      120080825G32406119            CYLINDER                    PN9122      CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA                              MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4258                                                           (CAN) CYLINDER CASTING COMPOSED OF ALUM STEEL ANCHOR BOLTS MOUNTED IN CASTING CAUSED CORROSSION OF ALUM BOSS BORES WHICH OVER TIME CAUSED THE BOSS CASTING TO CRACK DUE TO THE (SWELLING) ACTION OF THE CORROSION NEXT TO THE STEEL PINS. DUE TO THE NORMAL DIRT CREATED BY BRAKING VISUAL INSP DIFFICULT WITHOUT REMOVAL FOR CLEANING. BOTH ANCHOR BOLT BOSSES CRACKED ON BOTH CALIPERS (4 CRACKS).                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
             20081120     SO  2008       11         20         CA080827001      120080827G521012030027001     SHIM                        1454101760  EMB   145   EMB145LR    3260212SO                                                               PAX DOOR        CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA       20785                                                          (CAN) DURING 4Y, 8Y CHECK, BOTH SHIM P/N: 120-30027-001 LOCATED BETWEEN BRACKET P/N:145-25211-601, 145-25211-602 WAS FOUND HEAVELY CORRODED. DUE TO THE EXPENSION PRODUCE BY THE CORROSION, SOME BRACKET FASTENER WAS BROKEN AND THE ATTACHED FRAME P/N: 145-25299-001 WAS DEFORMED. (TC NR 20080827001)                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T    RTT00011AT                     
             20081120     NM  2008       11         20         CA080828001      120080826G7920AE7077093       FLEX LINE                               DHAV  DHC8  DHC8202     2809007NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  NR 2 ENGINE     DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) AN ACFT EXPERIENCED AN IN-FLIGHT ENGINE INCIDENT.  THE CREW OBSERVED SUDDENLY THE OIL PRESSURE INDICATOR DROPPED TO "0" ASSOCIATED WITH THE ENG NR 2 LOW PRESS CAUTION LIGHT AND MASTER WARNING LIGHT. FLIGHT CREW SHUT DOWN THE ENGINE NR2 IAW QRH PROCEDURES, ACFT MADE A SATISFACTORY SINGLE ENGINE LANDING.  ON GROUND, MAINT PERFORMED EXTERNAL VISUAL INSP AROUND ENG AND WAS FOUND CONSIDERABLE EVIDENCE OF OIL LEAKAGE, DETAILED INSP TO ENG DISCOVERED THE HOSE ASSY FLEXIBLE RT P/N DSC391-3 WITH ABNORMAL DAMAGE IN THE JOIN ZONE (BETWEEN FLEXIBLE HOSE AND RIGID TUBE). THE RT FLEXIBLE HOSE ASSY WAS REPLACED IAW EMM AND BUILD UP MANUAL, PERFORMED RUN TEST FOR OIL LEAKS AND THE ACFT WAS RETURNED TO SERVICE.           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081120     EA  2008       11         20         CA080828002      120080818G5610NP13932112      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       10871                                                          (CAN) BEGIN QUOTE  "DISC - WINDOW SHATTERED INFLIGHT WHEN FLYING C/A - RAR FOS WINDOW"  END QUOTE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA21EA                        
             20081120     EA  2008       11         20         CA080828003      120080820G2910601R752863      HYDRAULIC LINE                          CNDAIRCL600 CL6002B19   1900309EA                                                               HYDRAULIC SYS   CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKE OFF IN ROUTE, THE MESSAGE HYD NR1 LOW PRESS CAUTION CAME ON EICAS . CREW COMPLIED WITH QRH AND RETURNED.  AFT EQUIPMENT WAS SOAKED WITH SKYDROL.  A LEAK WAS FOUND ON A RETURN LINE ON THE HYD NR1 MANIFOLD.  THE LINE AND ELBOW WERE REPLACED , ACFT BACK TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA21EA                        
             20081124     EU  2008       11         24         CA080828004      120080828G2720137312E401      FITTING                                 BAG   JETSTMJETSTM3112  1500220EU  GARRTTTPE331TPE33110UGR 29069NE                              RUDDER          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) TAPER PINS PN SP28N14 FOUND SLIGHTLY LOOSE AT SPRING END FITTING ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTBA15CAA E4WE                 
             20081120     NE  2008       11         20         CA080828005      220080827G726031070371        SPUR GEAR                                                                  GARRTTTPE331TPE33110UGR 29069NE  MCAULY4HFR344HFR34C652  NE  GEARBOX         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FRONT GEAR CASE ON ENG REMOVED FOR TORQUE RING REPLACEMENT. PITTING FOUND ON SPUR AND HELICAL GEAR ASSY.  CONSULTATION WITH ENGINE OVERHAUL FACILITY IS ON GOING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                4  T          E4WE    6  C3PNE     
             20081120     CE  2008       11         20         CA080828006      120080827G7197                WIRE                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL                  OUT OF POSITION W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      (CAN) WHEN DESCENDING THROUGH FL 180, CREW NOTICED RT ENG WOULD NOT GO BELOW 1600 FT/LBS TORQUE WITH PWR LEVER AT FLIGHT IDLE. CREW CHECKED REMAINING RT INSTRUMENTS AND CONFIRMED IT WAS NOT AN INDICATION ISSUE.  RT PROP LEVER WAS OPERATED WITH TORQUE INCREASE ON FWD MOVEMENT, NORMAL OPERATION. PWR LEVER WAS MOVED FWD TO HIGHER POWER SETTING AND  ENG RESPONDED. STILL, WHEN RETARDING PWR LEVER TO FLIGHT IDLE, TORQUE REMAINED AT 1600 FT/LBS. CREW THEN DETERMINED THAT IT WAS CONSIDERED A RUNAWAY TORQUE SITUATION, DECLARED AN EMERGENCY, THEN SHUTDOWN AND SECURED THE RT ENG. A SAFE LANDING WAS CARRIED OUT AT THE DESTINATION AIRPORT STOPPING 3/4 DOWN THE RUNWAY. EMERGENCY CREWS MET THE ACFT AND ALL PASSENGERS AND CREW1L72 4T4  T  A24CE   E4EA    6  CP15EA    
             20081120     NE  2008       11         20         CA080829001      220080827G7421REM40E          SPARK PLUG                              DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              ENGINE          DEFECTIVE       W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          ININSP/MAINT     1                      CA                                                                      (CAN) ON TROUBLESHOOTING LT MAG DROP (100 RPM), REAR SPARK PLUGS WERE REPLACED WITH NEW SPARK PLUGS OBTAINED FROM RELIABLE SOURCE WITH CERTIFICATION. ENG WAS GROUND RUN AND MAG CHECK CONDUCTED AND RPM DROP ON LT MAG WAS 150RPM. AFTER INSPECTING LT MAG AND IGNITION LEADS IT WAS DISCOVERED THAT THE NEW SPARK PLUG IN NR 7 CYL REAR WAS NOT FIRING. THE SPARK PLUG WAS REPLACED AND ENG RUN WITH SATISFACTORY RPM DROP ON LT MAG.                                                                                                                                                                                                                                                                                                         1H71 3R3  RRCA806    5E1                  
             20081120     NM  2008       11         20         CA080829002      120080805G249791252ZC7C4001   CONTACTOR                               BOEING737   737232      1384475NM  PWA   JT8   JT8D17      52049NE                              ELECTRICAL SYS  FAILED          W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       TOTAKEOFF        1                      CA                                                                      (CAN) AFTER LIFTOFF, SEVERAL FAILURES OCCURED. ANTISKID INOP, F/O PITOT INOP, NR2 EPR GUAGE INOP, NR2 AFT FUEL PUMP INOP, PINNED ASSOCIATED LIGHTS TO TRANSFER BUS PROBLEMS. LANDING BOTH 115V AND 28V AC TRANSFER BUS INOP. NR2 TRANSFER BUS CONTACTOR WAS FOUND TO HAVE A VOLTAGE DROP ACROSS THE C1 AND C2 CONTACTS. ALSO HEARD LOOSE PARTS RATTLING WITHIN THE SELF CONTAINED RELAY. RELAY WAS REPLACED. (TC NR 20080829002)                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E2EA                 
             20081120     EU  2008       11         20         CA080829003      120080829G2841SIC6734         MODULE          GE          SIC505911   AIRBUSA319  A319112     3930323EU  CFMINTCFM56 CFM565B6P   13018NE                              FUEL SYSTEM     IMPROPER PART   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DISCOVERED DURING THE SHOP`S PRELIMINARY INSP OF A FQIC UNIT, THAT THIS DASH 11 UNIT HAD INSTALLED (2) CPU MODULES (P/N SIC6734, S/N`S 545 AND 575) THAT WOULD NORMALLY BE FOUND ON A SIC5059-04 UNIT. IN OTHER WORDS, A -11 UNIT WAS RECEIVED WITH -04 CPU BOARDS, WHICH IS NOT CONSIDERED A PROPER CONFIGURATION. ACFT WAS UNDER A "N" (USA) REGISTRATION WHEN THE COMPUTER WAS FITTED TO THE ACFT.                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA28NM                        
             20081120     EA  2008       11         20         CA080829004      220080826G7314200F5002R       PUMP                                    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              FUEL SYSTEM     LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            402                                                       (CAN) THE FUEL WAS FOUND DURING REGULAR INSP LEAKING, FUEL PUMP WAS REPLACED WITH SIMILAR ONE. THE PROBLEM DIDNT AFFECT THE ENG PERFORMANCE. FUEL TRACE WAS LOCATED BETWEEN BODY STAGE OF THE PUMP. THIS IS THE FIRST PROBLEM OF LEAK WITH THIS TYPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A20SO   E14EA                
             20081126     EA  2008       11         26         CA080829005      220080829G74146350            MAGNETO                                 GROB  120   G120A       1660208EU  LYC   O540  AEIO540D4D5      EA  HARTZLHCC3Y HCC3YR      GL  ENGINE          FAILED          W      D   RETURN TO BLOCK                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CA       7    7                                                         (CAN) ACFT FLOWN ON LOCAL FLIGHT TRAINING SORTIE WITH INSTRUCTOR AND STUDENT ON BOARD. INSTRUCTOR REPORTED NO NOTICEABLE ENGINE ROUGHNESS OR PWR LOSS DURING FLIGHT.  AFTER TAXI TO PARKING POSITION, INSTRUCTOR EGRESSED A/C AND ADVISED STUDENT TO CARRY-OUT SHUTDOWN CHECKLIST. AS INSTRUCTOR WALKED CLEAR OF ACFT HE NOTICED ENGINE CUT-OUT DURING THE STUDENTS DEAD MAG TEST PRE SHUTDOWN. POST BRIEFING INTERVIEW WITH STUDENT CONFIRMED THAT ENG WOULD NOT CONTINUE TO OPERATE ON RT MAGNETO ALONE. DISCREPANCY WAS REPORTED TO MAINT AND ENTERED AS SUCH IN JOURNEY LOG. MAINT CONFIRMED DEAD MAG ON ENG RUN-UP. TIMING CHECK IN HANGAR SHOWED NO FAULTS. REMOVAL/DISASSEMBLY OF MAGNETO SHOWED EVIDENCE OF OVERHEATING/ELECTRICAL SHORT1L71 3O3  ORTA49CE   1E4     5  CP25EA    
             20081120     SO  2008       11         20         CA080829006      120080829G27204004009         TORQUE TUBE                 4004638     PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA  HARTZLHCE3Y HCE3YR2A    GL  RUDDER          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       *                                                              (CAN) DUE FOR INSP IAW SB 1105A, AWD 2003-24-07, EXTERNAL RUST FOUND.  HOLE DRILLED IN TOP OF TUBE, SEVERE CORROSION FOUND ON LOWER INTERNAL SURFACES. PART REMOVED FROM SERVICE UNSERVICEABLEV.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081120     CE  2008       11         20         CA080829007      120080828G3240420001263       VALVE                       99123682    CESSNA525   525B        2076616CE                                                               RESERVOIR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       361                                                            (CAN) DURING DAILY INSP, THE PRESSURE WAS FOUND LOW ON THE EMERGENCY GEAR/BRAKE RESERVOIR.  BOTTLE WAS REMOVED, VALVE AND FITTINGS WERE LEAK CHECKED WITH SNOOP AND CRACK WAS FOUND IN BOTTOM OF VALVE NEAR GAUGE BOSS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4F    RTA1WI                         
             20081120     CE  2008       11         20         CA080902001      120080806G27100510105364      CONTROL CABLE                           CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  AILERON         FRAYED          W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      CA       2197                                                           (CAN) DURING IMPORT INSP, THE LT AFT AILERON CABLE WAS CHAFING ON THE PHANOLIC RUB STRIP ATTACHED TO THE RIB EXTENSION AT WS 71.125 RESULTING IN SEVERE DAMAGE TO THE CABLE. CABLE REPLACED. UNFORTUNATELY THE CABLE HAD BEEN REMOVED BEFORE PICTURES WERE TAKEN OF THE WORN CABLE.  UWN1 AND 3 SIMULATE THE CABLE OVER THE CHAFE STRIP USING THE NEW CABLE, AND UWN2 SHOWS THE DAMAGED OLD CABLE.                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10    5  NP857     
             20081120     CE  2008       11         20         CA080902002      120080827G24324076            BATTERY                                 MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE33110    29053NE  HARTZLHCB4T HCB4TN5     GL                  THERMAL RUNAWAY W      H   DEACTIVATE SYST/CIRCUITS                                                                        M  OVER TEMP                                                                     ININSP/MAINT     1                      CA            11                                                        (CAN) DURING DAILY INSP OF ACFT, GPU USED. ACFT KEY TURNED (ON) TO CHARGE BATTERIES. APPROX. 2.5 HRS LATER, VENTING OF BATTERY NOTICED FROM ACFT. SMELL OF BURNING PLASTIC. GPU DISCONNECTED, KEY (OFF).  ACFT MOVED OUTSIDE. AIRPORT FIRE DEPT. REMOVED NR 1 BATTERY AND ALLOWED TO COOL. THERMAL RUNAWAY ALONG WITH GPU PRODUCING 30 VOLTS NOT 28.8 V.                                                                                                                                                                                                                                                                                                                                                                                        1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
             20081124     EU  2008       11         24         CA080902003      120080826G2750978732000       CONTROL SYSTEM                          PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  FLAP SYS        MALFUNCTIONED   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA       6586                                                           (CAN) CREW REPORTED FLAPS MOVED ONLY A FEW DEGREES UP AFTER SELECTING "0" FROM TAKEOFF POSITION "15" IN THE INITIAL CLIMB PHASE.  "FLAP" CAUTION ILLUMINATED.  ACFT RETURNED TO BASE, TROUBLESHOOTING REVEALED POWER DRIVE UNIT AT FAULT.  PDU REPLACED, FUNCTION CHECKS SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081120     CE  2008       11         20         CA080902004      120080816G32331FA1004323      BARREL                      1143800411  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  MLG ACTUATOR    CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED INSP THE LT MLG ACTUATOR (FRISBY) WAS SEEN TO BE LEAKING. THE ACTUATOR WAS REPLACED ON THE ACFT. WHILE IN REPAIR THE BARREL OF THE ATUATOR FAILED NDT FOR A CRACK IN THE THREADED AREA. THIS AREA IS NOT INCLUDED IN SB 32-3870 WHICH CALLS FOR NDT OF THE END CAP.                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20081120     SO  2008       11         20         CA080902005      120080831G321315200           HOUSING         ERAM        110P241021  EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  NLG STRUT       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1888                                                      (CAN) WHEN LANDING AT THE AIRPORT ON A TRAINING FLIGHT THE NLG PARTIALLY RETRACTED TOWARDS THE REAR OF THE ACFT. THE ACFT PITCHED RT AND FULL LT BRAKE WAS USED TO KEEP THE ACFT ON THE RUNWAY. THE ACFT MOMENTARILY LT THE RT SIDE OF THE RUNWAY AND STRUCK A RUNWAY LIGHT WITH THE RT PROPELLER. THE AFT THEN CAME TO A COMPLETE STOP ON THE RUNWAY. UPON INSP OF THE ACFT IT WAS FOUND THAT THE NLG STRUT HSG WAS BROKEN AT THE RT  TRUNNION LINK. THIS ALLOWED THE GEAR LEG TO TURN AND MOVE REARWARD UNDER THE ACFT.                                                                                                                                                                                                                       1L72 4T4  T  A21SO   E4EA    6  CP15EA    
             20081120     EU  2008       11         20         CA080902006      120080813G6123                AUTOFEATHER SYS                         AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              NR 2 ENGINE     MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA       11                                                             (CAN) THE TAKEOFF WAS ABORTED DUE TO THE NR 2 ENGINE ANALOGUE TORQUE INDICATION BEING STUCK AT 120 PERCENT. THE NR 2 ENGINE AFU WAS REPLACED AND THE ACFT RELEASED FOR SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRT        E20NE                
             20081120     NE  2008       11         20         CA080902007      220080815G7250                TURBINE                                 AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              ENGINE          DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT 10000 FEET, THE OIL PRESSURE DROPPED TO THE RED BAND ACCOMPANIED BY A LOW OIL PRESSURE WARNING. THE ENGINE WAS SHUT DOWN. POST EVENT EXAMINATION OF THE ENG SHOWED DAMAGE IN THE POWER TURBINES. THE ENGINE WILL BE REMOVED AND SENT FOR REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRT        E20NE                
             20081120     NE  2008       11         20         CA080902008      220080819G7200                ENGINE                                  CESSNA560   560XL       2076702CE  PWC   545   PW545B           NE                                              FLAMED OUT      W      D   RETURN TO BLOCK                                                                                 X  ENGINE FLAMEOUT                                                               TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE TAXIING FOR TAKEOFF, THE PILOT RETARDED THE POWER LEVER FROM MID POSITION TO IDLE AND THE ENGINE FLAMED OUT. POST EVENT TROUBLESHOOTING SHOWED THAT THE ENGINE WOULD NOT START. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00059EN             
             20081120     EU  2008       11         20         CA080902009      120080809G6123                AUTOFEATHER SYS                         AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              RT ENGINE       UNKNOWN         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         FR FLT CONT AFFECTED         PARTIAL RPM/PWR LOSS                                CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE RT ENGINE PROPELLER FEATHERED UNCOMMANDED. PILOT SHUTDOWN THE ENGINE AND RETURNED TO AIRPORT, WHERE AN UNEVENTFUL SINGLE ENGINE LANDING TOOK PLACE. THE AFU IS SUSPECT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRT        E20NE                
             20081120     NE  2008       11         20         CA080902010      220080805G7321                FUEL CONTROL                            FOKKERF27   F27MK50            EU  PWA   PWA120PW125B           NE                              LT ENGINE       UNKNOWN         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE LT ENGINE EXPERIENCED A SUDDEN TORQUE AND ITT INCREASE. THE CREW RETARDED THE POWER LEVER BUT THE TORQUE OSCILLATED BETWEEN 0 AND 60 PERCENT WITH ELEVATED ITT. THE ENGINE WAS SHUTDOWN. THE MFCU AND PUMP WERE REMOVED AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA817    E20NE                
             20081126     NE  2008       11         26         CA080902011      220080902G7414BL600646201     MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              CONTAMINATED    W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA            498                                                       (CAN) MAG WAS RECEIVED FOR 500 HR INSP. END PLAY WAS NOTICED BEFORE DISASSEMBLY (0.003", 0.0015" IS MAX ALLOWABLE). WHEN MAG WAS DISASSEMBLED A COATING OF ENGINE OIL WAS FOUND ON ALL MAG COMPONENTS. THE COIL TAB WAS NOT LEVEL AND WAS PROTRUDING ABOVE MAG HSG PARTING SURFACE. THE COIL TAB SHOULD BE LEVEL + OR - 5 DEGREES, THIS TAB WAS BENT APPROXIMATELY 10 DEGREES UP. TAB HAD CONTACTED THE METAL WASHER ON THE DISTRIBUTOR GEAR AND HAD STARTED TO WEAR THE TAB AND WASHER. THE COIL TAB WAS BENT BACK TO LEVEL, THE OIL SEAL WAS REPLACED AND THE ROTATING MAGNET BRGS WERE INSPECTED AND RESHIMMED TO MFG SPECS. THE MAG WAS THEN RETURNED TO SERVICE.                                                                           1G71 3O3  O  H11NM   1E4                  
             20081120     CE  2008       11         20         CA080903001      120080902G8011149NL           STARTER                                 CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  ENGINE          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1222                                                           (CAN) DURING FIRST START OF THE DAY THE PILOT NOTED A GRINDING NOISE WHEN THE STARTER WAS ENGAGED. THE BENDIX WAS SUSPECTED TO NOT COMPLETELY ENGAGE RING GEAR. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    1E10    5  NP857     
             20081120     SO  2008       11         20         CA080903004      120080801G7920SA00402SE       HOUSING                     SA00402SE   PIPER PA30  PA30        7103002SO  LYC   O320  IO320B1A    41508EA  HARTZLHCE2Y HCE2YL2     GL  OIL FILTER      CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA       350                                                            (CAN) RT ENGINE OIL FILTER SEPARATED FROM HSG SHORTLY AFTER TAKEOFF. ENGINE SHUTDOWN IN-FLIGHT. ACFT LANDED SAFELY. ACD REMOTE OIL FILTER HSG THREADED STUD FOUND CRACKED. ONE PORTION OF THREADED STUD REMAINED IN FILTER AND THE OTHER HALF REMAINED IN THE FILTER HSG.  RT REMOTE FILTER HSG THREADED STUD FOUND TO HAVE 0.020" WALL THICKNESS AT THE NON-THREADED PORTION.  LT ENGINE ACD REMOTE FILTER HSG INSPECTED AND THREADED STUD FOUND TO HAVE ONLY 0.017" WALL THICKNESS AT THE NON-THREADED PORTION.  SUSPECT THAT BOTH PARTS WERE INCORRECTLY MACHINED.  A REPLACEMENT PART FROM MFG HAD 0.060" WALL THICKNESS.                                                                                                                   1L72 3O3  O  A1EA    1E12    5  CP9EA     
             20081120     WP  2008       11         20         CA080903005      120080813G243514924HT         MOUNT                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STARTER MOUNT PAD CRACKED THROUGH BY FRONT MOUNTING HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081120     EA  2008       11         20         CA080903006      120080831G3230NAS16128        O-RING                                  CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              LANDING GEAR    DETERIORATED    W      D   RETURN TO BLOCK                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       5135                                                           (CAN) DEPARTING, EN ROUTE, NR3 HYDR SYS LO PRESS. LIGHT CAME (ON) AND QTY READ 2 PERCENT. ACFT RETURNED TO BASE. INVESTIGATION SHOWED A (BLOWN) SEAL ON PRIORITY VALVE IN  THE LANDING GEAR WHEEL WELL. O-RING FOUND DETERIORATED.  REPLACED O-RING, FUNCTION TESTED AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
             20081120     NM  2008       11         20         CA080903007      120080208G5320HL10878         COLLAR                                  BOEING777   777222      1385219NM                                                               FASTENER        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       40041                                                          (CAN) FOUND DURING INSP, SEVERAL  HI-LOCK COLLARS CRACKED. ALL HI-LOCK COLLARS REPLACED IAW SRM 51-40-02.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTT0001SE                      
             20081120     SW  2008       11         20         CA080903008      120080828G56102719442003      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  COCKPIT         CRACKED         W      I   CABIN DEPRESSURIZATION                                                                          O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) CAPTAINS WINDOW SHATTERED ON DECENT DURING FINAL LEG INTO BASE. SHORTLY AFTER ENTERING CLOUD WITH ICING. W/S HEAT WAS ON LOW. MAINT REPLACED THE WINDSHEILD. NO EXTERNAL DAMAGE COULD BE FOUND ON THE WINDOW WHICH MAY HAVE CAUSED THE FAILURE. THE TREND OF PREMATURE FAILURES OF THESE WINDOWS FOR THIS OPERATOR CONTINUES AS IS LIKEY CAUSED DUE TO SUBSTANDARD PARTS.                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081120         2008       11         20         CA080903009      120080903G3411                FITTING                                                                    GARRTTTFE731TFE73140    29001NE                              PITOT/STATIC SYSLEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRYING OUT AN AUTO SLAT CHECK, DURING AN A-CHECK, THE STATIC SYS WAS REQUIRED TO SIMULATE 25,000 FT AGL. AN EXCESSIVE LEAK RATE WAS NOTICED ON THE NR1 SIDE AND ISOLATED TO THE FLEX LINE AT THE NR1 ADC STATIC FITTING. UPON FINDING THE NR1 SYS PROBLEM THE NR2 SYS WAS ALSO CHECKED AND THE SAME LINE ON THE NR2 SIDE WAS ALSO FOUND DEFECTIVE.                                                                                                                                                                                                                                                                                                                                                                                       4  F          E1NM                 
             20081120     SW  2008       11         20         CA080903010      120080828G56102719442003      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  COCKPIT         CRACKED         W      I   CABIN DEPRESSURIZATION                                                                          O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) ON DESCENT AT APPROX 13000FT THE LT HEATED WINDSHIELD CRACKED. MAINT REPLACED THE WINDSHEILD AND NO PREXISTING DAMAGE WAS FOUND WHICH WOULD HAVE CONTRIBUTED TO THE WINDOW CRACKING. PREMATURE FAILURE OF THESE WINDOWS IS NOT UNCOMMON.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081120     NM  2008       11         20         CA080903011      120080903G29136617303         SHAFT                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYDRAULIC PUMP  SHEARED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT ENGINE THE NR2 HYDR PUMP CAUTION LIGHT CAME ON ACFT CONTINUE NORMAL LANDING. NR2 HYDR PRESS BEING MAINTAINED BY PTU MAINT. FOUND EDP SHAFT SHEARED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081120     EA  2008       11         20         CA080903012      120080827G2810215640014       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  LT WING         LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1744                                                           (CAN) FUEL LEAKING FROM LT WING.  FUEL CELLS REMOVED LEAK CHECKED.  FUEL CELL NR1 FAILED LEAK CHECK.  CELL REINSTALLED, SYS LEAK CHECKED FOUND SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
             20081118     EA  2008       11         18         CA080903013      120080827G2810215640024       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1744                                                           (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 3 FAILED LEAK CHECK. NEW CELL INSTALLED SYSTEM LEAK CHECKED AND FOUND SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA14EA   E20NE                
             20081118     EA  2008       11         18         CA080903014      120080827G2810K215T6400212    FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 4 FAILED LEAK CHECK. NEW CELL INSTALLED SYSTEM LEAK CHECKED AND FOUND SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA14EA   E20NE                
             20081118     WP  2008       11         18         CA080903015      120080816G2435                GEAR                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER GEN     WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       277                                                            (CAN) STARTER TEETH FOUND WORN, REPLACED WITH A SERVICEABLE STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081118         2008       11         18         CA080903016      220080903G7414                ROTOR           SLICK                                                                                                                   MAGNETO         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       135                                                            (CAN) CUSTOMER RETURNED MAG FOR WARRANTY PURPOSES. MAG ROTOR SHAFT WAS BROKEN BETWEEN THE DRIVE END BEARING AND THE MAGNET PORTION. THE BREAK STILL ALLOWED THE ROTOR TO SPIN BUT THE ROTOR STARTED TO CONTACT THE HOUSING. THE CUSTOMER CLAIMS THAT THIS IS THE SECOND MAG THEY HAVE SEEN WITH THIS TYPE OF FAILURE. THIS MAG HAD THE NAS1149CO632R WASHER INSTALLED UNDER THE DRIVE GEAR AS PER TCM SB03-7. THE HUB WAS INSPECTED AS PER SLICK SB1-07 AND NO CRACKING WAS FOUND. MAG WAS RETURNED TO MANUFACTURER FOR FURTHER INVESTIGATION.                                                                                                                                                                                                                                            
             20081118         2008       11         18         CA080904001      420080902G2562                BATTERY                                                                                                                                 ELT             LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) ELT WAS FUNCTION TESTED DURING ROUTINE SCHEDULED INSPECTION AND WOULD NOT TRANSMIT. SUBSEQUENT INSPECTION AT AVIONICS SHOP REVEALED LEAKING BATTERY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
             20081118     CE  2008       11         18         CA080904002      120080826G3060                BOOT                                    CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA  MCAULY3D36C B3D36C432   GL  PROP DEICE      SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       523                                                            (CAN) DEICE BOOT RETAINING STRAP SEPARATING FROM NR 3 BLADE, DISCOVERED DURING ANNUAL INSP. (AT ELECTRICAL LEAD AREA). NR 3 DEICE BOOT REPLACED.  MCCAULEY SL2006-5 PERFORMED ON ALL 3 BOOTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ORTA4CE    E14EA   5  CP58GL    
             20081219     WP  2008       12         19         CA080904003      120080901G6310C1883           SPRAG CLUTCH                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      DAMAGED         W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA       3773 1921                                                      (CAN) UNTIL THE OFFICIAL REPORT ARRIVES, THIS IS WHAT IS DETERMINED HAPPENED. DURING TAKEOFF THE PILOT EXPERIENCED A LOUD NOISE AND THEN ACFT YAWED SLIGHTLY.  THE ACFT LANDED WITHOUT INCIDENT.  THE CLUTCH WAS REPLACED AND ACFT RETURNED TO SERVICE.  DETAILS WILL BE BROUGHT FORWARD ONCE THE CLUTCH IS DISASSEMBLED AND A TEAR DOWN REPORT IS AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
             20081118     EU  2008       11         18         CA080904004      120080903G32109321921210      BOLT            PILATS                  PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  PIVOT PIN       BROKEN          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       322                                                            (CAN) ON TAKE OFF THE PILOTS NOTED AN AIR/GROUND LIGHT ON AND THE GEAR WAS UNABLE TO RETRACT. THE PILOTS RETURNED TO THE AIRPORT AND MX LOOKED AT THE PROBLEM. THE ACFT WAS PLACED UP ON JACKS AND UPON INSPECTION IT WAS NOTED THAT 1 OF THE WEIGHT ON WHEEL SWITCHES WAS MAKING CONTACT WITH THE TARGET. THE WOW SWITCH WHICH WAS MAKING CONTACT WAS INSPECTED CLOSER AND FOUND THAT THE PIVOT PIN HAD TWISTED. THE PIVOT PIN IS HELD IN PLACE WITH A BOLT AND THE BOLT WAS FOUND SHEARED INTO 3 PIECES. THE BOLT HEAD AND NUT WAS HELD IN PLACE BY THE SEALANT THAT PREVENTS WATER ENTERING ALONG THE BOLT. THE PIVOT PIN WAS REMOVED AND THE SHANK OF THE BOLT WAS REMOVED AND THE GEAR WAS VISUALLY INSPECTED AND FOUND SERVICEABLE. A NEW 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081118     EA  2008       11         18         CA080904006      220080904G7414                COIL            BENDIX                  PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA                              MAGNETO         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            463                                                       (CAN) MAG WAS RECEIVED FOR 500 HOUR INSPECTION. WHEN DISASSEMBLED THE COIL TAB WAS FOUND TO BE BENT DOWN AND ALMOST TOUCHING THE INSULATION COVERING THE COIL (APPROX. 10 DEGREES). THE CARBON BRUSH HAD WORN THE EXTERNAL EDGE ONLY. THIS TAB IS SUPPOSED TO BE LEVEL + OR - 5 DEGREES. THE TAB WAS BENT BACK UP DURING THE 500 HOUR INSPECTION AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA                
             20081119         2008       11         19         CA080905001      120080903G32469595601143      GROMMET         BFGOODRICH                                                                                                              MLG WHEEL       MISMARKED       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) VALVE STEM GROMMET SEAL PN TRRG30 WAS CROSS REFERENCED THEN ORDERED FROM AN ACFT MANUFACTURE SUPPLIER USING THE CROSS REFERENCE NR OF 959.56.01.143. A BAG OF 10 SEALS WERE RECEIVED AS LABELED 959.56.01.143 ON THE OUTER PACKAGING. A VISUAL CONFIRMATION AT A LATER DATE DETERMINED THAT THE PACKAGING RECEIVED FROM THE SUPPLIER ACTUALLY CONTAINED VENDOR PN TRRG6 SEALS. THE REMAINDER OF THE STOCK WAS PULLED AND THE SUPPLIER NOTIFIED. 1 SEAL HAD BEEN ISSUED TO A WHEEL REPAIR. THE WHEEL WAS PULLED FROM STOCK AND THE SEAL WAS REPLACED WITH THE CORRECT SEAL. THE TRRG6 SEAL AND THE CORRECT PN TRRG30 (959.56.01.143) SEAL WERE NOTED VERY SIMILAR IN SIZE AND APPEARANCE. THE SUPPLIER WAS NOTIFIED, AN INVESTIGATION REVEA                                          
             20081119     EA  2008       11         19         CA080905002      120080902G2497M275008SP3U00   WIRE HARNESS    HAMFLU      761339D     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              ADG             BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19543                                                          (CAN) FOLLOWING THE COMPLETION OF AD CF2008-09, WHILE PERFORMING A FUNCTION CHECK OF THE AIR DRIVEN GENERATOR, 2 OF THE 3 MAIN FEED WIRES WERE FOUND BROKEN AFT OF THE CONNECTOR P1XC.   CLOSER INSPECTION OF THE WIRES REVEALED PITTING CORROSION AND BREAK IN SEVERAL STRANDS OF THE WIRES. ALL 3 WIRES WERE REPLACED AS AN ASSEMBLY P/N M27500-8SP3U00.                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
             20081119     NE  2008       11         19         CA080905003      220080903G7530658385          CONTROLLER                              BOEING727   727260      138408KNM  PWA   JT8   JT8D17      52049NE                              BLEED SYSTEM    MALFUNCTIONED   W      O   OTHER                                                                                           EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AT FL300, TOP OF DESCENT, AS THRUST REDUCTION COMMENCED, LARGE BANG WAS EXPERIENCED BY THE FLIGHT CREW WITH FLUCTUATIONS IN NR 2 ENGINE PARAMETERS. ENGINE WAS IDLED FOR THE REMAINDER OF THE FLIGHT AND SHUT DOWN UPON LANDING.  MX PERSONNEL CARRIED OUT TROUBLESHOOTING AND THE PRESSURE RATIO BLEED CONTROLLER WAS REPLACED.  THE PRBC HAS BEEN SENT TO AN OVERHAUL FACILITY AND AWAITING COMPLETE STRIP REPORT TO VERIFY DEFECTIVE PRBC.                                                                                                                                                                                                                                                                                             2L73 4F4  FRTA3WE    E2EA                 
             20081119     SW  2008       11         19         CA080905004      120080904G2497                WIRE                                    FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR 29081NE  MCAULY4HFR344HFR34C652  NE  MASTER SWITCH   BURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) RT AVIONICS AUX MASTER SWITCH WAS SELECTED ON AND SMOKE WAS NOTICED WITHIN 5 SECONDS. SWITCH WAS SELECTED OFF AND SMOKE STOPPED. NO OTHER ABNORMALITIES WERE NOTICED EXCEPT VISUAL BLACK DISCOLORATION ON F/O PHONE JACK OF HEADSET. THIS OCCURRED ON THE GROUND IN BETWEEN FLIGHTS. MX WAS DISPATCHED AND FOUND THAT THE WIRING FROM THE AUX AVIONICS SWITCH WAS BURNT AND ALSO 1 WIRE FROM THE 50AMP CB WAS BURNT. ALL AFFECTED WIRING WAS REPLACED AND ALL SYSTEMS AFFECTED TESTED AND NO FURTHER FAULTS FOUND. SUSPECT WIRE FROM AUX SWITCH CHAFED AGAINST 50AMP CB WIRE.                                                                                                                                                             2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081119     NE  2008       11         19         CA080905005      220080824G7250                TURBINE BLADES                          CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          FRACTURED       W      BA  EMER. DESCENT           UNSCHED LANDING                                                         YA ENGINE STOPPAGE           FLAME/FIRE                                          CRCRUISE         1                      CA                                                                      (CAN) APPROX 45 MINUTES INTO THE FLIGHT PILOT REPORTED ENGINE TROUBLE AND WAS ATTEMPTING AN EMERGENCY LANDING. CONTROL OF THE ACFT WAS LOST DURING LANDING AND THERE WAS A POST CRASH FIRE. EXAMINATION OF THE ENGINE REVEALED FRACTURED COMPRESSOR TURBINE (CT) BLADES. CT BLADES ARE ORIGINAL TO ENGINE MFG. MFG HAS REQUESTED COMPRESSOR TURBINE DISK AND BLADES TO BE RETURNED FOR ANALYSIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                           1H71 3T3  T  A37CE   E4EA                 
             20081222     NE  2008       12         22         CA080905006      220080904G7323B2475           GOVERNOR                                ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       1557                                                           (CAN) PILOT WAS LANDING THE ACFT AND THE RPM DROPPED DUE TO THE GOVERNOR NOT HOLDING THE REQUIRED RPM, GOVERNOR REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
             20081119     CE  2008       11         19         CA080905007      120080904G5220                TAB                                     BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              EMERGENCY EXIT  BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1206 1206                                                      (CAN)  EMERGENCY EXIT DOOR LATCH APPEARS AS THOUGH THE LATCH TAB HAD BEEN BENT SO THAT IT COULD BE INSTALLED IN THIS MANNER. IN THIS MODE, THE LATCH CAN ALWAYS (EVEN WHEN PRESSURIZED) BE OPENED AS THE TAB PASSES OVER THE SAFETY PLUNGER. THE TAB SHOULD CONTACT THE PLUNGER WHEN PRESSURIZED AND ENTER THE SLOT FURTHER DOWN THE PLUNGER SHAFT WHEN THE PLUNGER IS PROTRUDING IN THE UNPRESSURIZED MODE.  REMOVING THE LATCH ASSEMBLY AND REPOSITIONING THE STEEL TAB TO CORRECTLY INTERFACE WITH THE PLUNGER HAS FIXED THE PROBLEM AND THE ASSEMBLY IS NOW SERVICEABLE. WE OPINED THAT THIS CONDITION LIKELY EXISTED SINCE MANUFACTURE. AN INSPECTION OF THE REMAINDER OF OUR FLEET FOR THIS CONDITION REVEALED NO OTHER FAULTS.           1L72 3T4  TRT3A20    E4EA                 
             20081119     SW  2008       11         19         CA080905008      120080902G215020475546        A/C PACK                                FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  LT              DAMAGED         W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, THE PILOT NOTICED SMOKE COMING OUT OF FRESH AIR VENTS AND MOMENTS LATER LT WING OVERHEAT LIGHT CAME ON. ACFT LANDED WITHOUT INCIDENT. MX WENT TO LOOK AND FOUND THAT THE LT COOLING TURBINE HAD A CATASTROPHIC FAILURE. THE LT BLEED SYSTEM WAS MEL`D AND DISABLED. NUMEROUS RUNS WERE COMPLETED WITH NO FURTHER SMOKE COMING INTO CABIN.                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081119     SO  2008       11         19         CA080908001      120080829G71206666200         MOUNT                                   PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7948                                                           (CAN) CRACKS WHERE TUBES ARE WELDED TO NOSE STRUT. CHAFING WHERE AERO DUCT HOSE TOUCHED MOUNT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  2A13    E274                 
             20081119     EA  2008       11         19         CA080908002      220080827G7414K3975           COIL            SLICK                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              MAGNETO         OPEN            W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       1895                                                           (CAN) PILOTS NOTED A DEAD LT MAGNETO WHEN PERFORMING PRE FLIGHT RUNUP. MAGNETO WAS REMOVED AND DISASSEMBLED AND FOUND THAT THE COIL SECONDARY WINDING WAS OPEN CIRCUIT (SHOULD BE BETWEEN 1500-20,000) - MANGETO WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10                 
             20081119     CE  2008       11         19         CA080908003      120080902G28101183810021      FLOAT VALVE                             BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                              FUEL CELL       DISLODGED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       757                                                            (CAN) ATTACH PIN MIGRATED OFF ALLOWING FLOAT TO BECOME DISLODGED FROM FLOAT VALVE PIN 118-381002-1. ATTACH PIN MIGRATED TO ORIGINAL POSITION AFTER FLOAT BECAME DISLODGED. THE FLOAT WAS LOCATED AT THE RT FUEL FILLER. THE NEW VALVE WAS DATED IN 2000 WHILE THE DEFECTIVE VALVE WAS DATED JULY, 2005. THE NEW VALVE WAS OF A DIFFERENT CONSTRUCTION IN THE ATTACH PIN AREA LESS CONDUCIVE TO ALLOWING DISLODGING OF THE FLOAT.                                                                                                                                                                                                                                                                                                                1L72 4T4  T  A24CE   E4EA                 
             20081119     NM  2008       11         19         CA080908004      120080902G27222334003001      ACTUATOR                                DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  RUDDER          BYPASSING       W      O   OTHER                                                                                           FG FLT CONT AFFECTED         MULTIPLE FAILURE                                    NRNOT REPORTED   1                      CA       4180141801                                                     (CAN) FLT CREW REPORTED RUDDER TRIM INDICATOR SHOWS 40% RT DEFLECTION TO CENTRE BALL ON HSI. MX REPLACED THE RUDDER TRIM ACTUATOR AND CHECKED SYSTEM SERVICEABLE. ON THE NEXT FLIGHT THE CREW REPORTED NO APPRECIABLE CHANGE AND THAT IT APPEARED THEY WERE CROSS CONTROLLING THE ACFT WITH THE TRIMS.  MX DISCOVERED THAT BOTH THE NR 1 AND 2 SYSTEM RUDDER ACTUATORS WERE INTERNALLY BYPASSING FLUID. MX WAS ABLE TO MOVE RUDDER BY HAND EVEN WITH FULL HYDRAULIC SYSTEM PRESSURE. BOTH RUDDER ACTUATORS PN 233400-3001, SN 0575 (NR 1), SN 0580 (NR 2), IPC 27-20-00 FIG 5, ITEM 618 WERE REPLACED AND OPS, FUNCTIONAL AND LEAK CHECKS COMPLETED. RUDDER CABLES TENSIONED. ACFT TEST FLOWN SATISFACTORILY AND RETURNED TO SERVICE. NOTE:MX TA2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081119     EU  2008       11         19         CA080908005      120080908G5753Z4243300014     SPRING                                  ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA                              FLAP SPRING     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLAP SPRING LOCK WAS DISCOVERED CRACKED DURING SCHEDULED MX. SPRING BROKE COMPLETELY DURING REMOVAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O0 A76EU   1E10                 
             20081119     SW  2008       11         19         CA080908006      120080507G6320430040003       TRANSMISSION                            BELL  430   430         1182150SW                                                               MAIN ROTOR      DAMAGED         W      BA  EMER. DESCENT           UNSCHED LANDING                                                         CJ F.O.D.                    WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) WHILE IN CRUISE FROM AN OIL RIG , THE PILOT HEARD A LOUD BANG AND THE ACFT YAWED LT AND RT AND WAS FOLLOWED BY A LOUD RUMBLING SOUND. THE COCKPIT INDICATION SHOWED THAT THE ACFT HAS A TRANSMISSION CHIP AND A CHIP SUMP CAUTION. THE PILOT DESCENDED DOWN TO APPROXIMATELY 400 FEET READY TO PREPARE FOR DITCHING. AFTER APPROXIMATELY 1 1/2 TO 2 MINUTES, THE RUMBLING STOPPED AND THE ACFT NOISE WENT BACK TO NORMAL. THE PILOT PROCEEDED TO LAND WITHOUT EVENT AND SHUT DOWN THE HELICOPTER. AFTER INSPECTION, NUMEROUS CHIPS AND FLAKES OF METAL ON THE SUMP PUMP CHIP DETECTOR, COLLECTOR GEAR DETECTOR AND THE MAGNETIC DRAIN PLUG. SOME METAL FOUND ON THE LT INPUT QUILL CHIP DETECTOR AND IN THE OIL FILTER. TRANSMISSION WILL 1G72 3U    RTH9SW                         
             20081119     SO  2008       11         19         CA080908007      220080828G853007502385AWL     RISER                                   CESSNA185   A185E       2072818CE  CONT  O520  IO520F      17032SO                              NR 5 CYLINDER   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       680                                                            (CAN) DURING 100 HOUR INSPECTION AME FOUND RT EXHAUST STACK CRACKED AT NR 5 CYLINDER, PART WAS REPLACED WITH PART NR 0750161-31.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  3A24    E5CE                 
             20081119     EA  2008       11         19         CA080908008      220080906G8530AEL85099        CYLINDER                                CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  NR 1            SEPARATED       W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA       2577 2577                                                      (CAN) ACFT WAS CLIMBING OUT ON A TRAINING FLIGHT. SHORTLY AFTER HEARD A LOUD BANG AND RPM DROPPED TO APPROX 1200. TURNED BACK AND LANDED SAFELY FOUND THE NR1 CYL HEAD SEPARATED FROM THE BARREL WITH APPROX 1 INCH OF BARREL EXPOSED PAST THE CYLINDER FINS. NR1 INTAKE LIFTER WAS DAMAGED AS WELL AS THE ENG CRANKCASE, ENG REMOVED FOR OVERHAUL. ENG WAS OPERATING ON AN ON-CONDITION PROGRAM. (@2567 HOURS, TBO IS 2000) FIRST FAILURE OF THIS TYPE. CYL WAS NOT AFFECTED BY AD 2006-12-07 AND WAS IN FACT NOTED AS AN ACCEPTABLE REPLACEMENT CYLINDER FOR THE PN MENTIONED IN THE AD. ENGINE WAS INSTALLED IN THIS AIRFRAME. REPLACED ORIGINAL ENGINE.                                                                                     1H71 3O3  ONT3A12    E274    5  NP910     
             20081124     CE  2008       11         24         CA080908009      120080908G551112326212        SPAR                                    CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO                              HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND THAT THE RT AND LT REAR SPAR WAS HEAVILY CORRODED (LEVEL 3) AND CRACKED UNDER THE OTBD HINGE BRACKET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  A4CE    E5CE                 
             20081124     CE  2008       11         24         CA080908010      120080808G5312071111229       BULKHEAD                                CESSNA185   A185F       2072821CE  CONT  O550  IO550D      17042SO                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING NON-ROUTINE MX REPAIRS AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER RT CORNER AT REAR FLOAT FITTING. CUSTOMER WAS NOTIFIED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A24    E3SO                 
             20081124     CE  2008       11         24         CA080909001      120080907G2435                COOLING FAN     TRW                     BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA                              STARTER GEN     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1581 662                                                       (CAN) WHILE PERFORMING AN INSPECTION, THE ENGINEER PULLED THE STARTER-GENERATOR AND NOTICED THE COOLING FAN BROKEN. UPON FURTHER INVESTIGATION, THE ENGINEER NOTICED THAT 1 OF THE BROKEN FAN BLADES WAS PROVIDING A GROUND PATH INTERNALLY BETWEEN THE GENERATOR AND THE CASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  T  A14CE   E4EA                 
             20081124         2008       11         24         CA080909003      220080909G7414M3611           CAM             SLICK                                                                                                                   MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO, CUSTOMER HAS YET TO INFORM US AS TO HOURS ON UNIT. THE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE CONTACT POINTS WAS FOUND TO BE EXCESSIVELY WORN. THIS IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS RETURNED TO UNISON/SLICK FOR INSPECTION.                                                                                                                                                                                                                                                                                                                                                                           
             20081124         2008       11         24         CA080909004      220080909G7414M3611           CAM             SLICK                                                                                                                   LOBES           WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) (2ND MAG) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO. CUSTOMER HAS YET TO INFORM US AS TO HOURS ON UNIT. THE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE POINTS WAS FOUND TO BE EXCESSIVELY WORN. THIS IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS RETURNED TO UNISON/SLICK FOR INSPECTION.                                                                                                                                                                                                                                                                                                                                                                         
             20081124     EA  2008       11         24         CA080909005      120080819G27501104SD1201      SHAFT                                   CNDAIRCL600 CL6002B19   1900309EA                                                               TE FLAPS        BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       20680                                                          (CAN) AFTER LANDING AND ON RETRACTION OF THE FLAPS, THE CREW RECEIVED A FLAP FAIL CAUTION MSG.  PIREP: FLAP FAIL CAUTION. WHEN FLAP SELECTOR MOVED FROM 45 DEG TO 8 DEG, FLAPS STOPPED AT THE 22 DEG POSITION.  MX EXAMINED THE FLAPS AT THE GATE AND DETERMINED THAT THERE WAS EVIDENCE OF OIL CANNING ON THE TOP SURFACE SKIN OF THE RT INBD FLAP. THE ACFT WAS TAKEN OUT OF SERVICE AND PROCESSED TO THE HANGAR FOR FURTHER INVESTIGATION.  LOCATED A BROKEN FLEX SHAFT TIP AT THE INBD SIDE OF THE OTBD ACTUATOR FOR THE INBD FLAP. ALL DAMAGED PARTS INCLUDING THE FLAP SURFACE WERE REPLACED.                                                                                                                                             2L72 4F    RTA21EA                        
             20081124     CE  2008       11         24         CA080910001      120080903G7160155212914       INTAKE DUCT                             CESSNA337   337F        2075725CE  CONT  O360  IO360C      17025SO  MCAULY2AF34CD2AF34C306  GL                  CRACKED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              APAPPROACH       1                      CA       2712                                                           (CAN) DURING A ROUTINE PATROL FLIGHT THE PILOT EXPERIENCED A VIBRATION IN THE AREA OF THE REAR ENGINE. HE ELECTED TO RETURN TO THE AIRPORT AND MADE AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPON INSPECTION BY THE MX CREW, IT WAS DISCOVERED THAT THE FWD EDGE OF THE INNER & OUTER SECTIONS OF THE AIR COOLING DUCT HAD PARTIALLY SEPARATED FROM THE NOSE CAP. THIS ALLOWED ROM AIR TO FLOW BETWEEN THE INNER & OUTER SECTIONS AND CAUSED THE INNER DUCT TO VIBRATE AND SUBSEQUENTLY CRACK & BREAK.                                                                                                                                                                                                                                          1H72 3O3  O  A6CE    E1CE    5  CP5EA     
             20081124     WP  2008       11         24         CA080910002      120080818G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       345                                                            (CAN) THE STARTER WAS NOT CRANKING OVER ENGINE, STARTER REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
             20081124     SO  2008       11         24         CA080910003      220080715G8520                COTTER PIN      CONT                                                       CONT  O200  O200A       17020SO                              CONNECTING ROD  MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NO COTTER PINS IN ANY OF THE 8 CON-ROD BOLTS DISCOVERED UPON DISMANTLE FOR PROPELLER STRIKE INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          3  O          E252                 
             20081119     NE  2008       11         19         CA080910004      220080909G7530                SWITCH                                  EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              NR 2            FAULTY          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING THE DEPARTURE, THE FLIGHT HAD A NR2 BLEED VALVE FAILURE INDICATION WHICH WAS RESET. AND THEN FAILED AGAIN, FOLLOWED WITHIN 2 MINUTES WITH A BLEED NR1 FAILURE. QRH PROCEEDURES WERE FOLLOWED AND THE FLIGHT RETURNED TO LAND. THE FLIGHT WAS NOT OVERWEIGHT FOR LANDING AND THERE WAS NO EMERGENCY DECLARED.   BLEED NR1 FAULT CODE HAS BEEN TROUBLESHOT. BLEED O/P SWITCH NR2 REPLACED IAW AMM. TORQUE MOTOR LINES TO VALVE CHECKED OK.                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA57NM   E00070EN             
             20081119     SW  2008       11         19         CA080910005      120080709G6510407340340103    DISC PACK                               BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              T/R DRIVESHAFT  CRACKED         W      O   OTHER                                                                                           Z  SIGNIFICANT FAILURE REPORT                                                    ININSP/MAINT     1                      CA                                                                      (CAN) FOUND (3) DISCS CRACKED AND ALL DISCS CORRODED ON THE FWD NR 1 POSITION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  UO H2SW    E1GL                 
             20081119     NE  2008       11         19         CA080910006      220080820G7314C8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       993                                                            (CAN) FUEL PUMP ELECTRICALLY MALFUNCTIONING, REPLACED FUEL PUMP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081126     SO  2008       11         26         CA080911001      120080908G812089682002        SHROUD                                  PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540AE2A  41532EA                              AIR PUMP        LOOSE           W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       2626                                                           (CAN) THE LWR AIRPUMP COOLING SHROUD ASSY, ALTHOUGH NOT LOOSE TO THE TOUCH, WAS ABLE TO ROTATE WITH A LIGHT TO MODERATE PUSH.   THIS ROTATION ALLOWED THE AIR INLET DUCT AND CLAMP TO CONTACT THE LINKAGE ON THE TURBO CONTROLLER. THE SHROUD ROTATION OCCURRED DURING FULL POWER, THIS TRAPPED THE LINKAGE ON THE TURBO CONTROLLER IN THE CLIMB POWER POSITION.  THE LOWER AIRPUMP COOLING SHROUD ASSEMBLY(P/N 89682-002), ROD(P/N 89682-008), HOSE (P/N 89684-002), AND CLAMP(P/N 5544-896) WERE REPLACED WITH NEW. THE NEW SHROUD AND CLAMP WERE POSITIONED TO PROVIDE MAXIMUM CLEARANCE TO THE TURBO CONTROLLER. THE NEW SHROUD AND ROD FIT IS MORE SECURE TO PREVENT FURTHER ROTATION.  AN ENGINE GROUND RUN WAS CARRIED OUT SATISFACTORILY1L71 3O3  ORTA25SO   E14EA                
             20081119     EA  2008       11         19         CA080911002      120080909G5610601R330339      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            Z  SIGNIFICANT FAILURE REPORT                                                    DEDESCENT        1                      CA       1823818238                                                     (CAN) ON DESCENT THE LT WINDSHIELD CRACKED AT FL370 AND THE LT WINDSCREEN HEAT CAUTION CAME ON. AN EMERGENCY WAS DECLARED, BUT THE A/C LANDED WITHOUT INCIDENT. THIS WINDSHIELD HAD OVER 18,000 HRS AND WAS WELL ABOVE THE AVERAGE FOR NORMAL FAILURE RATES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
             20081119     NM  2008       11         19         CA080911003      120080905G27821U1110          ACTUATOR                                BOEING727   727225      1384077NM  PWA   JT8   JT8D9A      52048NE                              KRUEGER FLAP    FAILED          W      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THROUGH APPROX 2,000 FT NR1 ENGINE LOW HYDR PRESSURE LIGHT ILLUMINATED, SYS `A` HYDRAULIC OIL AND PRESSURE LOSS. ACFT RETURNED TO DEPARTURE. NR5 KRUGER FLAP ACTUATOR FOUND FAILED AND ATTACH BRACKET DAMAGED. REPLACED ACTUATOR AND TESTED IAW AMM 29-11-00 AND 27-81-22. KRUEGER FLAP ATTACH BRACKET REPAIRED IAW SRM 51-10-2. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                   2L73 4F4  F  A3WE    E2EA                 
             20081119     EU  2008       11         19         CA080911004      120080908G32205322012165      BARREL NUT      PILATS      532001203   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NLG             CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) NLG OLEO WAS STICKING AND NOT EXTENDING WHEN GEAR UP WAS SELECTED. WITH THE TIRE FALLING SHORT OF THE BACK OF THE WHEEL WELL IT MAKE CONTACT WITH THE NOSE GEAR DOOR RODS. BOTH LT AND RT RODS BUSTED OFF LEAVING THE DOORS FLOATING. THE NOSE WHEEL BEING SHORT CONTACTED AND RUBBED THE GEAR UP BUMPER AND LIGHTLY TOUCHED THE RT GEARDOOR LEAVING A BLACK RUBBER MARK. UPON INSP, IT WAS FOUND THAT THE BARREL NUT STARTED TO CORRODE INTERNALLY UNDER THE PHENOLIC BUSHING FORCING THE PHENOLIC BUSHING AGAINST THE OLEO. BARREL NUT AND SEALS REPLACED.                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081126     NM  2008       11         26         CA080911005      120080911G7920443330          O-RING                                  BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              GEARBOX OIL     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) WHILE CLIMBING OUT, NOTICED ENG NR 1 OIL QUANTITY INDICATOR SLOWLY DECREASING, QUANTITY  WAS 1 GALLON AT TOP OF CLIMB. AT MID POINT, QUANTITY DECREASED TOWARD ZERO. ENGINE SHUTDOWN DRILL AND CHECK LIST COMPLETED.  ENGINE  WINDMILLING SUPPLEMENT COMPLETED PRIOR TO DESCENT.  ALL OTHER ENGINE INDICATIONS NORMAL PRIOR TO SHUTDOWN.  OPENED COWLING ON NR 1 ENG, CHECKED FOR OIL LEAK, NOTHING OBVIOUS, ADDED 12 QUARTS OF OIL IAW MM  12-13-001-2.  NR 1 ENG RUN AT IDLE TO LEAK CHECK,  SIGNIFICANT OIL LEAK FROM GEARBOX TO OIL  COOLER TUBE. FOUND OIL LINE HAD TENSION ON IT WHEN REMOVING TUBE. SEAL SPLIT AND REAR PIECE MISSING.  PROCURED SEAL P/N 443330 (REV.A).  CPN 0043234 INSTALLED SEAL AND REPOSITIONED TUBE, REMOVE2L73 4F4  F  A3WE    E2EA                 
             20081119     NE  2008       11         19         CA080911006      220080904G7200JT8D9A          ENGINE                                  BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              NR 2            FAILED          W      AE  UNSCHED LANDING         ENGINE SHUTDOWN                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       544691313                                                      (CAN) AFTER T/O AND CLIMB OUT, NR2 ENGINE LOST OIL QTY AND OIL TEMP ROSE RAPIDLY INTO RED INDICATION. INFLIGHT SHUTDOWN COMPLIED WITH AND ACFT RETURNED TO DEPARTURE. NR2 ENGINE REPLACED IAW AMM AND KFL TASK CARDS, ACFT RETURNED TO SERVICE. ENGINE TO BE EVALUATED IN ENGINE SHOP FOR CAUSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                2L73 4F4  F  A3WE    E2EA                 
             20081119     NE  2008       11         19         CA080912001      220080825G7321                ECU                                                                        PWA   PW121 PW121       52124NE                              NR 1 ENGINE     MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 JX WARNING INDICATION        ENGINE FLAMEOUT                                     CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE PILOT NOTICED FLUCTUATION OF NR1 ENGINE PARAMETERS. WHILE ATTEMPTING TO ADJUST PROPELLER SPEED, ENGINE FLAMED OUT. AN ATTEMPT TO RESTART ENGINE IN-FLIGHT WAS NOT SUCCESSFUL. DURING GROUND INSP, ALL ENGINE PARAMETERS FLUCTUATED WITH ECU "ON" AND ALL PARAMETERS STABLIZED WITH ECU "OFF". THE ECU WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                           4  T          E20NE                
             20081119     NE  2008       11         19         CA080912002      220080826G7320                HMU                                     BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              LT ENGINE       MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA                                                                      (CAN) ACFT EXPERIENCED LOSS OF POWER TO FLIGHT IDLE (FI) ON LT ENGINE DURING FLIGHT WHICH LEAD TO A COMMANDED ENGINE IN-FLIGHT SHUTDOWN + RESTART WITH INABILITY TO GO ABOVE FI. FLIGHT WAS DIVERTED WHERE THE A/C LANDED WITH THE LT ENGINE AT FI POWER. EXTENSIVE TROUBLESHOOTING LED TO HMU REPLACEMENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                2H72 4F4  FRTA16SW   E25EA                
             20081119     EA  2008       11         19         CA080912003      220080902G8530SL11625         PLUG                                    CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  ENGINE          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1300                                                           (CAN) THE PISTON PIN PLUGS IN TWO CYLINDERS ON THE ENGINE WORE UNUSUALLY AND CAUSED ALUMINUM METAL CONTAMINATION THROUGHOUT THE ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081119     CE  2008       11         19         CA080912004      120080912G57533516505030      HINGE BRACKET                           BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  TE FLAP         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE REPLACEMENT OF THE REAR SPAR LT BRACKET, THE LT OTBD FLAP WAS REMOVED FOR ACCESS AND FOUND THE INBD HINGE OTBD BRACKET WITH DAMAGE CAUSED BY THE ROLLER BEARING FLANGE APROX 0.025 DEEP.  DECIDED TO PERFORM DVI OF ALL REMAINING FLAP ROLLER ASSY AND REMOVE THE RT OTBD FLAP. FOUND THE SAME DAMAGE ON THE RT OTBD FLAP INBD HINGE OTBD BRACKET. INVESTIGATION SHOWED THAT THE BEARINGS AND FLAPS WERE INSTALLED CORRECTLY. BRACKETS ARE BEING REPLACED.                                                                                                                                                                                                                                                                     2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20081120     CE  2008       11         20         CA080912005      120080911G249710936102247     WIRE                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  LT NACELLE      BURNED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) LT ENGINE FAILED TO ROTATE ON START UP. MAINT DISCOVERED LT STARTER GEN WIRE FEED THRU ASSY (CONSISTS OF 3 PARALLEL HEAVY GUAGE WIRES) TERMINAL ENDS BURNED OFF AT START CONTROL PANEL TERMINAL. NEW WIRE FEED THRU ASSY ON ORDER. START CONTROL PANEL ON ORDER. WILL CARRY OUT A FLEET WIDE INSP OF LT AND RT NACELLES FOR WIRE FEED THRU TERMINAL ENDS FOR CONDITION.                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20081120     SW  2008       11         20         CA080912006      120080908G7920991930811       TUBE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  OIL SYSTEM      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE PREFLIGHT WALKAROUND, THE FLIGHT CREW NOTICED OIL DRIPPING FROM THE RT ENGINE. MX WAS DISPATCHED TO THE LOCATION WHERE THE STAINLESS STEEL TUBE ASSY FROM THE ENGINE PROP GOVERNOR TO THE NEGATIVE TORQUE SENSING (NTS)MANIFOLD WAS FOUND LEAKING. DURING REMOVAL, 1 FLARED END OF THE TUBE WAS FOUND CRACKED 3/4 OF THE WAY AROUND THE CIRCUMFERENCE OF THE TUBE. TOSL TIME ON THE TUBE COULD NOT BE DETERMINED. THIS SAME PN TUBE HAS BEEN FOUND CRACKED PREVIOUSLY ON OTHER ACFT. THE CRACK WAS LIKELY DUE TO IMPROPER ALIGNMENT OF THE TUBE ASSY DURING INSTALLATION ON THE PROP GOVERNOR.                                                                                                                                 2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081120         2008       11         20         CA080912007      120080817G5210                ATTACH FITTING  BRAERO      1371008C409                                    GARRTTTPE331TPE33110UGR 29069NE                              PAX DOOR        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SEVERE CORROSION NOTED AT MAIN CABIN DOOR ATTACH FITTINGS. CORROSION ALSO NOTED UNDER SEVERAL DOOR SEAL CLIPS. DOOR DEEMED BEYOND ECOMONICAL REPAIR AND REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  T          E4WE                 
             20081120         2008       11         20         CA080912008      120080912G5210                FITTING         BRAERO      1371008C409                                    GARRTTTPE331TPE33110UGR 29069NE                              PAX DOOR        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS DOOR WAS INSTALLED AS A REPLACEMENT DUE TO SEVERE CORROSION FOUND ON ORIGINAL DOOR. REPLACEMENT DOOR INSPECTED AND CORROSION DISCOVERED UNDER SEVERAL DOOR INFLATION SEAL CLIPS. CLIPS REMOVED AND CORROSION REMOVED AND SURFACES TREATED. CLIPS REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                               4  T          E4WE                 
             20081126     GL  2008       11         26         CA080915006      120080826G3260                WARNING LIGHT                           BOMBDRBD700 BD7001A10   1390006GL  HNYWL AS907 AS90711A    33908WP                              MLG             ILLUMINATED     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) DURING FLT, "GEAR SYS FAIL" CAUTION MESSAGE POSTED.  CREW VERIFIED ACTIVE FAULTS IN CAIMS TO FIND LGECU CHANNEL B FAILED. CREW PROCEEDED TO PREPARE FOR LANDING FOLLOWING ACFT FLT MANUAL PROCEDURE FOR GEAR SYS FAIL MESSAGE. MANUAL LANDING GEAR EXTENSION PROCEDURE WAS CARRIED OUT IAW AFM.  ON APPROACH, ACFT DESCENDED TO AN ALTITUDE OF 500 FEET WHEN ENHANCED GROUND PROXIMITY WARNING SYSTEM "TOO LOW GEAR" UN-MUTABLE AURAL WARNING SOUNDED, WHICH PROMPTED PILOT TO GO AROUND AND VERIFY THE REASON FOR THIS WARNING. AFTER VERIFICATION CREW MADE A SECOND ATTEMPT ON APPROACH AND THE "TOO LOW GEAR" AURAL WARNING SOUNDED AGAIN DISREGARDED BY CREW TO FINALIZE LANDING.  ON TOUCH DOWN, THE PILOT NOTICED THAT THE LT ENGIN2L72 4F4  FRTT00003NYE00010LA             
             20081120     WP  2008       11         20         CA080915007      120080816G2822D7431           PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     FAULTY          W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA       267                                                            (CAN) THE AUX FUEL PUMP LIGHT WOULD NOT EXTINGUISH, AUX PUMP REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  H11NM   1E4                  
             20081120     EU  2008       11         20         CA080916001      120080911G323372MEF20151      SWIVEL FITTING                          SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F25 NE  RT MLG          SHEARED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKE-OFF, DURING GEAR RETRACTION, THE RT MLG DOWNLOCK ACTUATOR SWIVEL FITTING LOCATED ON THE DRAG BRAC, FAILED. THIS CAUSED A SUBSTANTIAL LOSS OF FLUID.  AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT AND THE ACFT RETURNED TO BASE WITH NO FURTHER PROBLEMS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20081120     CE  2008       11         20         CA080916002      120080806G2752                ROLL PIN        CESSNA      C1450046RX  CESSNA208   208         2073702CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  TE FLAP         SHEARED         W      O   OTHER                                                                                           FP FLT CONT AFFECTED         NO WARNING INDICATION                               ININSP/MAINT     1                      CA       2998                                                           (CAN) DURING ROUTINE INSPECTION, STANDBY FLAP SYSTEM OPS DISCOVERED INOPERATIVE (MOTOR TURNING - NO FLAP MOVEMENT). UPON FURTHER INVESTIGATION, ROLL PIN SECURING STANDBY DRIVE TO WARM GEAR WAS FOUND TO BE SHEARED RENDERING STAND BY FLAP OPS U/S. SUSPECT FAILURE WAS DUE TO AGE OF PART. RECOMMEND TESTING OF STAND BY FLAP SYSTEM PER A/C MAN. N.M. AT EACH INSPECTION. IN THIS INSTANCE PRIMARY FLAP OPS WERE NOT AFFECTED.                                                                                                                                                                                                                                                                                                              1H71 3T3  TNTA37CE   E4EA    5  CP60GL    
             20081120     EU  2008       11         20         CA080916004      120080915G4940                CONTROL BOX                             AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73131C   01518NE                              COCKPIT         DEFECTIVE       W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       12101                                                          (CAN) PILOTS HAVE BEEN REPORTING INTERMITTENT SULPHUR SMELL IN THE ACFT. WHILE TROUBLESHOOTING, THE MECHANIC NOTICED THAT THE APU DOOR WAS OPEN AND APU MASTER AS OFF. WHEN THE APU SWITCH WAS CYCLED TO CLOSE THE DOOR, SPARKS STARTED TO APPEAR NEXT TO START SWITCH IN THE COCKPIT. UPON REMOVAL OF THE CONTROL BOX, IT WAS NOTICED THAT THE RUBBER SLEEVE AROUND THE START SWITCH WAS MELTED AND THERE WERE SIGNS OF BURNING ON THE WIRES COMING OUT OF THE SWITCH.                                                                                                                                                                                                                                                                         2L73 4F4  F  A46EU   E6WE                 
             20081126         2008       11         26         CA080916005      420080830G3457GNS530430W      GPS                                                                                                                                                     MALFUNCTIONED   W      O   OTHER                                                                                           GH MULTIPLE FAILURE          ELECT. POWER LOSS-50 PC                             CRCRUISE         1                      CA                                                                      (CAN) GNS530W AND GNS430W SIMULTANEOUSLY LOOSE SATELLITE RECEPTION. SATELLITES ARE REAQUIRED BETWEEN 2 AND 20 MINUTES LATER. EXTENSIVE TROUBLESHOOTING FOUND NO FAULT WITH THE INSTALLATION. MFG PRODUCT SUPPORT INDICATED THAT SIMILAR REPORTS HAVE BEEN RECEIVED FROM OPERTORS IN ALASKA AND THE ANOMOLY APPEARS AT AROUND THE LATITUDE OF FAIRBANKS. THERE IS A PROBLEM WITH THE GNS SOFTWARE AND THE ALASKA WAAS GROUND STATION. THE WAAS ENGINE IN THE GNS NAVIGATOR MUST BE SHUT OFF IN THAT AUXILLARY MENU SETUP PAGE TO PREVENT SATELLITE LOSS IN NORTHERN LATTITUDES. THIS INFORMATION IS NOT READILLY AVAILABLE TO OPERATORS AND OWNERS.                                                                                                                                        
             20081222     CE  2008       12         22         CA080916006      120080912G555104320049        ATTACH BRACKET                          CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  SNSNCH72C   72CK        EA  VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CARRIED OUT SEB 03-6 ON VERTICAL TAIL ATTACH BRKT AND STAB SPAR. SPAR WAS NOT CRACKED BUT THE STEEL ATTACH BRKT WAS CRACKED AROUND A RIVET HOLE FOR THE PREVIOUSLY INSTALLED NUT PLATES. AD PREVIOUSLY ALLOWED REMOVAL OF NUT PLATES.  THIS OPERATOR HAS SEEN AT LEAST TWO OTHER FAILURES OF THIS PART. A/C TT IS ~22,950 HOURS OPERATING IN AN FTU.  REPLACED PART WITH A USED, INSPECTED SERVICEABLE PART DUE TO NO PARTS SUPPORT FROM MFG.   NOTE: NO PICTURE, NOT ABLE TO TAKE A PICTURE FROM THE INSIDE OF THE BRACKET.                                                                                                                                                                                                              1H71 3O3  ONT3A19    E223    5  NP9045    
             20081120     CE  2008       11         20         CA080916007      120080728G2436C6110040101     VOLT REGULATOR                          CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO                              ELECTRICAL SYS  SHORTED         W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) ACFT WAS IN CRUISE FLIGHT WHEN THE PILOT NOTICED THE ELECTRICAL SYSTEM WAS DRAINING THE BATTERY. THE ACFT LANDED AND WSA INVESTIGATED BY MX. IT WAS FOUND THAT THE BATTERY WAS DISCHARGED AND THE ELECTROLYTE HAD BOILED FROM THE BATTERY. FURTHER INVESTIGATION REVEALED THE VOLTAGE REGULATOR WAS AT FAULT, ALLOWING THE ALTERNATOR TO OVERVOLT THE BATTERY AND DESTROY IT. THE BATTERY COMPARTMENT WAS CLEANED AND A NEW BATTERY WAS INSTALLED, A NEW VOLTAGE REGULATOR WAS INSTALLED AND A NEW ALTERNATOR WAS ALSO INSTALLED AS A PRECAUTIONARY MEASURE. THE ACFT WAS GROUND RUN & ELECTRICAL SYSTEM CHECKED SERVICEABLE.                                                                                                             1H71 3O3  O  A4CE    E5CE                 
             20081120         2008       11         20         CA080916008      120080913G3040                MOTOR                                                                      GARRTTTPE331TPE3312201A      WP                              WINDSHIELD      MALFUNCTIONED   W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) SKYVAN EN ROUTE WITH 2 CREW ,1 PASSENGER ON BOARD ADVISED ARCTIC RADIO THEY HAD SMOKE IN COCKPIT, CREW REQUESTED EMERGENCY VEHICLES, ACFT LANDED SAFELY, CREW AND PASSENGER WERE CHECKED AT LOCAL NURSING STATION AND RELEASED. FURTHER INVESTIGATING PROBLEM, IT WAS FOUND THAT THE WINDSHIELD WIPER MOTOR HAD BURNT OUT. WIPER MOTOR WAS REPLACED WITH A SERVICEABLE UNIT , FUNCTION CHECKED AND RELEASED BACK TO SERVICE. TOTAL TIME ON WIPER MOTOR UNKNOWN.                                                                                                                                                                                                                                                                                  4  T          E3WE                 
             20081120         2008       11         20         CA080917001      120080826G28203014884         TUBE                                                                       PWA   PT6T  PT6T3B      52045NE                              FUEL SYSTEM     CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       3219                                                           (CAN) FUEL FOUND LEAKING ONTO ENGINE DECK FROM AT BRAZE ON BOTTOM "B" NUT FITTING ON TUBE. TUBE LOCATED ON FORWARD FACE OF ENGINE ACCESSORY GEARBOX. ACFT WAS GROUNDED UNTIL PART WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        4  U          E22EA                
             20081120     EA  2008       11         20         CA080917002      120080911G32138A04000021      SUPPORT                     8000FLOATS  DHAV  DHC3  DHC3        2800202EA  PWA   PT6   PT6A34      52043EA                              MLG AXLE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEEL ASSEMBLIES AND BRAKES REMOVED FOR INSPECTION AND REBUILD. IT WAS DISCOVERED THAT THE AXLE SUPPORT BODIES ON BOTH MAIN GEAR ASSEMBLIES HAD CRACKS AND REQUIRED REPLACEMENT. THIS WAS FOUND ON A 200 HR. INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3R4  T  A815    E4EA                 
             20081126     NM  2008       11         26         CA080917003      120080916G21333964401         SHUTOFF VALVE                           BOEING727   727247      138408FNM  PWA   JT8   JT8D15A     52051NE                              A/C PACK        FAILED          W      JA  DUMP FUEL               UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMBOUT, SEPT 16 2008, PRESSURIZATION FAILED TO OPERATE NORMALLY. WHEN CLIMBING THROUGH 23,000 FT, CABIN ALTITUDE EXCEEDED 10000 FT. FUEL DUMP CARRIED OUT IN ORDER FOR ACFT TO RETURN TO DEPARTURE.  CABIN PRESSURIZATION LEAK CHECK CARRIED OUT, NO FAULTS. PRESSURIZATION CONTROLLER AND PRESSURIZATION CONTROL PANEL REPLACED. GROUND PRESSURIZATION CHECKS CARRIED OUT WITH NO FAULTS DETECTED. ON SEPT 17, 2008, ACFT WAS DEPARTED. AS THE ACFT CLIMBED THROUGH 25000 FT, CABIN PRESSURIZATION FAILED TO OPERATE NORMALLY WITH MINIMAL CONTROL. ACFT RETURNED TO DEPARTURE FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING REVEALED NO PROBLEMS WITH THE PRESSURIZATION SYS BUT HAS REVEALED THAT THE RT PACK FLOW CONTROL AND 2L73 4F4  F  A3WE    E2EA                 
             20081120     CE  2008       11         20         CA080917004      120080907G2750C3010010211     COUPLING                                CESSNA208   208         2073702CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  TE FLAP         FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      CA                                                                      (CAN) FLAP COUPLING FAILED DURING NORMAL LANDING PROCEDURES. UPON FAILING, THE PART BROKE INTO 2 PIECES, DISCONNECTING THE FLAP MOTOR FROM THE ACTUATOR ASSEMBLY. THIS RESULTED IN THE FLAPS STOPPING WHILE PARTIALLY EXTENDED. THE FLAPS WERE LEFT PARTIALLY EXTENDED FOR LANDING. THE CREW ELECTED NOT TO USE THE STANDBY FLAP MOTOR TO AVOID THE POTENTIAL FOR FURTHER DAMAGE TO THE FLAP ACTUATOR ASSEMBLY.                                                                                                                                                                                                                                                                                                                                 1H71 3T3  TNTA37CE   E4EA    5  CP60GL    
             20081124     NE  2008       11         24         CA080917005      220080910G720090623           ENGINE                                  BOEING777   777*        UTILUSENM  GE    GE90  GE90115B    30048NE                              NR 1            VIBRATION       W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA       889                                                            (CAN) IN CRUISE, THE FLIGHT EXPERIENCED A NR 1 ENGINE VIBRATION.  THE ENGINE CONTINUED OPERATING NORMALLY BUT WITH VIBRATION.  THE FLIGHT DIVERTED TO FAIRBANKS, ALASKA.  AN ENGINE HAS BEEN SCHEDULED AND TOOLS, PARTS AND MANPOWER ARE CURRENTLY BEING SHIPPED TO ALASKA. ACFT IS OUT OF SERVICE.  \ETQ INVESTIGATION NR 2917 INITIATED.                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTT00001SEE00049EN             
             20081120         2008       11         20         CA080917006      420080902G6122                GOVERNOR                                CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              PROPELLER       OUT OF ADJUST   W      EC  ENGINE SHUTDOWN         ABORTED TAKEOFF                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING TAXI ROLL IN PREPARATION FOR TAKE-OFF, THE COMPRESSOR TURBINE SPEED (NG) DROPPED BY APPROX 2%. PILOT ADVANCED POWER LEVER AND ITT ROSE TO 740 DEG C WITH NO INCREASE IN NG. THE LOW OIL PRESSURE ANNUNCIATED AND PILOT OBSERVED ZERO OIL PRESSURE. THE PROPELLER FEATHERED UNCOMMANDED AND THE PILOT SHUT THE ENGINE DOWN. THE PROP GOVERNOR WAS ADJUSTED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                        1H71 3T3  T  A37CE   E4EA                 
             20081120     EA  2008       11         20         CA080917007      220080823G7200                ENGINE                                  DHAV  DHC8  DHC8*              NM  PWC   150   PW150A           EA                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB PASSING THRU FL15, THE LOW OIL PRESSURE WARNING WAS ACTIVATED AND THE COCKPIT INDICATION WAS SEEN FALLING.  THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE.  NO TROUBLESHOOTING WAS DONE BY THE OPERATOR AND THE ENGINE WAS REPLACED. THIS WAS THE 2ND EVENT IN 7 DAYS.  THE FIRST EVENT LED TO THE REPLACEMENT OF THE OIL PUMPS.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN             
             20081120     CE  2008       11         20         CA080917008      120080808G5312071111210       BULKHEAD                                CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN LOWER LT AND RT CORNER AT REAR FRONT ATTACH, WHICH HAD BEEN PREVIOUSLY REPAIRED AND HAS CRACKED AGAIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  3A24    E5CE                 
             20081120     NE  2008       11         20         CA080917009      220080904G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              SHUTDOWN        W      D   RETURN TO BLOCK                                                                                 RX PARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT                                     TXTAXI/GRND HDL  1                      CA                                                                      (CAN) PILOT REPORTED THAT DURING TAXI THE ENGINE EXPERIENCED UNCOMMANDED ROLL BACK AND SHUTDOWN.  TROUBLESHOOTING INDICATED THAT THE ENGINE MAY HAVE ALSO EXPERIENCED AN OVERTEMP CONDITION AND WAS REMOVED FROM SERVICE FOR INSPECTION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA10CE   E35NE                
             20081120     CE  2008       11         20         CA080917010      120080808G5312071111229       BULKHEAD                                CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT CORNER AT REAR FLOAT FITTING.  CUSTOMER WAS NOTIFIED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A24    E5CE                 
             20081120     CE  2008       11         20         CA080917011      120080808G5312071111229       BULKHEAD                                CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A NON-ROUTINE INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT AND RT CORNERS AT REAR FLOAT FITTINGS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  3A24    E5CE                 
             20081120     NE  2008       11         20         CA080917012      220080907G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              MALFUNCTIONED   W      BA  EMER. DESCENT           UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) DURING A 5 MIN. RE-POSITIONING FLIGHT, THE ENGINE LOST POWER AND AN EMERGENCY LANDING WAS ATTEMPTED.  THE ENGINE WILL BE RETURNED TO P&WC FOR INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3T3  T  A37CE   E4EA                 
             20081120     NE  2008       11         20         CA080917013      220080908G7200                ENGINE                                  BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE                              RIGHT           MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 KJBFLUID LOSS                WARNING INDICATION        SMOKE/FUMES/ODORS/SPARKS  CRCRUISE         1                      CA                                                                      (CAN) A YAW OF THE ACFT CAUGHT THE ATTENTION OF THE PILOT AND A QUICK REVIEW OF THE COCKPIT GAGES REVEALED THAT THE RT ENGINE TORQUE WAS FLUCTUATING BETWEEN APPROXIMATELY 20% TO 40% WITH THE TEMPERATURE INDICATION RISING TO APPROXIMATELY 820 DEGREES.  THE PILOT VISUALLY CONFIRMED THAT LARGE AND SMALL SPARKS WERE EMANATING FROM THE ENGINE EXHAUST.  THE PILOT PROCEEDED TO SHUT THE ENGINE DOWN BEFORE MAKING AN UNEVENTFUL SINGLE ENGINE LANDING.  GROUND INSPECTION FOUND FUEL LEAKING FROM THE COWLING. THE ENGINE WILL BE REMOVED.                                                                                                                                                                                                2L72 4T4  TRTA24CE   E4EA                 
             20081120     NE  2008       11         20         CA080917014      220080901G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              DEFECTIVE       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, THE ENGINE LOST OIL PRESSURE.  AN AIR TURNBACK WAS INITIATED AND THE ACFT LANDED AT THE POINT OF DEPARTURE WITH THE ENGINE RUNNING.  POST FLIGHT INSPECTION FOUND OIL LEAKING AROUND THE ENGINE INTAKE AREA.  THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR.  P&WC WILL CLOSELY MONITOR THE INVESTIGATION RESULTS AND ISSUE UPDATES TO TC.                                                                                                                                                                                                                                                                                                                                                         1H71 3T3  T  A37CE   E4EA                 
             20081120     NE  2008       11         20         CA080917015      220080905G7250                TURBINE BLADES                          AEROSPATR42 ATR42*      8680900EU  PWA   PW121 PW121       52124NE                              ENGINE          DISTRESSED      W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE PILOT OBSERVED AN ENGINE OIL PRESSURE DROP TO THE RED ZONE.  HE ELECTED TO SHUTDOWN AND SECURE THE ENGINE BEFORE MAKING A SINGLE ENGINE LANDING AT DESTINATION.  GROUND INSPECTION FOUND LOW PRESSURE TURBINE BLADE DISTRESS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA53EU   E20NE                
             20081120     NE  2008       11         20         CA080917016      220080908G7200                ENGINE                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING A RE-POSITIONING FLIGHT, THE PILOT NOTED LOW AND FLUCTUATING OIL PRESSURE.  THE ENGINE WAS SHUT DOWN AND SECURED AND A SINGLE ENGINE LANDING WAS PERFORMED.  GROUND INSPECTION FOUND CONTAMINATION IN THE OIL FILTER AND FILTER BOWL.  THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                               2H72 4F4  FRTA16SW   E25EA                
             20081126     SW  2008       11         26         CA080917017      120080911G2597                CONNECTOR       ARTEX                   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              ELT             MISINSTALLED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSTALLATION OF NEW 406 ELT ON INSTALLATION OF CONNECTOR FOR REMOTE SWITCH THE ELT WAS SET OFF. THE ELT WAS NOT FULLY INSTALLED SO THE ELT ACTIVATION WAS NOT NOTICED. HAVE SINCE SPOKE WITH THE MFG AND FOUND THAT THIS IS A COMMON PROBLEM WITH THE INSTALLATION OF THE CONNECTOR NOT BEING INSERTED EXACTLY STRAIGHT, CAUSING THE PINS TO GROUND AND ACTIVATE ELT. POSSIBLE PROBLEM EVERY TIME YOU INSTALL OR REMOVE THIS ELT. THERE IS NO OFF SWITCH TO PREVENT THIS REOCCURRENCE JUST POSSIBILITY OF MONITORING 121.5 FOR ACCIDENTAL ACTIVATION AND RESET OF ELT IF IT GOES OFF.                                                                                                                                                     1G71 3U3  U  H2SW    E4CE                 
             20081124         2008       11         24         CA080917018      420080911G8300                GEARBOX                                                                    PWC   PW610 PW610FA     52267NE                              ENGINE          DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE, THE PILOT NOTICED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUT THE ENGINE DOWN.  WHILE DESCENDING THE CREW DECIDED TO RESTART THE ENGINE AND COMPLETE THE FLIGHT WITH THE LOW OIL PRESSURE INDICATION.  ON THE GROUND, THE PILOT COULD NOT RESTART THE ENGINE.  INITIAL TROUBLESHOOTING MAY HAVE INDICATED DAMAGE TO THE ACCESSORY GEARBOX AND THE ENGINE HAS BEEN REPLACED.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                         4  F          E00074EN             
             20081120     NE  2008       11         20         CA080917019      220080913G7220                INLET GUIDE VANE                        AMD   FALC50FALCON2000  2730170NM  PWC   PW308 PW308C      52182NE                              NR 1 ENGINE     MALFUNCTIONED   W      K   NONE                                                                                            YJ ENGINE STOPPAGE           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) IT IS REPORTED THAT 10 MINUTES BEFORE LANDING, ENGINE NR 1 SHUTDOWN BY ITSELF FOLLOWED BY A "NO DISPATCH" MSG ON THE COCKPIT DISPLAY.  TROUBLESHOOTING SHOWED THAT THE IGV POSITION DID NOT MATCH THE REQUESTED VALUE.  THE VIGV WAS REPLACED AND THE FAULT CLEARED.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA50NM   E00065EN             
             20081120     EU  2008       11         20         CA080918002      120080912G5753S5751202320     A/C PACK        SNIAS       S57512007004AEROSPATR72 ATR72212    8680945EU                                                               TE FLAP         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING C-CHECK INSPECTION (1C, 2C, 4C, CPCP2, A8), WHILE PERFORMING A DVI INSPECTION ON THE L INBD FLAP, THE INSPECTION REVEALED THAT THE FWD PICK-UP FITTING INBD LOG AT RIB 5 WAS BROKEN IN HALF. THE FITTING LOT NR IS P4110. THE BROKEN OFF PIECE WAS FOUND IN THE FLAP FAIRINGS.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T    RTA53EU                        
             20081120     CE  2008       11         20         CA080918003      120080917G243400317           ALTERNATOR                              CESSNA337   337G        2075730CE  CONT  O360  IO360G      17025SO  MCAULY2AF34CD2AF34C306  GL  FWD ENGINE      DAMAGED         W      K   NONE                                                                                            J  WARNING INDICATION                                                            CRCRUISE         1                      CA            577                                                       (CAN) THE ACFT, A CESSNA 337G WAS ON A RETURN FLIGHT TO MAIN BASE WHEN THE PILOT NOTICED A INDICATION OF A FAILED FRONT ENGINE ALTERNATOR.  THE ACFT LANDED WITHOUT INCIDENT AND MX INVESTIGATED THE PROBLEM.  DURING REMOVAL OF THE FRONT ALTERNATOR, IT WAS DISCOVERED THAT THE DRIVE SHAFT HAD BEEN SHEARED OFF.  THE DRIVE GEAR IN THE ENGINE WAS INSPECTED AND FOUND SERVICEABLE. A SERVICEABLE ALTERNATOR WAS INSTALLED AND THE ACFT RELEASED FOR SERVICE.  THE U/S ALTERNATOR HAD A TOTAL OF 577 HRS SINCE O/H.  WE HAVE HAD REPORTS OF SIMILAR PROBLEMS WITH THESE ALTERNATORS IN THE PAST.                                                                                                                                             1H72 3O3  O  A6CE    E1CE    5  CP5EA     
             20081125     SW  2008       11         25         CA080918004      120080914G2913                HOUSING         VICKERS                 SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              HYDRAULIC PUMP  SEPARATED       W      D   RETURN TO BLOCK                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA            3                                                         (CAN) DURING ENGINE START THE NR 2 ENGINE HYDRAULIC PUMP BEGAN TO LEAK SIGNIFICANTLY CAUSING A LOSS OF SYSTEM PRESSURE AND FLUID.  UPON INSPECTION BY MX THE PUMP WHICH WAS JUST INSTALLED 2.5 HRS PRIOR WAS FOUND TO HAVE SEPARATED AT THE PUMP HOUSING HALVES AND THE O RING SEAL WAS EXTRUDED. THE INTERNAL WRENCHING BOLTS WHICH HOLD THE HALVES TOGETHER APPEARED TO HAVE PULLED OUT OF THE THREADS ALLOWING THE PUMP HALVES TO SEPARATE TO THE POINT OF PUMP FAILURE.  THE COMPANY WILL SEND THE PUMP FOR WARRANTY REPAIR.                                                                                                                                                                                                                2L72 4T4  TRTA8SW    E4WE                 
             20081125     SW  2008       11         25         CA080918005      120080914G76032543161         SPRING                                  BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              THROTTLE RETURN BROKEN          W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA            101                                                       (CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED.  THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX.  WHEN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H2SW    E4CE                 
             20081125     CE  2008       11         25         CA080918006      120080909G273112601491        ACTUATOR                                CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO                              ELEVATOR TRIM   CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION A AME FOUND HEAVY CORROSION (LEVEL 3) ON THE ACTUATOR.  HE R&R THE PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A4CE    E5CE                 
             20081126         2008       11         26         CA080919001      420080917G2562                MOUNT BRACKET                           PIPER PA28  PA28180     7102808SO  LYC   O360  O360A4A     41514EA                              ELT             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE EXISTING ELT MOUNTING BRACKET WAS INSPECTED PRIOR TO REPLACEMENT OF THE VHF ELT WITH A 406 MHZ ELT.  UPON REMOVING THE NARCO ELT10 MOUNTING TRAY, IT WAS DISCOVERED THAT ACFT ELT MOUNTING BRACKET WAS CRACKED AT EACH MOUNTING TRAY SCREW HOLE LOCATION.  THE NARCO ELT TRAY WAS FOUND TO BE MOUNTED TO THE BRACKET USING ACCEPTABLE AN SCREWS AND SELF-CAPTIVE NUTS.  THERE WERE NO WASHERS USED BETWEEN THE SELF-CAPTIVE NUTS AND THE BOTTOM SIDE OF THE ACFT MOUNTING BRACKET.  AS PART OF THE 406MHZ ELT UPGRADE AND MODIFICATION REPORT, THE OLD BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND INSTALLED.                                                                                                               1L71 3O3  O  2A13    E286                 
             20081125     WP  2008       11         25         CA080919002      120080916G2421ALX8521RS       ALTERNATOR                              ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                                              DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            128                                                       (CAN) ALTERNATOR HAS STRIPPED HOUSING                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   E295                 
             20081125     WP  2008       11         25         CA080919003      120080910G6310C0512           ACTUATOR                                ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CLUTCH          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       712                                                            (CAN) CLUTCH ACTUATOR FOUND U/S DURING INSPECTION, SERVICEABLE ACTUATOR INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
             20081126     EA  2008       11         26         CA080919004      220080916G7261                NUT                         766859C     BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  OIL PUMP        LOOSE           W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT NR 2 ENGINE INDICATED LOW OIL PRESSURE.  ENGINE WAS SHUTDOWN AND UNEVENFUL LANDING WAS CARRIED OUT.   MX BORESCOPE INSP FOUND THE OIL PUMP DRIVE SHAFT NUT BECAME LOOSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081125     WP  2008       11         25         CA080919005      120080908G6310C0183           CLUTCH                                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1920                                                      (CAN) LOUD BANGING NOISE IN ACFT.  CLUTCH REMOVED FOR TEARDOWN INSPECTION, SERVICEABLE CLUTCH INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
             20081125     WP  2008       11         25         CA080919006      120080826G6310C0512           CLUTCH ACTUATOR                         ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1747                                                      (CAN) DRIVE BELTS SLIPPING, SERVICEABLE ACTUATOR INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081126     EU  2008       11         26         CA080919007      120080917G2110139312          SUPERCHARGER                            BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  CABIN PRESSURE  INOPERATIVE     W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       3982                                                           (CAN) WHILE IN CRUISE FLIGHT, ENROUTE, CREW NOTICED A STRANGE ODOR COMING FROM THE CABIN.  CREWMAN ONBOARD WENT TO LOOK IN THE CABIN AND NOTICED TEMPERATURE IN THE CABIN WAS VERY HOT AND THERE WAS LIGHT HAZE OR SMOKE IN SAFELY.  MX INSPECTED THE ACFT AND FOUND THAT BOTH CABIN SUPERCHARGER INTAKE FILTERS WERE NEARLY COMPLETELY CLOGGED.  FURTHER INSP REVEALED SOME SCORING ON THE INSIDE WALLS AND ROTORS OF THE CABIN SUPERCHARGERS.  INLET FILTERS WERE CLEANED AND BOTH LT AND RT CABIN SUPERCHARGERS REPLACED.  GROUND RUNS AND FLIGHT TEST WERE COMPLETED, THE ACFT WAS FOUND SERVICEABLE AND RELEASED FOR SERVICE.                                                                                                              2L72 3T4  T  A24EU   A196    6  CP899     
             20081125     CE  2008       11         25         CA080919008      120080825G8011149NL           STARTER                                 CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                                              FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       98                                                             (CAN) STARTER FAILS TO ENGAGE, SERVICEABLE STARTER INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    1E10                 
             20081125         2008       11         25         CA080919009      220080918G7414                ROTOR                                                                                                                                   MAGNETO         BROKEN          W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA                                                                      (CAN) CUSTOMER COMPLAINED ABOUT DEAD MAG.  TIME IN SERVICE IS UNKNOWN. MAG WAS OPENED AND INSPECTED.  THE ROTOR GEAR VANE SHOWED INDICATIONS OF RUBBING ON THE HALL EFFECT SENSOR AND HAD CONTACTED THE SENSOR.  THIS STOPPED THE ROTOR GEAR WHICH IS INSTALLED IN THE SLOT AND BROKE THE ROTOR SHAFT AT THE BASE OF THE SLOT.  THIS INFORMATION IS BEING SENT TO SLICK FOR EXAMINATION.                                                                                                                                                                                                                                                                                                                                                                                                  
             20081125     EA  2008       11         25         CA080919010      220080908G741410600646201     MAGNETO                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       331                                                            (CAN) REMOVED DUE TO ERRATIC ENGINE RPM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   E295                 
             20081126     NE  2008       11         26         CA080919011      220080918G7414                BEARING                     BL6006163   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         EXCESS PLAY     W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA            458                                                       (CAN) MAG WAS RECEIVED FOR 500 HR INSP.  BEFORE MAG WAS DISASSEMBLED THE BEARINGS WERE CHECKED BY SPINNING THE ROTATING MAGNET.  THE END PLAY WAS MEASURED AT 0.004", MFG LIMIT IS 0.0015" MAX.  THE BEARINGS WERE RESHIMMED, THE REST OF THE 500 HR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081201     CE  2008       12         1          CA080921001      120080919G3220AN17621A        BOLT                                    CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ROUTINE MX AND ENGINE CHANGE, NLG WAS REMOVED FOR ACCESS TO REPLACE LOOSE RIVETS IN ENG NACELLE AREA.  INSP OF NLG ATTACH BOLTS SHOWED SIGNS OF CRACKS JUST UNDER THE HEAD OF THE BOLT.  LPI INSP OF THE BOLT SHANKS CONFIRMED CRACKS.  BOLTS WERE BOTH REPLACED.  AFTT 12484.6 HOURS, A REVIEW OF ACFT HISTORY FOUND NO RECORD OF THESE BOLTS HAVING BEEN REPLACED.  A REVIEW OF THE MFG SERIES CAP, CONTINUED AIRWORTHINESS PROGRAM, SHOWED NO INITIAL INSP OR REPLACEMENT REQUIREMENTS.                                                                                                                                                                                                                                         1H71 3O3  O  A4CE    E5CE    5  CP36EA    
             20081201     NM  2008       12         1          CA080922001      120080917G3244DR0231T         TIRE                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 3            FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       255                                                            (CAN) PASSENGER REPORTED NR 3 TIRE BURST DURING TAKE OFF.  CREW EXTENDED GEAR AND FA CONFIRMED TIRE WAS BLOWN.  ACFT RETURNED TO BASE FOR LANDING. OPERATOR REPORTED TIRE WAS ON SECOND RETREAD WITH 238 CYCLES 255 HOURS. AXLE WAS NOT DAMAGED AND IS NOT BEING REPLACED.  THE RUNWAY WAS SWEPT AFTER THE INCIDENT AND NO DEBRIS OTHER THAN BITS OF TIRE WERE FOUND.  INSPECTION COMPLETED AND TIRE REPLACED,                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081201     EA  2008       12         1          CA080922002      220080822G7414                IMPULSE COUPLING                        CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  MAGNETO         MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA  CGGPE                                                               (CAN) ENGINE WAS OVERHAULED AND STORED UNTIL AUGUST 2008.  DURING INSTALLATION ON AUG. 22, 2008, IT WAS NOTICED THAT THERE WAS NOT :CLICKING: OF THE MAGNETO IMPULSE COUPLINGS AS THE PROPELLER WAS ROTATED A NR OF TIMES. BOTH MAGNETO (UNISON 4381`S, S/N 07031616 AND 07031617) WERE REMOVED FROM THE ENG AND INSPECTED, THE PAWLS ON THE IMPULSE COUPLINGS ON BOTH MAGNETOS WOULD NOT ENGAGE PROPERLY OR AT ALL.  IT APPEARED THAT THE IMPULSE COUPLINGS HAD BEEN ASSEMBLED INCORRECTLY.                                                                                                                                                                                                                                                    1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081125     NE  2008       11         25         CA080922003      220080915G7313301114521       ADAPTER                                 CESSNA208   208         2073702CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  REAR FUEL NOZZLECRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            400                                                       (CAN) DURING LEAK TEST AFTER CLEANING LEAKAGE NOTED AT THE HEAD FUEL NOZZLE ADAPTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3T3  TNTA37CE   E4EA    5  CP60GL    
             20081128     SW  2008       11         28         CA080922005      120080909G29102781032273      LINE                                    FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  HYDRAULIC SYS   CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) PILOT REPORTED HYD FLUID LEAKING IN LT WW.   SMALL PINHOLE WAS FOUND IN LINE.  LINE REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081128     EA  2008       11         28         CA080922006      120080915G215078279015        ACM                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              LEFT            ODOR            W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA       1324413244                                                     (CAN) ON FINAL APPROACH, SMOKE SMELL IN FLIGHT DECK.  AT THE SAME TIME UNABLE TO CONTROL LT PACK IN AUTO OR MANUAL MODE.  ALSO DISPLAY FAN OR AIR IN FAN MAKING GRINDING NOISE.  BOTH FANS PLACED IN FLT ALTN MODE AND SMOKE STOPPED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20081128     EA  2008       11         28         CA080923002      120080922G56106003303021      WINDOW                                  CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       4341                                                           (CAN) WHILE IN CRUISE, CREW EXPERIENCED THE FAILURE OF THE COCKPIT LT SIDE WINDOW OUTER MAIN PLY.  A CRACK SPANNED FROM THE LOWER FWD FRAME, TO THE FWD SECTION OF THE UPPER FRAME OF THE WINDSHIELD.  THE ACFT HAD DEPARTED AND WAS ENROUTE SOUTHBOUND WHEN THE FAILURE OCCURRED.                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20081128     EU  2008       11         28         CA080923003      120080912G539752802800        WIRE                                    BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              CARGO HOOK      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ACFT OVERHAULED, CAME BACK TO BASE LAST WEEK OF AUGUST, NO SLING LOAD OPERATION HAS BEEN LOGGED.  ELECTRICAL WIRE FOUND BROKEN AT HOOK CONNECTOR LOCATION.  ELECTRICAL WIRE ATTACHED WITH CLAMPS (4X) ALONG THE SWING CABLE SUPPORT.  THE ROUTING SEEMED TO BE TOO TIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 3U3  U  H3EU    E4CE                 
             20081125     SW  2008       11         25         CA080923004      120080922G7933                OIL SYSTEM                              BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              ENGINE          OVERTEMP        W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE OIL TEMPERATURE INCREASED TO 100 DEG. C.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
             20081128     NE  2008       11         28         CA080923006      220080806G72503022312         TURBINE WHEEL                           BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              ENGINE          DISINTEGRATED   W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA       10566                                                          (CAN) WHILE HOVERING DURING TAKEOFF, NR1 PWR SECTION LOST POWER (PILOT REPORTED HEARING LOUD BANG).  ACFT PUT DOWN WITHOUT FURTHER INCIDENT, NR2 POWER SECTION SHUTDOWN.  POWER SECTION REPLACED.  ACFT RETURNED TO SERVICE.  PRELIMINARY INSP REVEALED FAILURE OF THE PT DISK.  PARTIAL BLADE SEPARATION AND FOD TO EXHAUST DUCT.                                                                                                                                                                                                                                                                                                                                                                                                              1G71 4U4  U  H4SW    E22EA                
             20081128     NM  2008       11         28         CA080924001      120080920G3240900005831PR     BRAKE ASSY                              EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              NR 3            FAILED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA            2416                                                      (CAN) 100 M FROM STOPPING AT THE GATE, THE RT BRAKE STARTED TO GRAB.  BRAKE TEMPS ALL NORMAL RANGE.  AFTER SHUTDOWN, INSPECTED RT MAIN BRAKE ASSY AND APPEARS THAT BRAKE PAN AND ASSY CAME APART.  NR3 MLG WHEEL AND BRAKE ASSY REMOVED.  LG AND ACFT INSPECTED, NO ADDITIONAL DEFECTS NOTED.  NEW BRAKE AND WHEEL ASSYS INSTALLED AND TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA56NM   E00063EN             
             20081125     SW  2008       11         25         CA080924002      120080924G5302205001731101    SUPPORT                                 BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                              TAIL ROTOR SERVOCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2322                                                           (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 4U4  U  H4SW    E22EA                
             20081125     SW  2008       11         25         CA080924003      120080924G5302205001731101    SUPPORT                                 BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                              TAIL ROTOR SERVOCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2322                                                           (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 4U4  U  H4SW    E22EA                
             20081125     SW  2008       11         25         CA080924004      120080924G5302205001731001    SUPPORT                                 BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                              TAIL ROTOR SERVOCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2322                                                           (CAN) TAIL ROTOR SERVO SUPPORT FOUND CRACKED NEAR UPPER ATTACHMENT FLANGES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 4U4  U  H4SW    E22EA                
             20081128     SW  2008       11         28         CA080924005      120080918G561036004314SS      WINDSHIELD                              GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       1118                                                           (CAN) ACFT WAS ON A MEDEVAC FLIGHT AT NIGHT AT CRUISE ALTITUDE OF 16000 FT WHEN THE FLIGHT CREW HEARD A NOISE LIKE A SLAP.  THEY COULD SEE THEN THAT THE RT WINDSHIELD WAS CRACKED.  ACFT RETURNED WITHOUT FURTHER INCIDENT. INSP FOUND THE WINDSHIELD OUTER PANEL HAD SHATTERED.  WINDSHIELD IS BEING RETURNED FOR INSP AND WARRANTY CONSIDERATION.  WINDSHIELD REMOVED FROM ACFT AND STRUCTURE INSPECTED.  NO DEFECTS FOUND.                                                                                                                                                                                                                                                                                                                  1H72 3T4  T  2A4     E4WE    6  CP8EU     
             20081128         2008       11         28         CA080924007      120080924G2820                LINE                                                                       GARRTTTFE731TFE73140    29001NE                              FUEL SYSTEM     CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSP IN THE RT WW THE MAIN FUEL LINE TO THE RT ENGINE WAS FOUND TO BE CHAFING ON THE LAV SINK HEATED DRAIN LINE. THE DAMAGE WAS BEYOND LIMITS AND THE FUEL LINE WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  F          E1NM                 
             20081128         2008       11         28         CA080924008      120080924G282025W653120634    LINE                                                                       GARRTTTFE731TFE73140    29001NE                              FUEL SYSTEM     CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) IT WAS REPORTED THAT FUEL WAS SLOWLY TRANSFERRING FROM THE RT WING INTO THE CENTER TANK WHEN THE ACFT WAS STATIC.  THE MOTIVE FLOW LINE PN 25W653120-634 AT THE CENTRAL TANK LOWER TRANSFER JET PUMP WAS FOUND TO BE CHAFING ON THE FUEL QTY PROBE MOUNTING BRACKET.  THE LINE WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                     4  F          E1NM                 
             20081128     EA  2008       11         28         CA080924009      120080924G3210C6UM11104       ATTACH FITTING                          DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE 12 MONTH INSP OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081128     NE  2008       11         28         CA080924011      220080922G7200                TORQUE SHAFT                            AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              NR 1 ENGINE     CRACKED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE TORQUE WAS LOST ON NR 1 ENGINE, SUBSEQUENTLY THE ENGINE WAS SHUTDOWN BY THE CREW.  POST FLIGHT INSPECTION REVEALED A CRACKED TORQUE SHAFT AT THE WELD JOINT.  ENGINE IS BEING REMOVED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRT        E20NE                
             20081128     NE  2008       11         28         CA080924012      220080815G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              LEFT            FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  HOHOVERING       1                      CA                                                                      (CAN) ACFT WAS IN HOVER AND WAS TRANSITIONING TO FWD FLIGHT WHEN THE LT ENGINE ROLLED BACK IN POWER AND SHUTDOWN.  PILOT LANDED THE ACFT SUCCESSFULLY ON 1 ENGINE.  LT ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 4U4  U  H4SW    E22EA                
             20081128     NE  2008       11         28         CA080924013      220080922G7200                ENGINE                                  DORNERDO32  DO328100    2996000NM  PWA   119   PW119B           NE                                              FLUCTUATES      W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AT ABOUT 50 METERS FROM THE ARRIVAL GATE, THE ENG PARAMETERS STARTED FLUCTUATING.  PILOT SHUTDOWN THE ENG.  NO REPORTED DAMAGE. TROUBLESHOOTING IN PROGRESS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA45NM   E20NE                
             20081128     NM  2008       11         28         CA080925001      120080914G561080260008        WINDOW                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       371                                                            (CAN) RT WINDSHIELD CRACKED DURING CRUISE.  REDUCED SPEED TO 180 KTS AND DESCENDED TO FL100 AND LANDED AT DESTINATION.   MX REPLACED WINDSHIELD.  ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081128     CE  2008       11         28         CA080925002      120080924G5511053200198       SPAR                                    CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              HORIZONTAL STAB CRACKED         W      A   UNSCHED LANDING                                                                                 CA F.O.D.                    FLAME/FIRE                                          NRNOT REPORTED   1                      CA       9629                                                           (CAN) DURING THE 100 HRS/ANNUAL INSP, IT WAS DISCOVERED THAT THE HORIZONTAL STABILIZER FRONT SPAR ASSY (PN 0532001-98) AND THE RE-INFORCEMENT SPAR (PN 0531037-1) HAVE CRACKS AT 2 PLACES, ABOUT .5 INCH IN LENGTH, RADIATING FROM THE CENTER LIGHTENING HOLE BETWEEN BOLT ATTACHMENT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274                 
             20081128     EA  2008       11         28         CA080925003      220080919G7414BL600646201     MAGNETO                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          FAILED          W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               DEDESCENT        1                      CA       151                                                            (CAN) PILOT SNAGGED THERE WAS A HIGH ENGINE RPM RISE.  MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   E295                 
             20081128     EA  2008       11         28         CA080925004      220080919G7414BL600646201     MAGNETO                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          FAILED          W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               APAPPROACH       1                      CA                                                                      (CAN) PILOT REPORTED THERE WAS A HIGH ENGINE RPM RISE.  MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.  THIS IS DUPLICATED ON REPORT 20080925003.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   E295                 
             20081201     NE  2008       12         1          CA080925006      220080908G7200                ENGINE                                  SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              NR 2            MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN)  WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENGINE N1 LOW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENGINE LOW OIL PRESSURE LIGHT. A SCAN OF THE ENGINE GAUGES REVEALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. THE FLIGHT CREW IDENTIFIED THE PROBLEM AS AN ENG ROLL BACK AND ONCE THE LOAD WAS SAFELY JETTISONED, A SHUTDOWN OF THE NR 2 ENGINE WAS CARRIED OUT. THE ACFT THEN RETURNED TO ITS SERVICE LANDING AND MADE AN SINGLE ENGINE LANDING.  A POST FLIGHT INSPECTION OF THE T5 RECORDING SYS REVEALED THE ENGINE TEMP HAD REACHED 798 DEGREES C. THE ENGINE, FREE TURBINE ASSY AND FCU WERE REPLACED AND AFTER A COMPLETE GROUND CHECK TH2G72 4U4  U  H4EA    E15EA                
             20081202     NE  2008       12         2          CA080925007      220080908G7321                FUEL CONTROL                            SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                                              FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RMJPARTIAL RPM/PWR LOSS      OVER TEMP                 WARNING INDICATION        NRNOT REPORTED   1                      CA                                                                      (CAN) LIGHT  A SCAN OF THE ENG GAUGES REVEALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP.  FLIGHT CREW IDENTIFIED THE PROBLEM AS AN ENG ROLL BACK AND ONCE THE LOAD WAS SAFELY JETTISONED A SHUTDOWN OF THE NR (2) ENGINE WAS CARRIED OUT. THE ACFT THEN RETURNED TO IT`S SERVICE LANDING AND MADE AN SINGLE ENGINE LANDING.  A POST FLIGHT INSP OF THE T5 RECORDING SYS REVEALED THE ENGINE TEMP HAD REACHED 798 DEGREES C. THE ENG, FREE TURBINE ASSY AND FCU WERE REPLACED AND AFTER A COMPLETE GROUND CHECK ACFT WAS RETURNED TO SERVICE.  THE ENG, FREE TURBINE AND FCU WERE RETURNED TO MFG FOR AN OVER TEMP INSP AND EVALUATION AS TO A POSSIBLE CAUSE OF THE ROLL BACK.                                                    2G72 4U4  U  H4EA    E15EA                
             20081128     SW  2008       11         28         CA080925009      120080804G243523032027        STARTER GEN                             BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE.  STARTER WAS REPLACED AND NO ISSUES WERE NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E4CE                 
             20081128     WP  2008       11         28         CA080925012      120080924G6310C1883           SPRAG CLUTCH                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1781                                                           (CAN) CLUTCH WAS REMOVED FROM ACFT FOR VISUAL INSP DUE TO ISSUES WITH CLUTCH ASSY`S.  TEARDOWN REVEALED THE FOLLOWING: CAGE CRACKED AT 1 CROSSBAR, SHAFT C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL WAS VERY BLACK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081202     GL  2008       12         2          CA080925013      120080918G2421ALU8521LS       ALTERNATOR                              DIAMONDA40  DA40        2990002GL                                                                               INTERMITTENT    W      A   UNSCHED LANDING                                                                                 HJ ELECT. POWER LOSS-50 PC   WARNING INDICATION                                  CLCLIMB          1                      CA       6                                                              (CAN) INSUFFICIENT CLEARANCE BETWEEN THE HEAD OF THE FIELD TERMINAL STUD AND HSG.  BRUSH HOLDER ASSY WHEN FLEXED INWARD, CAUSES THE HSG AND HEAD OF THE STUD TO TOUCH.  IF YOU REMOVED THE BRUSH HOLDER ASSY YOU WILL NOTICE THAT THE RING TERMINAL THAT IS CRIMPED TO THE BRUSH LEAD IS SLIGHTLY LARGER THAN THE HEAD OF THE TERMINAL BOLT.  IT IS ACTUALLY THE RING TERMINAL THAT TOUCHES THE HSG.  THIS TRIPS THE VOLTAGE REGULATOR OFF LINE.  THE ALTERNATOR SWITCH NEEDS TO BE CYCLED TO RESET THE REGULATOR.                                                                                                                                                                                                                              1L71 3O    NTA47CE                        
             20081128     WP  2008       11         28         CA080925014      120080923G6310C1883           SPRAG CLUTCH                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      CHIPPED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       596                                                            (CAN) PILOT HEARD POSSIBLE NOISE WITH SLIPPAGE OF DRIVE TRAIN.  CLUTCH WAS REMOVED TO VERIFY NO INTERNAL DAMAGE.  THE FOLLOWING WAS FOUND DURING A TEARDOWN: 1 PEANUT INNER EAR CHIPPED, SHAFT PN C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL VERY BLACK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
             20081128     NE  2008       11         28         CA080926001      220080925G7414103571651       COIL                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       235                                                            (CAN) IT WAS FOUND WHEN THE MAG WAS ASSEMBLED NEW, THE HIGH TENSION TAB OF THE COIL WAS NOT MADE PARALLEL WITHIN THE HOUSING SPLIT LINE.  THIS CAUSED THE BRUSH TO WEAR A DEEP GROOVE INTO THE TAB.  THE BRUSH (10-160844) ALSO RECEIVED DAMAGE IN THE FORM OF A STEP GROUND INTO THE SIDE OF IT FROM THE SIDE LOAD IMPOSED BY THE BENT TAB.                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
             20081128     NM  2008       11         28         CA080926002      120080926G291082920010227     PIPE                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  HYD SYSTEM      DAMAGED         W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       12782                                                          (CAN) DURING TAXI OUT THE FLIGHT CREW REPORTED A LOSS OF NR 2 HYDR QUANTITY AND HYDR LOW PRESSURE CAUTION LIGHT.  MX DISCOVERED A HYDR TUBE LOCATED AT APPROX STA X409.00 RT SIDE HAD A (2) CENTIMETER CRACK LONGITUDINALLY ON THE INNER RADIUS OF A 90 BEND.  TUBE WAS PART OF THE MLG DOWN SYS, PRESSURE LINE, NR 2 HYDR.  TUBE WAS REPAIRED IAW THE AMM AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081128     SW  2008       11         28         CA080926003      120080914G272027720065        ARM                                     SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  RUDDER PEDAL    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FOUND 3 OF 4 RUDDER PEDAL ATTACH ARMS CRACKED ON LWR END, WHERE THE TORQUE TUBE THAT THE PEDAL IS MOUNTED TO ATTACHES TO THE CAST ARM. MATERIAL THICKNESS IS APPROX .2500 INCH IN THAT AREA.  ACFT IS 17,800 TOTAL TIME, LOW FOR THIS TYPE OF ACFT.  HAVE PREVIOUSLY FOUND 1 OTHER CRACKED ARM.                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
             20081128     CE  2008       11         28         CA080926004      120080922G2840S38521          RESISTOR                                CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  FUEL INDICATOR  WORN            W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      (CAN) DURING GROUND RUN, NOTICED THAT THE LOW FUEL WARNING LIGHT FOR THE LT SIDE WOULD FLICK ON.  IF YOU WERE QUICK ENOUGH TO CATCH IT THE LT FUEL QUANTITY NEEDLE WOULD TWITCH AT THE SAME TIME.  WITH THE SENDER REMOVED THE RESISTANCE IN THE SENDER WAS CHECKED WITH A DIGITAL MULTI METER. NORMAL OPERATION FROM THE EMPTY TO FULL IS 2 OHMS TO 90 OHMS. THE SENDER WAS FINE AT THE EMPTY POSITION AT 2 ISH OHMS UP TO 63 OHMS. PAST 63 UP TO FULL THE RESISTANCE COULD SPIKE UPWARDS AROUND 350 OHNS WHEN THE FLOAT ARM WAS WIGGLED. UNIT WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.                                                                                                                                                  1H71 3O3  ONT3A12    1E10    5  NP857     
             20081201     EU  2008       12         1          CA080926005      120080925G2597E0111241057     CONNECTOR                               AIRBUS310   A310               EU  GE    CF6   CF680       30025NE                              GALLEY POWER    DAMAGED         W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING STATION TRANSIT, CABIN CREW REPORTED SMOKE COMING FROM AFT GALLEY, WITH SMOKE WARNING, WHEN GALLEY ELECTRICAL PWR WAS PUT ON.  GALLEY POWER WAS REMOVED FROM THE AFT GALLEY.  DURING MX INVESTIGATION, THE GALLEY CONNECTOR 38 MC WAS FOUND DAMAGED WITH PINS AND SOCKET BURNED. CONNECTOR WAS REPLACED AND CAMPAIGN WAS INITIATED TO INSPECT ACFT EQUIPMENT WITH THE SAME TYPE OF INSTALLATION.                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA35EU   E13NE                
             20081202     EA  2008       12         2          CA080927001      220080926G8520130L119         PISTON RING                             ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          BROKEN          W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA            1547                                                      (CAN) PILOT REPORTED ENGINE ROUGH AT 80 PERCENT RPM.  ACFT WAS GROUNDED AND A COMPRESSION CHECK WAS CONDUCTED.  CYLINDER 1 WAS FOUND TO HAVE 58/80 PSI.  CYLINDER AND PISTON REMOVED AND COMPRESSION RING WAS FOUND CRACKED. PISTON/CYLINDER REPLACED.  ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   E295                 
             20081202     NE  2008       12         2          CA080929003      220080918G73218237002         FUEL CONTROL                            CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              ENGINE          FAILED          W      L   ABORTED APPROACH                                                                                XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA       3308 3308                                                      (CAN) ON DESCENT THROUGH 12000 FT, THE ENGINE EEC WARNING ACTIVATED, OIL PRESSURE DROPPED AND ENGINE SPOOLED DOWN TO 0.  APPROACH REJECTED AND EMERGENCY DECLARED, ACFT DIVERTED.  TROUBLESHOOTING CARRIED OUT, AS REQUESTED BY MFG, FUEL IS NOT PASSING THROUGH THE FCU, UNIT REMOVED FOR REPAIR/OVERHAUL, A REPLACEMENT UNIT HAS BEEN ORDERED.                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00059EN             
             20081209     SW  2008       12         9          CA080929005      120080924G6720369X2172313     PITCH LINK                              DOUG  500N  MD500N      3030001SW  ALLSN 250C  250C20B     03013GL                              TAIL ROTOR      SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       219                                                            (CAN) THE PITCH CHANGE ROD END BEARING BALL WAS FOUND SEPARATED FROM THE PITCH LINK.  THE PILOT REPORTED THAT THE TAIL ROTOR FELT DIFFERENT UPON LANDING.  IT WAS FOUND BY THE PILOT WHEN DOING A POST FLIGHT INSPECTION.  AN AME WAS DISPATCHED TO ATTEND THE PROBLEM.  BOTH PITCH CHANGE RODS WERE REPLACED AND THE HELICOPTER WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  UNCH3WE    E4CE                 
             20081202     WP  2008       12         2          CA080929006      120080929G6310C0183           CLUTCH                                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       955                                                            (CAN) THE C188-3 SPRAG S/N S164 REV G HAS 2 PEANUTS WITH 5 BROKEN EARS. C166-4 SHAFT SPRAG JOURNAL WORN UNDERSIZE, C167-3 HOUSING SPRAG JOURNAL WORN OVERSIZE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081202     CE  2008       12         2          CA080929007      120080920G284338522           INDICATOR                               CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170*      GL  FUEL QTY        INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FUEL QUANTITY SENDER FOUND ELECTRICALLY UNSERVICEABLE, READING EMPTY WHEN TANKS WERE FULL.  SERVICEABLE FUEL SENDER INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    1E10    5  NP857     
             20081202     EA  2008       12         2          CA080930001      120080928G5280CC670105202003  DOOR                                    CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1     30049NE                              LT MLG          MISSING         W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           APAPPROACH       1                      CA                                                                      (CAN) DURING THE WALKAROUND THE CREW NOTICED THE LT MLG DOOR WAS MISSING.  THE DOOR SEPARATED FROM ACFT DURING THE FLIG HT.  THE PRELIMINARY ASSESSMENT FROM PICTURES SHOWS THE HINGE FITTINGS CRACKED AND THE ROD END SNAPPED ON THE DOOR ATTACHMENT POINT.  LAST STRUCTURAL INSPECTION IAW AD CF2003-23 DONE 12 SEPT 2008.                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E00063EN             
             20081202     GL  2008       12         2          CA080930002      320080914G6110                PROPELLER                               FOUND FBA   FBA2C       3640102EA  LYC   O540  O540A1C5    41532EA  HARTZLHC92Z HC92ZK1     GL                  VIBRATION       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) PROPELLER REMOVED FOR EVALUATION DUE TO SMALL VIBRATION.  NOT CONSIDERED SERIOUS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  A7EA    E295    5  CP892     
             20081202     NE  2008       12         2          CA080930003      220080831G7261                SEAL                                    BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              ENGINE OIL      LEAKING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE OIL PRESSURE STARTED TO FLUCTUATE FOLLOWED BY A DROP TO ZERO, WHICH WAS ACCOMPANIED BY A GEARBOX CHIP DETECTOR WARNING FOR NR 2 POWER SECTION.  A SINGLE ENGINE LANDING WAS PERFORMED. TROUBLESHOOTING FOUND LITTLE OIL LEFT IN THE ENGINE AND A LEAK AT NR 2 PT GOVERNOR SEAL.  THE CHIP DETECTOR WAS FOUND CONTAMINATED.  THE POWER SECTION AND GEARBOX TC2523 WILL BE REMOVED AND FORWARDED FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                       1G71 4U4  U  H4SW    E22EA                
             20081202     CE  2008       12         2          CA080930004      120080929G273005117821        YOKE                                    CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C401   GL  ELEV CONTROL    CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN)  ASSEMBLY WAS FOUND CORRODED WHEN INSPECTED IAW SEB01-3.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  3A24    E5CE    5  CP47GL    
             20081202     CE  2008       12         2          CA080930005      120080929G53400512128         BRACKET                                 CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO                              FLAP PULLEY     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT FLAPS HAVE EXCESSIVE PLAY WHEN DEPLOYED.  SYSTEM INVESTIGATED AND LT SIDE FLAP PULLEY BRACKET FOUND BROKEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E5CE                 
             20081202     CE  2008       12         2          CA080930006      120080723G32464040A           WHEEL                                   CESSNA401   401         207590CCE  CONT  O520  TSIO520E    17040SO  MCAULY3AF32C3AF32C505   GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RT MAIN WHEEL ASSY BEAD AREA FOUND CRACKED.  WHEEL REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20081202     CE  2008       12         2          CA080930007      120080930G321024410071        SPACER                                  LEAR  35    35A         5170602CE  GARRTTTFE731TFE73122B   01518WP                              LT MLG ACTUATOR CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON REMOVAL OF LT GEAR ACTUATOR DUE TO HYDR BYPASS, CONICAL SPACER, P/N 2441007-1, ITEM NR 32 IN IPC 32-32-20, WAS FOUND CRACKED. RT ACTUATOR REMOVED, SPACER VISUALLY INSPECTED. NO CRACK INDICATIONS. BOTH ACTUATOR PILLARS REMOVED, CLEANED AND MAGNETIC PARTICLE INSPECTED IAW NDT MANUAL. NO DEFECTS NOTED. SURROUNDING AREA VISUALLY INSPECTED, NO DEFECTS NOTED. ACTUATORS INSTALLED WITH NEW SPACERS ON BOTH SIDES IAW ACFT MM. F/C OF GEAR C/O SERVICEABLE.                                                                                                                                                                                                                                                                     2L72 4F4  F  A10CE   E6WE                 
             20081202     SO  2008       12         2          CA080930008      120080929G8120                SEAL                                    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  TURBOCHARGER    LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    LDLANDING        1                      CA                                                                      (CAN) PILOT SAW THICK BLUE SMOKE FROM LT ENG JUST AFTER LANDING AT HOME BASE.  OIL PRESSURE INDICATIONS APPEARED NORMAL.  DURING INVESTIGATION FOUND LT TO BE 5 QUARTS LOW ON OIL, WITH NO VISIBLE EXTERNAL LEAKS.  CYL COMPRESSION CHECK SHOWED NO FAULTS.  TURBO CHARGER EXHAUST PIPE SHOWED WET OIL ON INSIDE OF EXIT PIPE.  PIPE REMOVED FROM TURBOCHARGER AND FOUND OIL STAIN IN EXHAUST TURBINE.  REPLACED TURBO AND GROUND CHECKED SERVICEABLE.  NO FAULTS REPORTED AFTER SUBSEQUENT FLIGHTS.                                                                                                                                                                                                                                            1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20081202     CE  2008       12         2          CA080930009      120080920G29101013880175      LINE                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  HYDRAULIC SYS   RUPTURED        W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) AFTER LANDING A HYDR LEAK WAS DISCOVERED BY THE MX CREW.  IT TURNED OUT TO BE THE RT MLG "REGULAR EXTEND" HYDR LINE.  THE LINE HAD RUPTURED ABOUT 1 INCH FROM THE END FITTING RESULTING IN A SUBSTANTIAL FLUID LOSS.  THE LINE WAS REPLACED WITH NO FURTHER ISSUES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
             20081202     NM  2008       12         2          CA081001001      120080916G7920                PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              ENGINE OIL      LOW PRESSURE    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT, THE LOW OIL PRESSURE WARNING FOR THE NR 2 ENGINE SOUNDED.  THE PILOT ELECTED TO SHUTDOWN AND SECURE THE ENGINE AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS PERFORMED AT DESTINATION.  GROUND INSPECTION REVEALED NO SIGNS OF EXTERNAL OIL LEAKAGE, HOWEVER THE OIL TANK SHOWED "EMPTY".  INITIAL TROUBLESHOOTING REVEALED INTERNAL DISTRESS OF THE OIL PUMP ASSY.  THE ENGINE HAS BEEN REMOVED AND WILL BE RETURNED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN             
             20081202     EU  2008       12         2          CA081001002      120080930G2440                TERMINAL                                SAAB  SF340 340B        7860101EU                                                               EXTERNAL POWER  MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ACFT ARRIVED FROM CUSTOMER WITH EXTERNAL POWER INOP (MEL).  AFTER INVESTIGATION, FOUND THE + TERMINAL MELTED AT THEN EXT PWR CONNECTOR.  SHEET METAL REPAIR WAS PREVIOUSLY DONE AT THE EXT PWR CONNECTOR ATTACHMENT.  BOTH TERMINALS WERE CRACKED HALF WAY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T    RTA52EU                        
             20081202     CE  2008       12         2          CA081001003      120080919G5751122005211       SKIN                                    CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  AILERON         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AT INSPECTION THE LT AILERON OTBD HINGE ASSY WAS FOUND CRACKED.  THE CRACKS WERE LOCATED AT THE BEND RADIUS OF THE LOWER AFT ATTACH ANGLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  A4CE    E5CE    5  CP47GL    
             20081202     SW  2008       12         2          CA081001004      120080927G5302206031329103S   FITTING                                 BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPPER LT TAILBOOM ATTACHMENT FITTING ON THE FUSELAGE SIDE FOUND CRACKED FROM THE RIVET HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H2SW    E1GL                 
             20081202         2008       12         2          CA081001006      420080924G2397GNS430          WIRE                                    UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B1   60056NE                              COMM 1          SHORTED         W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA       31                                                             (CAN) NO PILOT OR COPILOT SIDE TONE ON COMM 1.  TECH FOUND THE AUDIO PHONE WIRE SHORTED BY THE SHIELDING.  REPAIRED AND SIDE TONES WERE RETURNED TO NORMAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U3  U  H9EU    E00054EN             
             20081202     SW  2008       12         2          CA081001007      120081001G2821ZT2CV06A08B     CHECK VALVE                             BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              FUEL SYSTEM     DIRTY           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13135                                                          (CAN) AFTER A FUEL FILTER REPLACEMENT A 2 MINUTE RUN IS REQUIRED WITH BOOST PUMPS OFF TO ENSURE THERE ARE NO AIR LEAKS IN THE FUEL SYS.  DURING THIS 2 MINUTE GROUND RUN THE ENG FLAMED OUT AFTER APP 90 SECONDS INDICATING AN AIR LEAK.  FUEL SYS INSPECTED AND THE INLINE FUEL/CHECK VALVE WAS FOUND STUCK IN THE OPEN POSITION.  WHEN THIS VALVE IS STUCK OPEN AIR CAN BE SUCKED FROM THE FRONT FUEL TANKS IF THEY ARE EMPTY.  CHECK VALVES CLEANED AND HELICOPTER WAS GROUND RUN SATISFACTORILY.  THIS WAS POSSIBLY CAUSED BY FUELING FROM DRUMS FOR AN EXTENDED PERIOD OF TIME AND A SMALL QUANTITY OF DIRT ENTERED THE FUEL SYS.                                                                                                          1G71 3U3  U  H2SW    E1GL                 
             20081202     NM  2008       12         2          CA081001008      120080814G3000XD4N            RELAY                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  DEICE SYSTEM    FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       4093540935                                                     (CAN) DURING DESCENT FROM FL250, AS POWER WAS REDUCED BELOW 30 PERCENT TORQUE.  WHEN DESCENDING THROUGH 23000` CABIN STARTED TO CLIMB RAPIDLY. DE-ICE PRESSURE CAUTION LIGHT ILLUMINATED.  NO LOUD NOISES OR SQUEALS.  MX INVESTIGATION FOUND RELAY 2121-K6 AT FAULT.  RELAY REPLACED, ACFT RETURNED TO SERVICE. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND TIMES NOT TRACKED, TIMES PROVIDED ARE AIRFRAME TIMES)                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081202     CE  2008       12         2          CA081002001      120081002G3260SA24SDX111      SWITCH                                  CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF32C3AF32C505   GL  MLG             INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) LANDING GEAR INTERMITTENTLY WOULD NOT RETRACT.  FOUND ANNUNCIATOR PRESS TO TEST SWITCH INTERMITTENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  3A25    E8CE    5  CP22EA    
             20081202     CE  2008       12         2          CA081002002      120081002G32301002573         PISTON                                  CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA  HARTZLHCF3Y HCF3YR1     GL  MLG             SEPARATED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       51                                                             (CAN) RT MLG FAILED TO RETRACT.  FOUND HYDRAULIC CYLINDER PISTON HAD SEPARATED FROM CYLINDER RAM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ORTA4CE    E14EA   5  CP31EA    
             20081202     CE  2008       12         2          CA081002003      120080929G8120407809001       TURBINE WHEEL                           CESSNA340   340CESSNA   2076404CE  CONT  O520  TSIO520C    17040SO  MCAULY3AF32C3AF32C87    GL  TURBOCHARGER    SEIZED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA            774                                                       (CAN) TURBINE WHEEL SEIZED.  TURBOCHARGER REMOVED, OVERHAULED TURBOCHARGER INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  3A25    E8CE    5  CP22EA    
             20081202     NM  2008       12         2          CA081002004      120081001G2432                BATTERY                                 BOEING737   737275C     13844ASNM  PWA   JT8   JT8D17      52049NE                              MASTER          OVERHEATED      W      O   OTHER                                                                                           BM SMOKE/FUMES/ODORS/SPARKS  OVER TEMP                                           TXTAXI/GRND HDL  1                      CA                                                                      (CAN) PASSENGERS WERE ON THE ACFT, ACFT WAS ON EXTERNAL GROUND POWER AT THE TIME.  WHEN THE PILOTS WENT TO START THE APU, THEY NOTICED THE START WAS NOT NORMAL, AND THE APU ALSO DID NOT START.  APU OVERSPEED CAUTION LIGHT ILLUMINATED.  CAPTAIN WENT TO THE E&E BAY TO RESET THE APU BOX.  APU START ATTEMPTED AGAIN, SAME RESULT.  PILOT AGAIN RESET THE APU CONTROL BOX, AND THAT WAS WHEN HE NOTICED THE BATTERY SMOKING/VENTING.  IT WAS HOT TO THE TOUCH.  PEOPLE WERE REMOVED FROM THE ACFT.  MX CONFIRMED THE BATTERY WAS STILL HOT, AND IT WAS REMOVED.  A NEW OVERHAULED BATTERY WAS INSTALLED, AND THE BATTERY CHARGING CIRCUIT WAS TESTED IAW WORKCARD.  NO FAULTS WERE NOTICED, ACFT WAS RELEASED BACK INTO SERVICE.            2L72 4F4  FRTA16WE   E2EA                 
             20081126     CE  2008       11         26         CA081002005      120080929G282010192000015     LINE                                    BEECH 200   B200C       1152924CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING DAILY INSP, WITH POWER ON A FEW MOMENTS, NOTICED FUEL LEAKING FROM LT GEAR WELL. POWER TURNED OFF, NOTED FUEL LEAKING FROM SUPPLY LINE WHICH IS LOCATED BETWEEN AUX FUEL TANK AND NACELLE FUEL TANK. ON CLOSER INSP NOTICED  WHERE FUEL LINE PASSED THROUGH OPENING IN A BULKHEAD,  LINE RUBBING AGAINST B-NUT OF A HYD LINE. AFTER REMOVAL OF LINE, A WORN AREA & CRACK IN THE MIDDLE OF IT WAS FOUND TO BE THE CAUSE OF THE FUEL LEAK. THIS FUEL LINE WOULD ONLY LEAK IF FUEL WAS BEING TRANSFERRED FROM THE AUX TANK TO THE NACELLE FUEL TANK, OTHERWISE THE MOTIVE CHECK VALVE WOULD HAVE CLOSED AND NOT ALLOWED FUEL TO FLOW BACK FROM THE NACELLE TANK. PILOT HAD LEFT THE AUX FUEL TRANSFER OVERRIDE SWITCH IN THE MANUAL PO1L72 4T4  T  A24CE   E4EA    6  CP15EA    
             20081120         2008       11         20         CA081002006      120080926G5200                ACTUATOR        CNDAIR      215T752204                                     PWA   PW120 PW123            NE                              DOOR            LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       129  129                                                       (CAN) FOUND LEAKING AT THE PREES LINE CONNECTION, TSO129HRS, TOTAL DROPS 398 FOUND LEAKING DURING AN INSPECTION BY THE TECHNICAL ENGINEER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  T          E20NE                
             20081120     CE  2008       11         20         CA081002007      120080924G555304311481        FITTING                                 CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                              VERTICAL STAB   FRACTURED       W      C   ABORTED TAKEOFF                                                                                 F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT BROUGHT TO MX DUE TO ACFT NOT RESPONDING CORRECTLY, VERTICAL STABILATOR WAS INSPECTED AND A FRACTURE WAS FOUND IN THE BRACKET.  IT APPEARED TO BE A STRESS FRACTURE IN THE FITTING.  WE WOULD LIKE ALL CESSNA OWNERS TO UNDERSTAND THAT IF THE TAIL HITS THE GROUND OR IT RUBS THE GROUND IN ANY WAY THAT IT SHOULD BE INSPECTED.  THIS ACFT HAD BEEN INSPECTED APPROX 50 HOURS PRIOR AND THERE WAS NO FRACTURE AT THAT TIME.  ALL OF THE FITTINGS AND BOLTS RELATED TO THE ATTACH POINT OF THE VERTICAL FIN WERE REPLACED AND THE FIN WAS INSPECTED FOR ANY DAMAGE.  WE ARE GOING TO CONTINUE TO MONITOR THESE FITTINGS ON ALL 152`S AND IF FURTHER INFORMATION ABOUT THIS ISSUE BECOMES APPARENT TO US WE WILL UP DATE.            1H71 3O3  ONT3A19    E223                 
             20081120         2008       11         20         CA081002008      220080925G741410357584        DISTRIBUTOR GEARCONT        106006141                                                                                                   MAGNETO         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MAGNETO RECEIVED WITH TEETH BROKEN OFF THE DISTRIBUTOR GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
             20081120     EA  2008       11         20         CA081003001      120080926G5610NP13932211      WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) CAPTAINS SIDE WINDOW CENTER PANE SHATTERED ENROUTE.  MX CHANGED THE WINDOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20081120     NE  2008       11         20         CA081003002      220081001G73971710101         WIRE HARNESS                            EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FADEC           DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6526                                                           (CAN) FADEC WIRING HARNESS DAMAGED (WHICH REQUIRED REPLACEMENT) DUE TO THE LOWER SEAL ON THE PYLON PRE-COOLER LEAKING (NO LEAK/HEAT DETECTION IN THIS AREA). ATTACHED ARE PICTURES. BELOW ARE THE FIN`S AFFECTED WITH TIMES AND CYCLES. ACFT INDUCTED FOR THE FREEZE PROTECTION MOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA56NM   E00063EN             
             20081120         2008       11         20         CA081003003      120080925G8011149NL           HOUSING                                                                                                                                 STARTER         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       43                                                             (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20081120         2008       11         20         CA081003004      120080912G8011149NL           HOUSING                                                                                                                                 STARTER         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       207                                                            (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20081120         2008       11         20         CA081003005      120080924G8011                ATTACH BOLT                 149NL                                                                                                       STARTER         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       655                                                            (CAN) MOTOR TO HOUSING ATTACH BOLTS LOOSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
             20081124     NE  2008       11         24         CA081003006      220080930G7322                FLOAT           BENDIX                  DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              CARBURETOR      DAMAGED         W      O   OTHER                                                                                           YJ ENGINE STOPPAGE           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) FLIGHT CREW REPORTS THAT THE ENGINE FALTERED ON SHORT FINAL AND QUIT COMPLETELY AS THE FLOATPLANE CAME OFF THE STEP.  AFTER BEING TOWED TO THE DOCK, FUEL WAS OBSERVED POURING OUT OF THE CARBURETOR.  THE FLOAT VALVE APPEARED TO BE STUCK IN THE FULL OPEN POSITION. CARBURETOR WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.  THE CARBURETOR HAD BEEN INSTALLED 2 HOURS PREVIOUS FROM OVERHAUL.                                                                                                                                                                                                                                                                                                                                   1H71 3R3  RRCA806    5E1                  
             20081124     SW  2008       11         24         CA081003007      120080925G3233LA11C2110       ACTUATOR                                MOONEYM20   M20F        5870214SW  LYC   O360  IO360LYC*   41514EA                              MLG             FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) LANDING GEAR FAILED TO EXTEND ELECTRICALLY. ACTUATOR TEAR DOWN REVEALED THE MOTOR HAD FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O  2A3     1E10                 
             20081124     SO  2008       11         24         CA081003009      220081001G8530652420902       THRU BOLT                                                                  CONT  O360  IO360KB     17025SO                              NR 6 CYLINDER   BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            855                                                       (CAN) ON A PRE-FLIGHT INSPECTION, THE PILOT NOTICED A LOOSE WASHER ON THE FRONT OF THE ENGINE.  AFTER FURTHER INSPECTION IT WAS DISCOVERED THAT THE TOP FWD ENGINE THROUGH BOLT FOR NR 6 CYLINDER WAS BROKEN ON THE CYLINDER SIDE.  THE LOOSE WASHER WAS BECAUSE THE BOLT SNAPPED AND THERE WAS NO TORQUE ON THE OTHER SIDE AND THE NUT HAD WORKED ITS WAY LOOSE (IT WAS NEVER FOUND).  THE BROKEN PIECE OF BOLT AND NUT FROM THAT SIDE WERE FOUND ON TOP OF THE FWD ENGINE BAFFLE.  ALL OTHER BOLTS IN THE AREA WERE TORQUE CHECKED AND FOUND SERVICEABLE.  NO OTHER DEFECTS WERE NOTED.                                                                                                                                                              3  O          E1CE                 
             20081124     CE  2008       11         24         CA081004001      120081001G3245302247400       TUBE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  NLG             FOD             W      O   OTHER                                                                                           C  F.O.D.                                                                        NRNOT REPORTED   1                      CA                                                                      (CAN) TUBE HAD A HOLE CHAFED IN IT - NO EVIDENCE OF FOD INSIDE TIRE FROM INITIAL ASSY TO CAUSE WEAR HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081126     CE  2008       11         26         CA081006001      120081002G325005430223        STEERING SYS                            CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                                              INOPERATIVE     W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TOTAKEOFF        1                      CA                                                                      (CAN) INSTRUCTOR WITH A STUDENT PILOT ON BOARD REPORTED THAT ALTHOUGH RUDDER PEDAL TRAVEL APPEARED TO BE NORMAL DURING TAXI, AT THE POINT OF LIFT OFF RUDDER PEDAL MOVEMENT WAS RESTRICTED TO RT RUDDER ONLY. RUDDER COULD NOT BE MOVED TO THE LT. THE ACFT CONTINUED WITH A NORMAL CIRCUIT AND LANDED WITHOUT INCIDENT WHEREUPON THE RUDDER PEDAL MOVEMENT APPEARED TO RETURN TO NORMAL OPERATION. MAINT INSP WAS REQUESTED FOR THE ACFT. IT WAS DISCOVERED THAT THE LT STEERING TUBE ASSY, P/N 0543022-3 HAD LOST THE CUSHIONING EFFECT OF THE INTERNAL SPRING. THIS IN EFFECT HAD LEFT THE TUBE ASSY TO ACT AS A SOLID ROD, WHERE AFTER LIFT OFF WITH THE NOSE OLEO EXTENDED AND THE NOSE WHEEL LOCKED IN THE CENTER POSITION, IT WOULD HAVE 1H71 3O3  ONT3A19    E223                 
             20081124     GL  2008       11         24         CA081006002      120080929G24201707580A        CONVERTER                               BOMBDRBD700 BD7001A10   1390006GL                                                                               DAMAGED         W      O   OTHER                                                                                           MBGOVER TEMP                 SMOKE/FUMES/ODORS/SPARKS  MULTIPLE FAILURE          TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON GROUND, DURING GROOMING THE ACFT, THE AC POWER DROPPED OFF.  WHEN IT WAS RE-APPLIED, COCKPIT DISPLAYS SHOWED AC SYSTEM IN MAGENTA (NO COMMUNICATION).  FOUND THE EXTERNAL AC/DC CONVERTOR CARD LOCATED IN THE AC POWER CENTER HAD A BURNED TRACE.  THE MICROPROCESSOR CARD LOCATED ABOVE THE AC/DC CONVERTER CARD HAD A SMALL AMOUNT OF SOOT BUT NO VISIBLE DAMAGE.  THE PRIMARY LOGIC CARD WAS SOOTY AND , WHEN THE SOOT WAS WASHED OFF, A SMALL AREA ABOUT 3 SQUARE INCHES WAS DISCOLORED.  AC POWER CENTER  REPLACED TO DISPATCH THE ACFT.                                                                                                                                                                                          2L72 4F    RTT00003NY                     
             20081124     NM  2008       11         24         CA081006003      120081001G3231                CONTROL ROD                             DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE                              NLG DOOR        BROKEN          W      A   UNSCHED LANDING                                                                                 ED VIBRATION/BUFFET          INFLIGHT SEPARATION                                 CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB OUT, THE CREW NOTED A VIBRATION AND BANGING NOISE FROM THE NOSE OF THE ACFT.  THE ACFT RETURNED AND THE GROUND CREW NOTED THAT THE RT NLG DOOR WAS OPEN AND THAT THE DOOR CONTROL ROD AND TENSION SPRING (PN 83232010-105) FOR THE RT DOOR WAS BROKEN.  THERE WAS NO DAMAGE TO THE SURROUNDING STRUCTURE.  THE CONTROL ROD WAS SHEARED AT THE UPPER PERMASWAGE ON THE ROD.  GEAR INDICATION WAS NORMAL TO THE CREW.  THE BARTS WHERE REPLACED AND THE ACFT RELEASED BACK TO SERVICE.                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E20NE                
             20081120     SO  2008       11         20         CA081006004      120081003G7160434179          GROMMET                     86245041    PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6D   42305EA                              CARB HEAT BOX   MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       406                                                            (CAN) DURING A DEFECT RECTIFICATION ON OUR OTHER ACFT, IT WAS FOUND THAT THE LWR GROMMET AND BUSHING P/N 453-991 WAS MISSING ON THE LT ENGINE CARB HEAT BOX. THIS GROMMET SUPPORTS THE SHAFT IN THE CARB HEAT BOX. THIS PROMPTED THE INSP OF THIS ACFT, WHICH FOUND THE BOTTOM GROMMET AND BUSHING MISSING FROM ITS LT ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  A19S0   E286                 
             20081124     EA  2008       11         24         CA081007001      220081003G7320312240015       FADEC                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NR 2 ENGINE     MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       115                                                            (CAN) DURING PUSH-BACK FROM THE GATE WITH BOTH ENGINES RUNNING (PROPS FEATHERED), THE NR 2 ENGINE HAD AN UN-COMMANDED SHUTDOWN WITH AN ASSOCIATED NR 2 ENG FADEC FAIL WARNING LIGHT AND POWERPLANT MSG.  INTERROGATION OF THE CDS REVEALED THE FOLLOWING FAULT CODES: 705, 707, 734, MPT, 737, 740, 748 & 749. FIM TASKS ARE CURRENTLY IN WORK, BUT AS FAULT CODES 705 & 707 ARE INDICATING AN INTERNAL FAULT IN THE FADEC.  FADEC REPLACED IAW AMM TASK 73-21-01-400-801, FAULT CODES CLEARED, PLA TRIM AND ENGINE RUNS CARRIED OUT SUCCESSFULLY.                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN             
             20081124     NE  2008       11         24         CA081007002      220080906G7200                ENGINE                                  SKRSKYS92   S92A               NE  GE    CT7TS CT78A       30136NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) POST LANDING AND TAXI.  ACFT WAS STATIONARY WITH BOTH ENGINES IN THE GROUND IDLE POSITION WITH ROTORS TURNING.  PILOT OBSERVED ROTOR SPEED WAS NEARING A KNOWN "AVOID RANGE" AND ELECTED TO NUDGE THE NR 1 ENGINE CONTROL LEVER FORWARD TO INCREASE ROTOR SPEED SLIGHTLY ABOVE THE AVOID RANGE.  DURING THE EXECUTION OF THIS MARGINAL CONTROL LEVER MOVEMENT, THE RELATED ENGINE THEN UNEXPECTEDLY SHUTDOWN.  NO OTHER INDICATIONS OF A PROBLEM WERE OBSERVED BY EITHER PILOT.  THE HUMS DATA WAS DOWNLOADED AND DURING REVIEW IT WAS DISCOVERED THAT DURING THE CONTROL LEVER INCREASE, THE NR 1 ENGINE TGT SPIKED TO 1100 DEGREES C FOR A PERIOD OF 3 SECONDS BEFORE THE AUTOMATED PROTECTIVE CIRCUITS OF THE FADEC SHUT THE ENGINE DOW2G72 4U4  U  R00024BOE8NE                 
             20081124     NM  2008       11         24         CA081007003      120081006G5754NAS86034NAS86   SCREW                                   BOMBDRCL600 CL6002D15          NM  GE    CF34  CF348C5     30050NE                              SLAT            LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ALL SCREWS ON TOP OF WING UNDER THE SLATS WERE FOUND LOOSE. 2 SCREWS , 1 ON EACH SIDE, WERE FOUND PROTRUDING BEYOND THE WING SURFACE CAUSING  MINOR DAMAGE TO THE UNDER SKING SURFACE OF THE SLAT. ALL SCREWS WERE TIGHTENED BACK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E00063EN             
             20081124     NM  2008       11         24         CA081007004      120080929G213010010602        CIRCUIT CARD                            EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              CABIN PRESSURE  MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE AT APPROX 1500`, BLEED NR 1 AND NR 2 FAILED EICAS MSGS APPEARED, AND QRH CARRIED OUT (RESET) BUT UNSUCCESSFUL. ACFT DID NOT PRESSURIZE, AND RETURNED TO BNA FOR MX.  OTHER PNS AND SNS AFFECTED:                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA56NM   E00063EN             
             20081120         2008       11         20         CA081007005      420081007G3160071015980301    CONTROLLER                              PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67      52043NE                              MFD             FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       100  100                                                       (CAN) THE ABOVE MFD CONTROLLER IS A JOYSTICK TYPE CONTROL THAT ALLOWS THE CREW TO MAKE SELECTIONS ON THE MFD SCREEN IN THE MFG APEX SYS. THE JOYSTICK FAILS TO MOVE THE CURSOR TO THE RT AS DISPLAYED ON THE MFD SCREEN. THE CONTROLLER WAS REPLACED WITH A NEW ITEM THAT CLEARED THE PROBLEM THIS IS THE SECOND REPLACEMENT ON THIS ACFT SINCE NEW 150 HRS TT.                                                                                                                                                                                                                                                                                                                                                                                 1L71 4T4  TRTA78EU   E26NE                
             20081126     EU  2008       11         26         CA081007006      120081007G2910MS287786        O-RING                                  BAG   JETSTMJETSTM3112  1500220EU  GARRTTTPE331TPE33110    29053NE  ROTOL R333  R333482F12  GL  COUPLING        FAILED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) DURING GEAR DOWN LANDING CHECKS, ONLY NOSE GEAR LOCKED, BOTH MLG UNSAFE.  REQUESTED LOW AND OVER-CYMM FSS CONFIRMED 3 GEAR DOWN. RE-POSITIONED TO A SAFE AREA AND PERFORMED ITEMS LISTED ON QRH. PUMPED GEAR DOWN MANUALLY, GEAR WAS CONFIRMED 3 DOWN AND LOCKED. LANDED, WITH NO STEERING AND LIMITED BRAKE USE. STOPPED ACFT ON TAXIWAY A.  TOWED TO HANGER WITH PAX EMERGENCY SERVICES ON STANDBY FOR THIS INCIDENT. MAINT INSP CONFIRMED LT HYDR PUMP PRESSURE RETURN INLET BANJO COUPLING BASE O-RING HAD FAILED, CAUSING EXCESSIVE FLUID LOSS.  REMOVED AND REPLACED DEFECTIVE O-RING WITH NEW.  HYD SYS REPLENISHED GEAR, FLAP, STEERING, BRAKE SYSTEMS BLED, GEAR SWINGS C/O AND SYS F/C C/O SYS SERVICED AND L/C C/W.            2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
             20081124     EU  2008       11         24         CA081007007      120080929G5310350A38101832    CROSSBEAM                               SNIAS 350   AS350BA     8680817EU  ALLSN 250C  250C30      03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4692 702                                                       (CAN) A BI DIRECTIONAL CROSS BEAM WAS SENT OUT FOR NDT INSPECTION AND A CRACK INDICATION WAS FOUND INBD RADIUS OF CROSS BEAM WHERE THE LAMINATED MOUNT ATTACHES. A SECOND NDT INSPECTION WAS PERFORMED WITH THE SAME RESULTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  UNCH9EU    E1GL                 
             20081124     CE  2008       11         24         CA081007008      120081007G3340CM358910        SWITCH                                  CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              TAXI LIGHT      INOPERATIVE     W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         NRNOT REPORTED   1                      CA       566                                                            (CAN) TAXI LIGHT SWITCH FAILED WITH 566 HRS OF ACFT OPS FAULT WAS FOUND WHEN TRYING TO CHECK TAXI LIGHT FOR OPS.  SWITCH WAS REPLACED 7 MONTHS AGO AND 566 HRS OF OPS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    1E10                 
             20081124     CE  2008       11         24         CA081007009      120081001G3397903641241       C/BREAKER PANEL                         BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                              COCKPIT         BURNED          W      BA  EMER. DESCENT           UNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) PILOTS REPORTED FLAMES AND FIRE FROM LOWER RT CORNER OF THE RT CIRCUIT BREAKER PANEL AND MADE AN EMERGENCY LANDING. THE CIRCUIT BREAKER FOR THE EDGE LIGHTED PANEL LIGHTS OPENED AS A RESULT OF THE SHORT AT 1 BULB BUT NOT BEFORE THE HEAT HAD BURNED PART WAY THROUGH THE EDGE LIGHTED PANEL AND STARTED TO HEAT THE OVER LYING CIRCUIT BREAKER PANEL. NO FURTHER DAMAGE WAS NOTED. THIS EDGE LIGHTED PANEL WAS PREVIOUSLY INSPECTED AS PER THE MM ABOUT 565 HOURS AGO.                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
             20081124     SW  2008       11         24         CA081007010      120081002G32405011639         DISC                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  BRAKE           WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS BRAKE ASSEMBLY WAS REMOVED FROM ACFT ON THE RT - O/B GEAR FOR BRAKE WEAR BEYOND LIMITS.  UPON TEAR DOWN THE LUGS WERE FOUND TO HAVE WORN APPROXIMATELY 40% WHILE THE RIM SIDE HAD MINIMAL WEAR AND THE RIM WAS RETURNED TO SERVICE.  THIS TYPE OF WEAR IS NOT COMMON AS THEY WEAR CONSISTENTLY SIMILAR.  FURTHER INVESTIGATION WILL BE ACCOMPLISHED IN ORDER TO POSSIBLY DETERMINE OTHER CAUSES AS TO WHY THE UNEVEN WEAR PATTERN.                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081126     CE  2008       11         26         CA081008001      120080818G3220                FORK                                    CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6816                                                           (CAN) DURING A ROUTINE OPERATION, NR 2 INSP, A SUSPECTED CRACK WAS FOUND ON NLG FORK.  EDDY CURRENT REVEALED A LARGE DEFLECTION IN THE SUSPECTED AREA. SUBSEQUENTLY THE INSP WAS CONDUCTED ON THE OPPOSITE SIDE OF THE NLG FORK WITH THE SAME RESULTS. ADDITIONALLY FPI WAS ALSO DONE TO SHOW VISUALLY UNDER BLACK LIGHT. CRACKS WERE CLEARLY VISIBLE ON BOTH SIDES OF THE FORK UNDER THE BLACK LIGHT. THE ACFT WAS REMOVED FROM SERVICE AND A NEW NLG FORK ASSY WAS ORDERED FROM MFG AND INSTALLED UPON ARRIVAL.                                                                                                                                                                                                                               1H71 3O3  ONT3A12    E274    5  NP910     
             20081124     GL  2008       11         24         CA081008002      120080923G24102224121400      BRACKET                                 DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ALTERNATOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       715                                                            (CAN) ON SEPTEMBER 2, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES. THIS WAS THE SECOND CRACKED BRACKET FOUND ON THIS ACFT AND BOTH CRACKS HAVE BEEN LOCATED IN THE IDENTICAL LOCATIONS.                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTTA4CH   E7SO                 
             20081124     GL  2008       11         24         CA081008003      120080923G24102224121400      BRACKET                                 DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ALTERNATOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       448                                                            (CAN) ON MARCH 14, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O3  ONTTA4CH   E7SO                 
             20081124     SW  2008       11         24         CA081008006      120081007G5210205D10282       WINDOW FRAME                            BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              JUMP DOOR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) 10 INCH CRACK FOUND AT UPPER LT CORNER OF WINDOW FRAME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 4U4  U  H4SW    E22EA                
             20081124     NM  2008       11         24         CA081008007      120081008G5210SB003T0023      PANEL                                   DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE                              COCKPIT DOOR    MISALIGNED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLEX IN LAV WALL IS CAUSING SIGNIFICANT IN-SERVICE MISALIGNMENT OF PONS INSTALLED IN LATCH HOUSING USING TTF-SB-03T002-001.  REFER TO PROTECTED "A" AD CF-2008-26R1 AND STC SA03-70, SB TTF-SB-03T002-001 REV "D".                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE                
             20081124     EA  2008       11         24         CA081009001      120081002G38105000120701      WATER HEATER                            CNDAIRCL601 CL6013A     8070802EA                                                               FWD GALLEY      DAMAGED         W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB OUT SMOKE WAS OBSERVED COMING OUT OF THE FUEL CONTROL PANEL IN THE FORWARD GALLEY.  THE WATER HEATER INSULATION BLANKET IN THE FORWARD GALLEY HAD EVIDENCE OF HEAT DAMAGE.  INSTALLATION OF THIS PART IN THE FORWARD GALLEY OF THE ACFT IS A PART OF SUPPLEMENTAL TYPE CERTIFICATE ST09049SC.  THE PART IN QUESTION HAS BEEN FORWARDED TO THE TSB.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA21EA                        
             20081124     CE  2008       11         24         CA081009002      120080918G5753S16612          SWITCH                                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              TE FLAP         DAMAGED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       5911                                                           (CAN) THE FLAP SWITCH SHOULD SPRING BACK TO OFF POSITION WHEN PRESSURE IS RELEASED. THE PILOT SELECTED 20 OF FLAP TOOK PRESSURE OFF SWITCH BUT THE FLAPS EXTENDED TO 40 NEW SWITCH INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    E274                 
             20081124     GL  2008       11         24         CA081009003      220081002G732323065123        GOVERNOR                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              TURBINE         INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1234                                                           (CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED,                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H2SW    E4CE                 
             20081124     NM  2008       11         24         CA081009004      120081003G2421ALX8521R        ALTERNATOR                              ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                                              INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            331                                                       (CAN) ALTERNATOR LIGHT ILLUMINATED IN FLIGHT, ALTERNATOR CHECKED AND NOT CHARGING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H10WE   E286                 
             20081124     NE  2008       11         24         CA081009005      220080929G741410600646201     MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       90                                                             (CAN) ENGINE TACH FLUCTUATING, MAGNETO REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
             20081124     WP  2008       11         24         CA081009006      120080930G2435BC3151004       STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            359                                                       (CAN) STARTER NOT ENGAGING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081124     NM  2008       11         24         CA081009007      120081009G2781651781823       SWITCH          DECOTO                  BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              SLAT ACTUATOR   FAILED          W      JA  DUMP FUEL               UNSCHED LANDING                                                         N  FALSE WARNING                                                                 CLCLIMB          1                      CA            47                                                        (CAN) JUST AFTER DEPARTURE FROM YYZ, THE PILOTS NOTICED WHEN SELECTING FLAPS 5 TO FLAPS 2, THE LEADING EDGE FLAP INDICATOR ON THE FORWARD PANEL WENT MOMENTARILY GREEN THEN BACK TO AMBER.  THE LEADING EDGE INDICATOR ON THE REAR PANEL INDICATED THE NR 1 LEADING EDGE IN TRANSIT.  FUEL WAS DUMPED IN ORDER TO REDUCE LANDING WEIGHT OF THE ACFT AND THE ACFT RETURNED TO YYZ.  MX TROUBLESHOT THE SYSTEM AND INSTALLED A JUMPER CABLE ON THE SLAT ACTUATOR TO ENABLE THE ACFT TO DEPART.                                                                                                                                                                                                                                                    2L73 4F4  F  A3WE    E2EA                 
             20081124     NM  2008       11         24         CA081009008      120081008G2497                WIRE                                    BOMBDRCL600 CL6002D15          NM  GE    CF34  CF348C5     30050NE                                              CHAFED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) FLIGHT ATTENDANT REPORTED A BURNING ODOR IN THE CABIN.  THE ACFT LANDED UNEVENTFULLY.  THE CAUSE OF THE ODOR WAS TRACED TO CHAFED WIRE ABOVE THE FORWARD LAVATORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E00063EN             
             20081124     GL  2008       11         24         CA081009009      120080927G2497                WIRE            KELLY                   DIAMONDA40  DA40        2990002GL  CONT  IO360 IO360*      17025CE                              ALTERNATOR      BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) A+ TERMINAL MELTED OFF ALTERNATOR AND LOOSE. PROBLEM CAUSED BY BROKEN TERMINAL ON A+ WIRE GOING TO ALTERNATOR.  WIRE WAS ORIGINALLY VERY TIGHT CAUSING THE BREAKAGE, THEN IT ARCED CAUSING HEAT AND EVENTUAL FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  ONTA47CE   E1CE                 
             20081126     NE  2008       11         26         CA081009010      220080929G7532PN1422010       CLEVIS                                  EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              BLEED VALVE     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) (ENGINE INTAKE VARIABLE BLEED VALVE ACTUATOR) INTERFERENCE HAS OCCURRED BETWEEN THE SUBJECT CLEVIS LUG AND ADJACENT HARDWARE.  THE DAMAGE APPEARS TO BE A RESULT OF CONTACT WITH AN ADJACENT BOLT HEAD.  ACTUATOR ASSY: P/N 8100-052, S/N WYGB1199 (CLEVIS: P/N 1422-010 [REF CMM 75-30-02, FIGURE 01, ITEM 010)                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA57NM   E00070EN             
             20081126     GL  2008       11         26         CA081009011      120081007G27202227271100      RUDDER PEDAL                            DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  COCKPIT         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3498                                                           (CAN) ACFT WAS INSPECTED BY MAINT TO REPLACE A DEFECTIVE RUDDER PEDAL ADJUSTING CABLE. UPON COMPLETION OF THE JOB IT WAS NOTICED THAT THE SLIDE ASSY WAS NOT ABLE TO MAKE FULL TRAVEL. CLOSER INSP FOR OTHER SYMPTOMS REVEALED THAT THE RUDDER CABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TO THE PEDAL ASSY. CABLE WAS EXPOSED THROUGH THE LWR BEND OF THE S-TUBE TO A POINT WHERE IT JAMMED IN ITS WEAR HOLE AND RESTRICTING THE SLIDE ACTION. THE PEDAL ASSY AND THE CABLE WERE REMOVED FOR CLOSER INSP AND REPLACEMENT PARTS ARE ON ORDER.   WEAR ON THE S-TUBE BECOMES CRITICAL WHEN THE CABLE BECOMES VISIBLE FROM THE OUTSIDE OF THE TUBE. IT IS ALSO AN AREA THAT YOU WOULD NOT EXPECT THIS TO HAPPEN THEREFORE IT COULD BE OVERLOO1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081126     NM  2008       11         26         CA081010001      120080927G2820                LINE                                    BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              FUEL SYSTEM     CRACKED         W      O   OTHER                                                                                           KE FLUID LOSS                VIBRATION/BUFFET                                    APAPPROACH       1                      CA                                                                      (CAN) EXPERIENCED A LT ENG FUEL LEAK DURING APPROACH/LANDING.  MAINT IDENTIFIED AND REPLACED A CRACKED P/N BRH19082 FUEL PIPE. ON 28 SEP/08, ACFT WAS FERRIED. WHEN ACFT WAS ON TAXI INTO THE RAMP, ANOTHER ACFT BEHIND REPORTED FUEL POURING FROM UNDER THE LT ENGINE.  MAINT FOUND THAT PIPE WAS CRACKED AGAIN. SEVERAL FIRE LOOP BRACKETS WERE ALSO FOUND CRACKED. THE LT ENG WAS REPLACED, S/N 13243 OFF, THIS ENG HAD JUST BEEN INSTALLED ON 2 SEP/08, AT TIME OF REMOVAL: TSI 55 HOURS, CSI 35 CYCLES. HIGH VISIBILITY EVENT BY THE FAA DUE TO FUEL LEAK. ENG 13243 IN FOR INVESTIGATION. TEST BED RUN CONFIRMED HIGH VIBRATION EMANATING FROM ACCY GEARBOX, WHEN ENGINE POWERED UP AN OIL LEAK EMANATED FROM THE GEARBOX AT FUEL PUMP LOC2L72 4F4  FTRA6WE    E00061EN             
             20081124     NE  2008       11         24         CA081010002      220081009G731063E951          HOUSING         GRIMES                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              FUEL FILTER     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) MX DISCOVERED NR 1 ENGINE FUEL FILTER ASSEMBLY LEAKING FROM THE TOP OF THE FILTER HOUSING.  HOUSING IS EITHER CRACKED AROUND TOP FITTING OR IS LEAKING THROUGH PRC AROUND FITTING.  FUEL FILTER ASSEMBLY 4106T62P01 REF IPC 73-11-00 FIG 1 ITEM 110A INSTALLED.  ENGINE TTSN: 26020 HOURS, CYCLES 21453. AFTT: 31453 HOURS, CYCLES: 26057                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
             20081124     EA  2008       11         24         CA081010003      120081010G2750855D10011       BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              RT WING TE FLAP UNSERVICEABLE   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA       1010010100                                                     (CAN) ON APPROACH, AND UPON INITIAL FLAP SELECTION THE CREW RECEIVED FLAP FAILURE CAUTION MSG.  CREW CARRIED OUT A FLAP ZERO LANDING.  CREW SAID LANDING WAS UNEVENTFUL.  NO EMERGENCY DECLARED, NO CALL OUT REQUIRED.  WILL UPDATE INFO AS RECEIVED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20081124     SW  2008       11         24         CA081010004      120081003G3040                HEATER                                  GULSTM680   680         0141602SW  PWC   PW306 PW306C      52169NE                              WINDSHIELD      SMOKE           W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA       613                                                            (CAN) SMOKE DETECTED IN COCKPIT ON ENGINE STARTUP. PROBLEM ISOLATED TO LT WINDSHIELD.  RECTIFIED BY REPLACEMENT OF PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H72 3O4  F  2A4     E35NE                
             20081124     EA  2008       11         24         CA081010005      120081002G5343VALTBS112091    ATTACH FITTING                          DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA                              WING/MLG        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE WING GEAR/STRUT ATTACH FITTING TO BE CORRODED (LEVEL 3).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3T4  T  A806    E4EA                 
             20081124     EA  2008       11         24         CA081010006      120081002G2731C2T29A          TORQUE TUBE                             DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA                              ELEVATOR TRIM   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE 100 HOUR INSPECTION A AME FOUND THE ELEVATOR TRIM TORQUE TUBE TO BE CRACKED, PART WAS REPLACED AND CUSTOMER WAS ADVISED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3T4  T  A806    E4EA                 
             20081124     EA  2008       11         24         CA081010007      120081002G3246VALBVS12601     FITTING                                 DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA                              MLG FLOAT       SPLIT           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE FLOAT FITTING TO HAVE TYPE 3 CORROSION THAT CAUSED FITTING TO SPLIT.  FITTING REPLACED WITH NEW PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3T4  T  A806    E4EA                 
             20081124     EA  2008       11         24         CA081010008      220081003G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                                              MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       156                                                            (CAN) POOR MAG DROP, TIMING LIGHT FLICKERING BEFORE 25 DEGREES.  MAGNETO REPLACED WITH A SERVICEABLE MAGNETO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    1E10                 
             20081124     EA  2008       11         24         CA081010009      220081003G74144371            MAGNETO                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                                              MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       156                                                            (CAN) POOR MAG DROP.  TIMING LIGHT FLICKERING BEFORE 25 DEGREES.  REPLACED WITH SERVICEABLE MAGNETO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    1E10                 
             20081124     EA  2008       11         24         CA081010010      220081002G7321                SCREW                                   DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA                              FCU             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION POST RUN UP THE AME FOUND THE IDLE NEEDED TO BE ADJUSTED.  UPON LOOSENING IDLE SCREW JAM NUT IDLE SCREW FAILED DUE TO LEVEL 3 CORROSION. FCU REMOVED AND SENT FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3T4  T  A806    E4EA                 
             20081124     SW  2008       11         24         CA081010011      120081010G3500AS4857D01       TEE FITTING                             GULSTM680   680         0141602SW  PWC   PW306 PW306C      52169NE                              OXYGEN SYSTEM   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1251                                                           (CAN) DURING MX WALK AROUND FOUND LT OXYGEN SYSTEM LEAKING.  UPON INVESTIGATION FOUND TEE FITTING LOCATED AT LT FUSELAGE OXYGEN GAUGE CRACKED AT 2 POINTS.  IT APPEARS THAT UPON ORIGINAL INSTALLATION OF FITTING IT WAS OVER TORQUED.  FITTING REPLACED WITH NEW.  LEAK CHECKS CARRIED OUT.  SYSTEM FUNCTION CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                              1H72 3O4  F  2A4     E35NE                
             20081124         2008       11         24         CA081014001      120081010G6100                SHAFT                                                                      PWA   118   PW118            NE                              PROPELLER       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) EIR PW100-0477 CRACKED PROPELLER SHAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  T          E20NE                
             20081124     CE  2008       11         24         CA081014002      120081008G273007606861        CONTROL TUBE                            CESSNA182   182Q        2072732CE  CONT  O470  O470U       17026SO  MCAULY2A34C C2A34C204   GL  LT ELEVATOR     GOUGED          W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA       9986                                                           (CAN) THE BOLT PN AN21-10 ATTACHING THE LT ELEVATOR CONTROL CABLE PN 0510105-90 TO THE LT BELLCRANK CONTROL ARM ASSEMBLY PN 0760686-1 IS RUBBING ON THE LT BELLCRANK CONTROL TUBE SUPPORT PN 0760693-1.  THE DAMAGE IS 0.039 DEEP, 1.750 LONG AND 0.250 WIDE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A13    E273    5  CP3EA     
             20081124     CE  2008       11         24         CA081014003      120081009G2731071250012       ACTUATOR                                CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  HORIZ STAB TRIM SEPARATED       W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA       100                                                            (CAN) ACFT HORIZONTAL STAB TRIM JAM ON LANDING. ELEVATOR CONTROLS BECAME LIGHT.  ACFT LANDED WITHOUT INCIDENT.  UPON INSPECTION AT THE DOCK, THE PILOT FOUND THE HORIZONTAL STAB WAS COMPLETELY LOOSE,  STAB COULD BE MOVED FULL TRAVEL UP AND DOWN WITH NO RESISTANCE FROM THE TRIM JACKS.  MX FOUND THE TRIM JACK BARREL COULD BE SLID ON TO THE SCREW OF THE SCREW JACK WITH HAND PRESSURE, WHEN NORMALLY THEY HAVE TO BE SCREWED ON TO THE ACTUATOR SCREW.  BOTH BARRELS WERE FOUND TO HAVE THREADS ONLY ON 1 SIDE OF THE BARREL, INSTEAD OF COMPLETELY AROUND THE INSIDE OF THE BARREL.  THE ACTUATORS WERE REPLACED AND CESSNA DISTRIBUTOR CONTACTED DUE TO THE ACTUATORS IN QUESTION WERE ONLY 3 MONTHS OLD AND 100HRS. SINCE NEW TIME IN1H71 3O3  O  3A24    E5CE    5  CP3EA     
             20081124     NM  2008       11         24         CA081014004      120080917G52101700375200      SEAL                                    EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              PAX DOOR        GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) T FWD PAX DOOR AFT LATERAL SEAL (PN 170-03752-001) WAS FOUND GOUGED AT 3 LOCATIONS. PLEASE REFER TO THE ATTACHED PICTURES FOR DETAILS, TYPICAL DAMAGE SEEN TO THE PAX/SERVICE DOOR CUTOUT SEAL RESTS.  EMB HAS ISSUED A TYPICAL IC APPROVAL THAT PERMITS PERMANENT BLENDING OF UP TO 20% THICKNESS.                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA57NM   E00070EN             
             20081124     NE  2008       11         24         CA081014005      220081006G732287327003        ARM             PIPER                   PIPER PA44  PA44180     7104402SO  LYC   O360  LO360A1H6   42294NE                              CARB HEAT       SEPARATED       W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       379                                                            (CAN) THE ACFT RETURNED TO THE RAMP WITH REPORTED RT CARB HEAT U/S. INVESTIGATION REVEALED THE WELD SECURING THE ACTUATOR ARM ONTO THE CARB AIR DOOR HAD BROKEN CAUSING THE ARM TO SEPARATE FROM THE SHAFT.  THE WELD APPEARED TOO THIN IN COMPARISON TO THE LT ENGINE CARB AIR DOOR ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A19S0   E286                 
             20081124     SO  2008       11         24         CA081014006      120081006G7160434179          GROMMET         PIPER                   PIPER PA44  PA44180     7104402SO  LYC   O360  LO360A1H6   42294NE                              AIR BOX         MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       379                                                            (CAN) DURING A DEFECT RECTIFICATION ON THE CARB AIR DOOR ON THE RT ENGINE IT WAS DISCOVERED THAT THE LT ENGINE CARB AIR DOOR LOWER SHAFT SUPPORT BUSHING PN, 453-991 AND GROMMETT WERE MISSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A19S0   E286                 
             20081126     CE  2008       11         26         CA081014007      120081001G32461368520629      BEARING                                 BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              WHEEL           FAILED          W      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                TXTAXI/GRND HDL  1                      CA                                                                      (CAN) LT MLG OTBD MAIN WHEEL ASSY BECAME DETACHED FROM THE AXLE ASSY, ONLY BEING HELD ON BY THE OUTER MAIN WHEEL AXLE NUT AND BRG CONE.  INITIAL INVESTIGATION CONFIRMED THAT THIS WAS THE RESULT OF AN EXTREME BEARING FAILURE. FAILURE WAS TO SUCH EXTENT THAT IT ACTUALLY WELDED THE INNER BRG RACE PERMANENTLY TO THE AXLE AND HEAT TRANSFER TO THE NR2 WHEEL ALSO RESULTED IN A BEARING BURN WHICH IS NOT SEVERE IN MATTER BUT IS AN INDICATION OF HOW FAR THE INITIAL FAILURE EXTENDED. DAMAGE REQUIRED  REMOVAL OF THE LT GEAR LEG AND INSTALLATION OF A SERVICEABLE GEAR LEG. BOTH MAIN WHEEL ASSEMBLIES AFFECTED WERE REPLACED. ACFT WAS THEN RETURNED TO SERVICE. ONE WHEEL ASSY WAS DESTROYED AND THE OTHER SENT OUT FOR TESTING. BEA2L72 4T4  TRTA24CE   E26NE                
             20081126     SW  2008       11         26         CA081014009      120080904G3397                WIRE                                    BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              AT NAV LIGHT    CHAFED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) PILOT TURNS ON ALL REQUIRED BREAKERS FOR FLIGHT INCLUDING NAV LIGHTS. PRE LIFT-OFF THE PILOT NOTES THE BREAKER FOR THE NAV LIGHTS AT MIDPOINT. PILOT RESETS SWITCH AND LIFTS OFF. AS THE ACFT FLIES THROUGH 300 FT,  THE PILOT TURNS ON THE HEATER AND IN A FEW SECONDS SEES A MIST COMING FROM OVERHEAD PANEL. HEATER IS SWITCHED OFF THEN PILOT REALIZES ITS SMOKE FROM HOT WIRES. BATTERY, GENERATOR IS SWITCHED OFF AND ACFT RETURNS UNEVENTFUL TO THE TAKEOFF AREA. UPON INVESTIGATION, AN INITIAL SHORT IN THE NAVIGATIONAL LIGHTS CAUSED THE BREAKER TO TRIP. THE PILOT RESETS THE BREAKER WHICH CAUSES THE BREAKER POINTS TO WELD AND MAINTAIN CURRENT TO THE SHORTED NAV LIGHTS. THIS CAUSED THE WIRE FROM THE BUSS TO THE BREAKE1G71 3U3  U  H2SW    E4CE                 
             20081124     CE  2008       11         24         CA081015001      120081006G29106000100184      LINE                                    LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              HYD SYSTEM      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       3249                                                           (CAN) RETURN LINE FROM HYDRAULIC RETURN FILTER TO HYDRAULIC RESERVOIR 1/2" CRACK AT 90 DEGREE BEND ON LINE. CAUSE, MAIN HYDRAULIC SYSTEM RETURN LINE CHATTERING AGAINST A HYDRAULIC LINE WHICH GOES FROM THE AUXILIARY HYDRAULIC PUMP TO AUXILIARY PUMP INLINE FILTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA10CE   E35NE                
             20081124     EA  2008       11         24         CA081015002      220081006G8530AEL11795        SPRING                                  BNORM BN2   BN2B27      7080227EU  LYC   O540  O540E4C5    41532EA  HARTZLHCC2Y HCC2YK2     GL  INTAKE VALVE    BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       333                                                            (CAN) DURING INSPECTION OF LYCOMING SB 388C FOUND BROKEN INNER SPRING PART NR AEL11795 ON INTAKE AND EXHAUST VALVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3O3  O  A17EU   E295    5  CP920     
             20081124     NE  2008       11         24         CA081015003      220081015G7497BL60064620      WIRE                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         MISROUTED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1287                                                      (CAN) TACH WIRE CHAFING ON TACH POINT CONNECTOR TACH WIRES INCORRECTLY ROUTED.  TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING.  LAST MX ON MAGNETO WAS PRO AERO.  MAGNETO WAS REMOVED DUE TO ENGINE/ACFT OVERSPEED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   1E4                  
             20081124     NE  2008       11         24         CA081015004      220081015G749710400586        WIRE                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              TACH            MISROUTED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       235                                                            (CAN) TACH WIRES INCORRECTLY ROUTED COIL PRIMARY WIRE INCORRECTLY ROUTED. TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING.  MAGNETO WAS REMOVED FOR ENGINE/ACFT OVERSPEED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
             20081124     NE  2008       11         24         CA081015005      220081015G749710400586        WIRE                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              TACH            PINCHED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       90                                                             (CAN) TACH WIRE WAS PINCHED BETWEEN HOUSING AND CAPACITOR TACH WIRES INCORRECTLY ROUTED TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING MAGNETO WAS REMOVED FOR FLUCTUATING ENGINE TACH NEEDLE .                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
             20081124     EA  2008       11         24         CA081015006      220081015G749710400586        WIRE                                    ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              TACH            CHAFED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       151                                                            (CAN) TACH WIRES CHAFED THROUGH AND GROUNDING TO THE COIL PRIMARY CONNECTOR.  TACH WIRES INCORRECTLY ROUTED TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING.  VERY HIGH RESISTANCE FOUND BETWEEN THE TERMINALS OF THE TACH POINTS, WHEN CLOSED 1200-1500 OHMS, PROBLEM IS BLACK COATING ON TACH POINT ARM CAUSING A HIGH RESISTANCE.  MAGNETO REMOVED FROM ACFT BECAUSE IT WANTED TO OVERSPEED.                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   E295                 
             20081124     NM  2008       11         24         CA081016001      120081010G27811702286A        SENSOR                                  EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              FLAP SKEW       INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       1688                                                           (CAN) FLIGHT WAS INBOUND WHEN THE CREW HAD A FAILURE ON SLAT/FLAP 1 SELECTION.  ALSO SPOILER FAULT, AOA FAIL AND SHAKER ANTICIPATED CAS MSGS.  THE ACFT LANDED AND TAXIED TO THE GATE WITH HOT BRAKES.  FOUND OPEN CIRCUIT BETWEEN PINS 2 AND 4 OF THE LT OB SKEW SENSOR.  REPLACED SENSOR AS PER MM 27-83-01, CHECKED SERVICEABLE. ALL OTHER FAULTS CORRELATED TO SLAT FAILURE.                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA56NM   E00063EN             
             20081124     NM  2008       11         24         CA081016002      120081006G27811702286A        SENSOR                                  EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              SLAT SKEW       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, WHEN FLAP 2 SELECTED, EICAS SLAT FAIL MSG.  QRH CARRIED OUT.  UNEVENTFUL LANDING. SKEW SENSOR 2 AND 3 AFFECTED AND REPLACED PER AMM 27-83-01.  OPS CHECK SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA57NM   E00070EN             
             20081126     EA  2008       11         26         CA081016003      120081010G4930MS29513021      O-RING                                  CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF348E5A1   30062NE                              EMI FILTER      FAILED          W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA       2790                                                           (CAN) ACFT, PRIOR TO ENG START APU HAD AN UNCOMMANDED SHUTDOWN. WHILE CARRYING OUT COCKPIT TROUBLESHOOTING PILOTS OBSERVED APU BOOST PUMP FAIL LIGHT WAS ILLUMINATED. APU BOOST PUMP WAS SUSPECT BECAUSE IT HAD JUST BEEN CHANGED THE PREVIOUS DAY FOR SAME SNAG. BOOST PUMP ELECTRICAL CONNECTOR MALE PINS WERE FOUND CHARRED AND MELTED.  FEMALE PORTION OF CONNECTOR WAS ALSO FOUND CHARRED AND FUEL SOAKED. SUSPECT O-RING THAT PREVENTS FUEL FROM ENTERING CONNECTOR HAD FAILED ALLOWING FUEL TO DEGRADE THE INSULATION MATERIAL TO THE POINT WERE THE PINS SHORTED OUT. A NEW EMI FILTER HARNESS AND BOOST PUMP WERE INSTALLED AND ACFT RETURNED TO SERVICE.  FYI THE APU BOOST PUMP FUEL IS USED TO COOL.  APU LUBRICATING OIL. WITH NO F2L72 4F4  FRTA21AE   E00063EN             
             20081124     NE  2008       11         24         CA081016004      220081008G731010608486        HOSE                                    BOEING727   727225      1384077NM  PWA   JT8   JT8D15      52051NE                              FUEL SYSTEM     LEAKING         W      D   RETURN TO BLOCK                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING DEPARTURE OF THE ACFT PRIOR TO ENGINE START, FUEL WAS NOTICED LEAKING FROM NR 3 ENGINE.  MX REQUESTED NORMAL ENGINE START TO VERIFY FUEL LEAK.  ENGINE WAS SHUT DOWN, AND ACFT TOWED BACK TO GATE FOR FURTHER INVESTIGATION.  THE FUEL HOSE ASSEMBLY WAS R&R WITH A SERVICEABLE ASSEMBLY.  ENGINE GROUND RUN WAS CARRIED OUT AND LEAK CHECKED WITH NO FURTHER LEAKS OBSERVED.  THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                   2L73 4F4  F  A3WE    E2EA                 
             20081124     EA  2008       11         24         CA081016005      120081014G2751601R930301      TRANSMITTER                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              FLAP POSITION   FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) CLIMBING THROUGH 12000 FT AT 250 KIAS ACFT NOSED OVER AS FLAPS WENT TO AT LEAST 25 DEGREES AND AUTOPILOT KICKED OFF.  ACFT SLOWED TO 200 KIAS WHILE RETURNING TO DEPARTURE AIRPORT.  FLAPS CONTINUOUSLY CYCLED FROM 0 TO 12 DEGREES.  CIRCUIT BREAKERS 1F4 AND 2F4 WERE PULLED.  A 0 DEGREE FLAP LANDING WAS PERFORMED.  MX REPLACED THE FLAP POSITION TRANSMITTER AND THE SKEW DETECTION HARNESS PN K601R50533-3. AFTT: 27877:46, CYCLES: 23108.                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20081126     NM  2008       11         26         CA081016006      120081008G27821703911         ACTUATOR                                EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              NR 4 SLAT       MALFUNCTIONED   W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA       4135                                                           (CAN) SLAT FAIL ON APPROACH CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. T/S IAW FIM, SLAT INHIBIT CLEARED, OPS CHECK PASSED. CONSIDERED TRANSITORY CONDITION OF THE SLAT CONTROL SYS. 2 SLAT ACTUATORS REPLACED: LT SLAT ACT POS 04L REPLACED, P/N S/N AND TIMES GIVEN ABOVE. ALSO, RT NR 5 SLAT ACTUATOR REPLACED, P/N 1703909, S/N 0174, FH: 8052, FC: 3665.                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA57NM   E00070EN             
             20081126         2008       11         26         CA081016007      220081015G7414D6RN3200        MAGNETO                                                                                                                                 RT ENGINE       INOPERATIVE     W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING PREFLIGHT RUN-UP RT ENG, RT MAGNETO EXPERIENCED EXCESSIVE DROP AND WAS RUNNING ROUGH. UPON INVESTIGATION OF THE MAGNETO IT WAS FOUND THAT THE DISTRIBUTOR GEAR BUSHING HAD WORN IN THE DISTRIBUTOR BLOCK HSG CAUSING A MISS FIRING CONDITION. MAGNETO WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
             20081126     NM  2008       11         26         CA081016008      120081003G783065378786        SWITCH                                  BOEING727   7272Q6      138407VNM  PWA   JT8   JT8D17      52049NE                              THRUST REVERSER INOPERATIVE     W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB OUT, NR 3 ENGINE THRUST REVERSER OPERATING LIGHT ILLUMINATED THROUGH 5000 FT. THE ACFT RETURNED TO THE AIRPORT. THE NR3 ENG THRUST REVERSER WAS DEACTIVATED AND MEL APPLIED. UPON REACHING THE DESTINATION, THE NR3 ENGINE THRUST REVERSER SWITCH WAS REPLACED, ENGINE RUN CARRIED OUT AND THE THRUST REVERSER WAS FUNCTIONALLY CHECKED AS SERVICEABLE. THE DEFERRAL WAS CLEARED AND THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                           2L73 4F4  FRTA3WE    E2EA                 
             20081126     NM  2008       11         26         CA081016009      120081010G279719019566401     WIRE HARNESS                            EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              LE SLAT         DEFECTIVE       W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) SLAT FAIL MESSAGE ON FLAP 5 SELECTION ON APPROACH. CREW CARRIED OUT A MISSED APPROACH, QRH WAS FOLLOWED AND LANDED UNEVENTFULLY ON SECOND TRY. SLAT HARNESS REPLACED, OPS TEST CARRIED OUT IAW AMM 27-80-00-710-801A, NO FAULTS NO EICAS MESSAGES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA57NM   E00070EN             
             20081126     CE  2008       11         26         CA081016011      120081010G27201295240823      TORQUE TUBE     BEECH       1295240821  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              RUDDER CONTROL  BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       17702                                                          (CAN) RUDDER PEDALS LINKAGE (UNDER FLOOR) - LT TORQUE TUBE BROKEN JUST INBD OF THE LT RUDDER PEDAL BLOCK. RUDDER TORQUE TUBE FAILURE STARTED AT TAPER PIN HOLE USED TO SECURE THE RUDDER PEDAL ASSY BLOCK TO THE SHAFT. FAILURE APPEARS TO BE FROM AN OVERLOAD CONDITION WITH AN INITIAL CRACK AND THEN A SECONDARY CRACK AT ABOUT 90 DEGREES. A THIRD CRACK ALSO FOUND PARALLEL TO INITIAL CRACK. FAILURE OF THIS TYPE WOULD BE HARD TO PICK UP ON A VISUAL INSP AS EARLY FAILURE TAKES PLACE IN AN AREA NOT VISIBLE UNTIL UNIT IS DISMANTLED. ONCE FAILURE PROGRESSED TO COMPROMISE THE TORSION ABILITY OF THE SHAFT IT WOULD SPREAD RAPIDLY TO COMPLETE FAILURE.  COMPLETE RUDDER AND STEERING SYS WAS INSPECTED TO DETERMINE IF RELATED SYS 2L72 4T4  TRTA24CE   E26NE                
             20081124     EA  2008       11         24         CA081016012      220080925G7230                COMPRESSOR                              BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ENGINE          SEIZED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ACFT WAS EN ROUTE WHEN THE LT ENGINE LOST POWER.  THE CREW COMPLETED EMERGENCY PROCEDURES, SECURED THE ENGINE AND FEATHERED THE PROPELLER.  THEY DECLARED AN EMERGENCY AND CONTINUED TO DESTINATION, WHERE THE ACFT PERFORMED A SINGLE ENGINE LANDING.  POST FLIGHT INSPECTION REVEALED A SEIZED COMPRESSOR AND OIL FILTER CONTAMINATION.  THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION AND REPAIR.                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA24CE   E4EA                 
             20081124     NE  2008       11         24         CA081016014      220081002G7321                FUEL CONTROL                            GULSTM200   200         4500308NM  PWC   PW306 PW306A      52165NE                              ENGINE          MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) 2 TO 3 MINUTES AFTER ENGINE START, IT FLAMED OUT UNCOMMANDED.  NO FAULT CODES WERE RECORDED ON THE FADEC.  INSPECTION FOUND THE FAN FREE TO ROTATE WITH NO EVIDENCE OF INGESTION.  THE PILOT MOTORED THE ENGINE AND THEN PERFORMED AN ENGINE START.  THE BOOST PUMP AND MOTIVE FLOW WERE OPERATING NORMALLY.  THE ACFT IS SCHEDULED TO BE FLOWN TO BASE FOR MX. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA53NM   E35NE                
             20081124     NE  2008       11         24         CA081016015      220081002G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FIRE            W      EFB ENGINE SHUTDOWN         ACTIVATE FIRE EXT.      EMER. DESCENT                                   ARJFLAME/FIRE                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE PILOT SAW FLAMES COMING OUT OF THE ENGINE EXHAUST BEFORE LOSING POWER.  HE DECLARED EMERGENCY AND DIVERTED THE FLIGHT TOWARDS A NEARBY AIRPORT.  HE WAS NOT ABLE TO MAKE THE AIRPORT AND HE WAS FORCED TO LAND ON A ROAD.  THE PILOT WAS NOT INJURED AND THE ACFT SUFFERED NO DAMAGE.  THE ACFT WAS LATER TOWED TO THE AIRPORT WHERE FAA IS INVESTIGATING.  THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION.                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA                 
             20081106         2008       11         6          CA081017001      420081012G83003022375         SEAL                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ACCESSORY G/B   FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       7524 7524                                                      (CAN) PILOTS SHUT DOWN NR 1 ENGINE, DUE TO OIL PRESSURE FLUCTUATION AND OIL PRESS. ANNUNCIATOR ILLUMINATION. ACFT RETURNED TO YXS MX BASE.  OIL LOSS WAS FOUND TO BE COMING FROM THE HP PUMP DRAIN. OIL SEAL REPLACED, OIL CONSUMPTION ELIMINATED. EXPLORATORY WORK COMPLETED AS PER PRATT AND WHITNEY MX MANUAL.  ACFT RELEASED AS PER PRATT AND WHITNEY MX MANUAL PUTTING IN PLACE BOTH OIL FILTER/SCREEN AND CHIP DETECTOR INSPECTIONS.                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA24CE   E4EA                 
             20081106     EA  2008       11         6          CA081017002      120081007G61208210004         CSU                                     DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  RT ENGINE       MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA            1525                                                      (CAN) THE ACFT WAS IN CRUISE FLIGHT WHEN THE TORQUE ON THE RT ENGINE SURGED AND THE PROPELLER BEGAN TO FEATHER. AS THE POWER WAS BROUGHT BACK THE PROPELLER STOPPED FEATHERING. A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED AND THE ACFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. THE ENGINE AND ASSOCIATED SYSTEMS WERE TROUBLESHOT, WHICH DETERMINED THAT THE PROPELLER GOVERNOR WAS AT FAULT. THE GOVERNOR WAS CHANGED, A GROUND RUN AND A TEST FLIGHT WERE PERFORMED WITH NO FURTHER PROBLEMS.                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081106     NM  2008       11         6          CA081017003      120081007G5720190933321001    FAIRLEAD                                EMB   ERJ190ERJ190100IGW3260408NM                                                                               DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT WING AILERON FAIRLEAD BRACKETS. REMOVAL OF THE PLASTIC FAIRLEADS FOUND THAT THE CABLES DID NOT SIT ROUGHLY IN THE MIDDLE OF THE BRACKET HOLES. COMPARISON OF THE BRACKETS ON MSN 19000049 TO OTHER EMBRAER E190S IT WAS SUSPECTED THAT THE WRONG BRACKETS HAVE BEEN INSTALLED FROM FACTORY. PICTURES ATTACHED OF THE BRACKETS INSTALLED ON MSN 19000049 AS REFERENCE.  PER E190 SRM 57-50-00 FIGURE 45A THE CORRECT BRACKETS ARE 190-933321-001, 190-93298-001, 190-93298-001 AND 190-93318-001 (FROM IB MOST TO OB MOST BRACKETS).                                                                                                                                                                                                   2L72 4F    RTA57NM                        
             20081106     WP  2008       11         6          CA081017004      220081017G723031081822        BLADE           NORMALAIR                                                  GARRTTTPE331TPE33110UA  01514WP                              IMPELLER        DAMAGED         W      D   RETURN TO BLOCK                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       4210 4210                                                      (CAN) IT WAS NOTICED ON A GROUND RUN AFTER THE ENGINE WAS INSTALLED THAT THERE WAS A SQUEALING NOISE COMING FROM THE ENGINE. THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR EVALUATION. UPON DISASSEMBLY THE NR 1 IMPELLER WAS FOUND TO HAVE A PIECE OF THE BLADE MISSING. THE NR 1 IMPELLER HAS NO OTHER DAMAGE EXCEPT WHERE THE BLADE PIECE IS MISSING. THE NR 1 IMPELLER WILL BE FORWARDED TO A METALURGY FACILITY FOR EVALUATION TO DETERMINE WHY THE BLADE PIECE BROKE OFF. THERE WAS SUBSTANTIAL DAMAGE TO THE ENGINE FROM THE IMPELLER BLADE PIECE.                                                                                                                                                                                4  T          E4WE                 
             20081106     EA  2008       11         6          CA081017005      120081017G2910AE4760H0592055  LINE                                    CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF343A2     30067NE                              NR 2 EDP        BURST           W      O   OTHER                                                                                           KS FLUID LOSS                AFFECT SYSTEMS                                      CRCRUISE         1                      CA                                                                      (CAN) AFTER TAKEOFF IN CRUISE AND ON THE WAY NR 2 HYD PRESS LOST MASTER CAUTION ON REPORT BY THE CAPTAIN, HE STILL HAD HIS NR 1 AND NR 3 HYD SYSTEM. ACFT LANDED SAFELY WITHOUT ANY EMERGENCY REQUEST. NR 2 ENGINE HYD PUMP OUTLET LINE FOUND BUSTED, LINE REPLACED.  NR 2 HYD PUMP CHANGED AS MTCE PREVENTIVE AND NR 2 HYD FILTER CHECKED FOR FOD. NOTHING WAS FOUND.                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
             20081106     SW  2008       11         6          CA081017006      120080925G5302214001920101    HORN                                    BELL  214   214B1       1182105SW  LYC   T55   T5508D      41555NE                              ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2034                                                           (CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SENT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2G71 4U4  U  H6SW    E4NE                 
             20081106     GL  2008       11         6          CA081017007      220081017G732323065123        GOVERNOR                                BELL  206   206L        1181522SW  ALLSN 250C  250C20R2         GL                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1683                                                      (CAN) UPON REMOVAL OF THE GOVERNOR IT WAS NOTED THAT THE DRIVE GEAR HAD COME SEPARATED. ALL PARTS WERE FOUND IN THE DRIVE GEAR FOR THE GOVERNOR. THERE WAS DIFFICULTY GETTING FULL RANGE OF THE GOVERNOR, COULD NOT ADJUST FOR 100 PERCENT ON THE GROUND. THE DRIVE GEAR USUALLY HAS A BONDING MATERIAL ON THE END OF THE WASHERS THAT WAS NO LONGER THERE. THE GOVERNOR WAS CHANGED AND FUNCTIONALLY CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
             20081106     SW  2008       11         6          CA081017008      120081003G5302204032806079A   LONGERON                                BELL  204   204B        1181404SW  LYC   T53   T5311B      41549NE                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES AFT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 4U4  U  H1SW    E1EA                 
             20081106     CE  2008       11         6          CA081020001      120081003G5551                MOUNT                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              RUDDER CONTROL  MISINSTALLED    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) METAL FILINGS WERE FOUND UNDER THE RUDDER SERVO DUE TO THE MOUNTING STRUCTURE HAVING BEEN INSTALLED OFFSET FROM THE FACTORY. THIS CAUSED THE RUDDER CABLE TO EXIT THE DRUM ON AN ANGLE AND RUB THE CAPSTAN. THE SERVO WAS REPLACED AND A PERMANENT FIX IS SCHEDULED FOR MAR. 09 AT CESSNA CITATION SERVICE CENTER.  PICTURES ARE AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                               1L72 4F4  FRTA1WI    E3GL                 
             20081106     CE  2008       11         6          CA081020002      120081011G3213                TORQUE LINK                             BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6035                                                           (CAN) DURING REGULAR MX, A MECHANIC NOTICED A CRACK ON THE UPPER TORQUE LINK OF THE LT MLG. THE TORQUE LINK WAS REPLACED AND ACFT RETURNED TO SERVICE. THE RT MLG TORQUE LINKS WERE INSPECTED WITH NO FAULTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  T  A14CE   E4EA                 
             20081106     CE  2008       11         6          CA081020003      120081019G8011MMU6001         STARTER                                 CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  ENGINE          BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) SNAG REPORTED THAT ACFT WOULD NOT START. UPON INVESTIGATING IT WAS NOTED THAT THE STARTER HOUSING WHERE IT ATTACHES TO ENGINE WAS BROKEN. ALSO NOTED THAT THE BENDIX DRIVE TEETH WERE MISSING/SHEARED OFF. ENGINE CASE INSPECTED FOR DAMAGE, NONE FOUND NEW STARTER INSTALLED AND FUNCTION CHECKED SERVICEABLE. A CHECK ON STARTER SOLENOID SHOWED NO FAULTS.  SUSPECT STARTER WAS RE-ENGAGED BY PILOT AFTER ENGINE WAS RUNNING.                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A19    E223    5  NP50GL    
             20081222     EU  2008       12         22         CA081020004      120081002G6720350A21136324    BRACKET                                 SNIAS 350   AS350*             EU                                                               TAIL ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) A US OPERATOR HAS REPORTED 7 CASES OF THE RT TAIL ROTOR BELLCRANK MOUNTING BRACKET CRACKING.  ALL THESE ACFT HAVE LIMITED LT PILOT MODIFICATION STC SH96-32 (FAA STC SR00429NY).  LIMITED HAS ISSUED A SB ECL-122 REQUIRING AN INSP BEFORE NEXT FLIGHT REPEATED AT 50 HOURS THEN EVERY 100 HOURS.                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U      H9EU                         
             20081106     GL  2008       11         6          CA081020005      320081017G6114HCD4N3C         SEAL                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  PROPELLER       WORN            W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            3135                                                      (CAN) DURING WALK AROUND, RT PROPELLER NOTED TO HAVE OIL DRIPPING FORM THE BLADE FACES. SOME OIL WAS NOTED TO BE ON THE UPPER ENGINE COWL, HOWEVER THE REST OF THE ENGINE WAS DRY. PROP SPINNER WAS REMOVED, INSIDE OF SPINNER WAS DRY AS WELL. GROUND RUN CARRIED OUT WITH SPINNER REMOVED, AND OIL WAS NOTED TO BE LEAKING FROM THE FRONT OF THE PROP CYLINDER, THE PROP HAD TO BE EXERCISED FROM REVERSE, FINE PITCH AND FEATHER TO GET IT TO SHOW ANY LEAKAGE, THE LEAK WAS COMING FROM THE PITCH CHANGE ROD AND REVERSE ADJUST LEVER, THE MAJORITY OF THE OIL LEAKAGE ENDED UP ON THE BLADES ONLY, THE CYLINDER DID NOT SHOW VERY MUCH OIL LEAKAGE AT ALL, THE OIL SEEMED TO JUST SLING OUT ONTO THE BLADES AND A LITTLE BIT ON THE UPPER C1L72 3T4  T  A14CE   E4EA    5  CSTC      
             20081106     SW  2008       11         6          CA081020006      120081019G3230KRP5064         BEARING                                 FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  MLG             DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) UPON TAKEOFF THE CREW REPORTED THAT THE RT GEAR WOULD NOT REMAIN LOCKED. ACFT RETURNED TO BASE AND UPON MX INSPECTION IT WAS FOUND THAT THE UP-LOCK HOOK BEARING AND ATTACHING HARDWARE WERE MISSING. IT WAS ALSO NOTED THAT THE UP-LOCK HOOK SHAFT ATTACH POINTS HAD BEEN MARRED. THIS LEADS US TO BELIEVE THAT THE BEARING WAS INSTALLED AND EITHER THE BEARING OR BOLT FAILED. FAILED PARTS WERE REPLACED - GEAR SWINGS CARRIED OUT AND ACFT RETURNED SERVICE.                                                                                                                                                                                                                                                                         2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081106         2008       11         6          CA081020007      420081019G23303042865102      ELECTRICAL BOX                          BOEING737   737*               NM  GE    CFM56 CFM567B24        NE                              SEAT ROW 16ABC  ODOR            W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) FLIGHT ATTENDANTS NOTICED ELECTRICAL ODOR AT ROW 16 AND SHORTLY AFTER THE ROW 16ABC MALFUNCTIONED. LIVETV SYSTEM SHUT OFF IN FLIGHT DECK AND FLIGHT ATTENDANT STATION. THE SEB P/N 3042865-102 S/N 1792 WAS REMOVED. THIS SDR WILL BE UPDATED WHEN SEB TEARDOWN INFORMATION IS AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA16WE   E00055EN             
             20081219     SW  2008       12         19         CA081020008      120081009G56102621126005      WINDSHIELD                              SWRNGNSA226 SA226T      8780122SW  GARRTTTPE331TPE3311     01514WP                              COCKPIT         CRACKED         W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA            177                                                       (CAN) DURING CRUISE FLIGHT THE LT COCKPIT WINDSHIELD GLASS CRACKED WITH AN EXPLOSIVE BANG.  THE CREW IMMEDIATELY DESCENDED AND REDUCED CABIN PRESSURE TO AVOID THE POSSIBILITY OF THE WINDOW GLASS BLOWING OUT.  THE WINDOW WAS INSTALLED ON APRIL 11, 2006 AND HAD A TOTAL OF 177 HOURS SINCE OVERHAUL AND INSTALLATION.  THE ACFT WAS IN THE USA AT THE TIME OF THE OCCURRENCE AND THE ACFT WAS FLOWN TO ITS INTENDED DESTINATION AS IT WAS ONLY ABOUT 30 MINUTES FROM THE DESTINATION AT THE TIME OF OCCURRENCE.  THE WINDOW WAS REPLACED BY APPROPRIATELY RATED FAA REPAIR STATION.  THE WINDOW WILL BE SENT TO THE MANUFACTURER FOR WARRANTY AND EXAMINATION.                                                                              2L72 4T3  TRTA5SW    E3WE                 
             20081229     SW  2008       12         29         CA081020009      120081007G3244196K089         TIRE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33110U   29066NE  MCAULY4HFR344HFR34C652  NE  MLG             SEPARATED       W      O   OTHER                                                                                           C  F.O.D.                                                                        TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING GROUND HANDLING PROCEDURES THE NR2 MAIN WHEEL WAS FOUND TO BE SHREDDED AND THE TREAD PORTION OF THE TIRE MISSING. THIS TIRE WAS A RECAPPED TIRE RECEIVED FROM A CERTIFIED FAA REPAIR STATION.  THE TIRE WHEN IT SHREDDED CAUSED DAMAGE TO THE ACFT FLAP AND SURROUNDING WW WHICH REQUIRED REPLACEMENT OF THE FLAP AND REPAIR OF THE WW AREA.  MAINT REPAIRED THE ACFT AND REPLACED THE TIRE.                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081106     SO  2008       11         6          CA081020010      120081015G7930                FITTING                                 PIPER PA31T PA31T2      7103127SO  PWA   PT6   PT6A135     52043NE  HARTZLHCB3T HCB3TN3     GL  OIL PRESS LINE  FAILED          W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       59                                                             (CAN) DURING TAXIING OF THE ACFT, THE CREW NOTED THE ANNUNCIATOR FOR OIL PRESSURE ON THE LT ENGINE CAME ON. THEY SHUTDOWN THE LT ENGINE AND TAXIED THE ACFT USING 1 ENGINE BACK TO THE HANGER. AFTER INSPECTION, IT WAS FOUND THAT THE HOSE ASSEMBLY FROM THE ENGINE OIL COOLER TO THE ENGINE HAD FAILED AND WAS LEAKING ENGINE OIL FROM WHERE THE HOSE IS SECURED INTO THE FITTING ASSEMBLY ON THE HOSE ASSEMBLY. THE HOSE ASSEMBLY WAS REPLACED WITH A NEW HOSE ASSEMBLY. THE ENGINE CHIP DETECTOR AND ENGINE FILTER WAS INSPECTED WITH NO FAULTS FOUND. THE WAS SERVICED WITH OIL AND SATISFACTORY OPS AND LEAK CHECKS WHERE CARRIED OUT WITH NO FAULTS FOUND. THE HOSE ASSEMBLY WAS REPLACED PRIOR BECAUSE THE HOSE ASSEMBLY TIME LIMIT WAS 1L72 3T4  TRTA8EA    E4EA    6  CP15EA    
             20081107     WP  2008       11         7          CA081020011      120081016G7714                TACHOMETER                              ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) DURING DESCENT FROM ALTITUDE TO BEGIN LOW LEVEL FLIGHT FOR PIPE LINE SURVEILLANCE AT APPROX. 75 KNOTS INDICATED AIRSPEED AND VSI AT APPROX. 500 FPM, THE ENGINE RPM TACH INDICATED ENGINE OVERSPEED WELL ABOVE 110%. ALL OTHER ENGINE PARAMETERS REGISTERED WITHIN LIMITS, INCLUDING THE ROTOR RPM TACH. NO WARNING OR CAUTION LIGHTS.  THE THROTTLE WAS LOWERED TO MAINTAIN NR RPM WHEN LOW ROTOR RPM HORN SOUNDED.  A POWER ON LANDING PERFORMED WHILE ATTEMPTING TO MAINTAIN ENGINE TACH INDICATING WITHIN LIMITS. LOW ROTOR HORN SOUNDED REPEATEDLY DURING DESCENT WHILE ENGINE TACH INDICATED OVER 102%.  20 MINUTES INTO THE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE TO A HIGHER FREQUENCY, BUT NO ABNORMALITIES FOUND ON1G71 3O3  O  H11NM   1E4                  
             20081107     NE  2008       11         7          CA081020012      220081019G8530                VALVE                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          STUCK           W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA                                                                      (CAN) DURING STRAIGHT AND LEVEL CRUISE FLIGHT, THE PILOT NOTICED A SUDDEN INCREASE IN VIBRATION, THOUGHT TO BE COMING FROM THE ENGINE, AND AN INCREASE IN MANIFOLD PRESSURE. HE OPTED TO TURN AROUND AND LAND AT A NEARBY CAMP. DURING HIS DESCENT, THE VIBRATION STOPPED AND ENGINE PERFORMANCE RETURNED TO NORMAL. A COMPRESSION CHECK WAS FOUND NORMAL ON ALL CYLINDERS. A WIGGLE CHECK ON THE EXHAUST VALVES WAS FOUND SATISFACTORY, HOWEVER, 1 OF THE VALVES WAS AT 0.014 WHILE ALL THE OTHERS WERE AT 0.020 OR BETTER. IT IS SUSPECTED THAT THIS EXHAUST VALVE BECAME STUCK AND THEN CAME FREE AGAIN.                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081107     CE  2008       11         7          CA081021001      120081001G3220NAS150A48       BOLT            BEECH                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  NLG             LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BOLT WAS FOUND LOOSE ON RT SIDE OF NLG. THE COTTER PIN AND NUT WERE MISSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
             20081107     NM  2008       11         7          CA081021002      120081018G3260401020101       SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG DOOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4571                                                           (CAN) ON INSPECTION FOUND NOSE GEAR DOOR CLOSED SENSOR CRACKED. SENSOR REPLACED IAW AMM 32-61-06-04                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E00062EN             
             20081107         2008       11         7          CA081021003      420081019G312049712631        PRINTER                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              ACARS           SMOKE           W      G   O2 MASK DEPLOYED                                                                                B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA       5044 5044                                                      (CAN) DURING DESCENT TO YOW, CREW NOTICED SMOKE COMING FROM THE ACARS PRINTER, ELECTRICAL CIRCUIT BREAKER POPPED AND SMOKE STOPPED. NO EMERGENCY DECLARED AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. ACARS PRINTER DIFFERED IAW MEL 23-22-0 AND CIRCUIT BREAKER SECURED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
             20081107     NM  2008       11         7          CA081021004      120081019G3260                SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG DOOR        OUT OF RIG      W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) NOSE GEAR DOOR LIGHT FLICKERING ON AND OFF IN FLIGHT.  RIGGED NOSE GEAR DOOR PROXIMITY SENSOR IAW AMM 32-61-06. CYCLED NOSE GEAR DOORS AND NO OTHER FAULTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E00062EN             
             20081107     GL  2008       11         7          CA081021005      220081020G732323065121        GOVERNOR                                HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA            1329                                                      (CAN) PILOT REPORTED ROTOR SPEED HUNTING IN CRUISE SO THE GOVERNOR WAS REMOVED TO CLEAN THE ORIFICES. ONCE REMOVED IT WAS NOTICED THAT THE EPOXY BOND ON THE END OF THE DRIVESHAFT WAS MISSING AND THE SPLINE DRIVE WAS LOOSE ON THE GOVERNOR DRIVESHAFT. IF LEFT THIS WOULD LIKELY TURN INTO WHAT WAS REPORTED IN SDR 20071015004 AND COULD LEAD TO AN ENGINE DECEL OR SHUT DOWN.                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
             20081107     EU  2008       11         7          CA081021006      120081020G2730258CT29115A     JACKSCREW       HAWKER                  BRAERODH125 BAE125800A  1500285EU  GARRTTTFE731TFE7315R    01518WP                              TRIM ACTUATOR   FROZEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8137                                                           (CAN) CREW REPORT THE ELEVATOR TRIM WAS DIFFICULT TO MOVE IN FLIGHT. UPON INSPECTION BY MX IT WAS FOUND THE ACTUATOR WAS CORRODED INTERNALLY AND THE GREASE WAS CONTAMINATED AND HARDENED. HAWKER BEECHCRAFT ALREADY HAS SB 27-3840 R1 TO CHECK FOR THIS SAME ISSUE WITH THESE ACTUATORS. BOTH LT AND RT ACTUATORS WERE REPLACED DUE TO THIS ISSUE AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA3EU    E6WE                 
             20081107     NM  2008       11         7          CA081021007      120081017G792128E997          OIL COOLER                              DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE                              NR 1 ENGINE     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) NR 1 ENGINE OIL PRESSURE BELOW 40 PSI. NR 1 ENGINE SHUT DOWN IN FLIGHT. AFTER THE ACFT RETURNED TO BASE IT WAS FOUND AN OIL LEAK FROM THE NR 1 ENGINE OIL COOLER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE                
             20081107     CE  2008       11         7          CA081022001      120081021G5343AN35A           BOLT            CESSNA                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              MLG TRUNNION    WRONG PART      W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) CARRY OUT INSPECTION AS PER CAMPAIGN 851-53-11-047 CESSNA 550 CHANNEL-TRUNION BRACE.  FOUND INCORRECT HARDWARE INSTALLED.  NO VISUAL DAMAGE TO STEERING ARM.  REPLACED HARDWARE AS PER CAMPAIGN.  NO RESTRICTED TRAVEL FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
             20081107     NM  2008       11         7          CA081022002      120081014G324014209114        CONTROL MODULE                          EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              RT BRAKES       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA       3089                                                           (CAN) AFTER LANDING, DURING DECELERATION ON RUNWAY AT APPROX 80 KTS, LT AND RT BRAKE FAULT MSG APPEARED ON EICAS ACCOMPANIED BY COMPLETE LOSS OF BRAKING. AFTER APPROX 8 SECONDS BRAKING RETURNED TO NORMAL AND EICAS MSG DISAPPEARED. SERVICE NEWS LETTER SNL190-32-0023R00 IS RELATED NO MX MSG CORRELATION WITH LT AND RT BRAKE MSG. IN CMC MX MSG HISTORY OF OCT 14 LEG 3 FOUND MSG: "MAU2 BCM2/MAU2 NWSCM" CODE 32533301NWS. PER FIM 32-53-00-810-813-A00, BCM2 WAS REPLACED PER MM                                                                                                                                                                                                                                                        2L72 4F4  FRTA57NM   E00070EN             
             20081230     CE  2008       12         30         CA081022003      120081020G5240H1721050100     LATCH                                   LEAR  35    31A         5170531CE  GARRTTTFE731TFE73123B        WP                              SERVICE DOOR    UNSERVICEABLE   W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              DEDESCENT        1                      CA                                                                      (CAN) SINGLE POINT FUEL DOOR LATCH OPENED IN FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA10CE   E6WE                 
             20081107     EU  2008       11         7          CA081022004      120081015G2421200322          GENERATOR                               AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  NR 1            FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE NR 1 A/C WILD GENERATOR WENT OFF LINE. MX INSPECTED AND FOUND NR 1 AC WILD GENERATOR HAD FAILED INTERNALLY WITH SMALL SCREWS, WASHERS, ETC LAYING ON OUTLET COOLING SCREEN. TSO UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20081107     NM  2008       11         7          CA081022005      120081021G3260401020101       PROXIMITY SENSOR                        DHAV  DHC8  DHC8*              NM  PWC   150   PW150A           EA                              RT MLG          OUT OF RIG      W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) RT MLG FAILED TO RETRACT NORMAL, AMBER DOOR LIGHT, HANDLE LIGHT AND RED DISAGREEMENT LIGHT ILLUMINATED.  RT MLG PROXIMITY SENSOR FOR UPLOCK INDICATION RIGGED AS PER AMM 32-61-06-400-802. GAP SET TO .045, MH 8.621                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN             
             20081107     WP  2008       11         7          CA081022006      220081019G7261                CARBON SEAL                             DORNERDO228 DO228202    2992030EU  GARRTTTPE331TPE3315     01514WP                              NR 1 ENGINE     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) NR 1 ENGINE CREW SHUT DOWN DUE TO STEADY DROP OF OIL PRESSURE AND TORQUE FLUCTUATION, BELIEVED LATER THAT THE REAR CARBON SEAL BEGAN TO LEAK THUS INGESTION OIL IN ENGINE AND BURNT. ENGINE REMOVED FROM ACFT TO BE SENT FOR FURTHER TESTING AT ENGINE SHOP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA16EU   E4WE                 
             20081230     GL  2008       12         30         CA081022008      120081021G2710AN2412          CLEVIS BOLT                             DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD22D   22D30       NE  CONTROL CABLE   WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AN AILERON CABLE (IN WING) REPLACEMENT THE CLEVIS BOLTS WERE FOUND TO BE WORN MORE THAT 30 PERCENT, REPLACED WITH NEW AN 24-12 CLEVIS BOLTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R3  RRCA806    5E1     5  CP736     
             20081107     NE  2008       11         7          CA081022009      220081007G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              DAMAGED         W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE PILOT HEARD AN UNUSUAL NOISE FROM THE ENGINE FOLLOWED BY A DECREASE IN COMPRESSOR TURBINE SPEED. THE PILOT RETURNED TO HIS POINT OF DEPARTURE WHERE AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS NOT SHUT DOWN AND THE EMERGENCY POWER LEVER WAS NOT USED. THE ENGINE HAS BEEN SENT TO REPAIR STATION FOR INVESTIGATION, MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                1H71 3T3  T  A37CE   E4EA                 
             20081230     CE  2008       12         30         CA081022010      120081002G2752503801537       DRIVE ASSY      BEECH                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  FLAP ACTUATOR   SHEARED         W      L   ABORTED APPROACH                                                                                F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE FLAPS WERE SELECTED TO 17 DEG BUT FAILED TO EXTEND PAST 10 DEG. THE FLIGHT CREW INITIATED AN OVERSHOOT TO TROUBLESHOOT THE PROBLEM, THEY WERE UNABLE TO FIX THE BROKEN FLAPS AND RETURNED TO BASE. MX REPLACED THE FLAP DRIVE AND NO FURTHER FAULTS WITH SYS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
             20081230     NM  2008       12         30         CA081023001      120081023G2710                BEARING                                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  CABLE PULLEY    SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING FLAP INSP, AN ENGINEER FOUND AN AILERON PULLEY INSIDE THE WING BOX SEIZED.  FURTHER INVESTIGATION REVEALED THE ADJACENT PULLEY WAS ALSO CORRODED.  BOTH PULLEYS WERE REPLACED AND THE ACFT RETURNED TO SERVICE. 1915 HRS WERE REMAINING BEFORE COMPLETION OF TASK 2710/02 (11000 HRS).                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     NM  2008       12         30         CA081023002      120081013G291019071270901     RESTRICTOR VALVE                        EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              HYDRAULIC SYS   CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) HYD LEAK 10 DPM ON SYS NR2 RETURN LINE AND UNION FREE FALL SELECTOR VALVE RT WW AREA. WRENCH CHECK NIL FIX. FOUND RESTRICTOR VALVE CRACKED ON EMERGENCY EXTENSION SELECTOR VALVE. RESTRICTOR VALVE REPLACED, BUT STILL HAD A LEAK. UPON CLOSE INSP, FOUND A VERTICAL CRACK IN THE THREADED PORTION OF THE VALVE UNDER THE B-NUT (BOTH RESTRICTOR VALVES). THESE FINDINGS RAISED THE CONCERNS OF ATTACHING A STAINLESS STEEL LINE AND B-NUT TO THE LIGHTER ALUMINUM RESTRICTOR VALVE. A 1.1250 IN WRENCH IS REQUIRED TO TIGHTEN THE "B" NUT. NOTE, WE ALSO REPLACED THE HYD LINE ASSY.                                                                                                                                                     2L72 4F4  FRTA57NM   E00070EN             
             20081107     NM  2008       11         7          CA081023003      120081019G279719019564401     WIRE HARNESS                            EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              SLAT SYSTEM     DAMAGED         W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ON FLAP RETRACTION AFTER T/O. SLAT FAIL EICAS MSG DISPLAYED. CARRIED OUT QRH FOR SLAT FAIL. DID NOT RECTIFY PROBLEM. ACFT RETURNED RT SLAT SKEW SENSOR HARNESS W611 REPLACED AS PER AMM 27-83-07 PB 401, RT SLAT 2/3 SKEW SENSOR  REPLACED AS PER AMM 27-83-01 PB- 401.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA57NM   E00070EN             
             20081230     NE  2008       12         30         CA081023004      120081016G792228E251          THERMOSTAT                              SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              NR 2  OIL COOLERUNSERVICEABLE   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP 8 EXCEEDED RED LINE LIMIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G72 3U3  U  H1NE    E1GL                 
             20081222     SW  2008       12         22         CA081023005      120080727G5302205032807003    FITTING                                 BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED A CRACK INDCATION OF 1.5 INCHES LONG IN THE FITTING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 4U4  U  H1SW    E17EA                
             20081222     SO  2008       12         22         CA081024001      120081024G53436705403         TRUNNION                                PIPER PA32  PA32R300    7103213SO  LYC   0540  IO540K1G5D  41532SO  HARTZLHCC3Y HCC3YR      GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4771                                                           (CAN) FOUND GREASE LEAKING FROM TOP PORTION OF THE LWR BRG SUPPORT. CLEANED AREA AND RE GREASED TRUNNION. GREASE WAS FOUND COMING OUT OF CRACK. THE CRACK IS APPROXIMATELY ONE INCH LONG, HORIZONTAL. THIS CRACK INDICATION DOES APPEAR TO BE CAUSED BY IMPROPER GROUND HANDLING. STEPS ARE BEING TAKEN TO REPLACE PART AT THIS TIME.                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  A3SO    1E4     5  CP25EA    
             20081230     NE  2008       12         30         CA081024002      120081021G29109265004900101   HEAT EXCHANGER                          SKRSKYS92   S92A               NE  GE    CT7TS CT78A       30136NE                              HYD SYSTEM      CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) ENROUTE AT 7000 FT, ACFT STARTED TO NOD UNCHARACTERISTICALLY. IT WAS NOTED THAT THE NR 1 HYD SYS PRESSURE WAS HIGH (IN THE RED). DECISION TO RETURN MADE AND NR 1 HYD SYS DE-SELECTED BUT PRESSURE REMAINED HIGH. NO OTHER ADVISORY/CAUTION LIGHTS WERE ON AT THIS POINT. ABOUT 10 MINUTES AWAY FROM DESTINATION, PRESSURE DROPPED AND "HYD NR 1 RESEV LOW" LIGHT CAME ON FOLLOWED BY M/R AND T/R SERVO NR 1 PRESS, HYD NR 1 PUMP FAIL, PSAS PRESS AND AUTO-PILOT FAIL LIGHTS. EMERGENCY CHECKLIST CONSULTED AND CARRIED OUT.  ACFT LANDED AND SHUTDOWN WITH NO FURTHER INCIDENT.  PAX WERE BRIEFED IN-FLT AND AT SHUTDOWN. THE HYD NR 1 SIDE OF THE RT HEAT EXCHANGER FOUND TO HAVE CRACK AT BOTTOM OF HSG. NR 1 HYD SYS DRAINED OUT ALL 2G72 4U4  U  R00024BOE8NE                 
             20081107     WP  2008       11         7          CA081024003      120081015G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INOPERATIVE     W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       413                                                            (CAN) STARTER GEN WOULD NOT ENGAGE ENGINE, REPLACED WITH SERVICEABLE STARTER GEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
             20081107     WP  2008       11         7          CA081024004      120081011G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              PILOT VALVE     LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA       1690                                                           (CAN) SERVO LEAKING FROM PILOT VALVE                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081107     WP  2008       11         7          CA081024005      120081011G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              PILOT VALVE     LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) SERVO LEAKING FROM PILOT VALVE                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081230         2008       12         30         CA081024006      420081010G2216                GROUND WIRE                             LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              TRIM SYS        OPEN            W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) ON LANDING, A WHITE CAS MESSAGE (SECONDARY TRIM FAULT) APPEARED. SYS TROUBLESHOT AND FOUND AN OPEN GROUND WIRE AT RBA0664N-22 AT SPLICESP322. SPLICE REPAIRED AND FUNCTION CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTT00008WIE6WE                 
             20081107     NE  2008       11         7          CA081025001      220081024G7530BRH10211MS3215  PIN                                     BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              LINKAGE         MISSING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       10795                                                          (CAN) ON 26 SEPT, ENGINE RECORDED 73-2138, BBV/FMU MECHANICAL FAULT. BVV AND FMU WAS CHANGED. ENGINE GOOD FOR 2 FLIGHTS BEFORE ENG SYS FAIL CAME BACK INFLIGHT FOR THE SAME FAULT. ACFT DIVERTED, OPERATOR REPORTS PROBLEMS WITH THE BVV LINKAGE THAT CANNOT BE CORRECTED ONWING. ENGINE WAS REMOVED IN UNSERVICEABLE CONDITION DUE TO BOOSTER BLEED VALVE MECHANISM MALFUNCTION. IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENGINE AT ROLLS ROYCE CANADA FOR REPAIR TO DETERMINE THE ROOT CAUSE OF MECHANISM MALFUNCTION. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER BLEED VALVE MECHANISM AND IT WAS NOTED THAT PIN AND RETAINING RING WERE MISSING.  THIS PIN IS THE JUNCTION BETWEEN THE BELL CRANK LEVER 2L72 4F4  FTRA6WE    E00061EN             
             20081107     NE  2008       11         7          CA081025002      220081010G7320251818          BRACKET                                 BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              ENGINE          BROKEN          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA            22738                                                     (CAN) ENGINE AUTO IFSD, ACFT DIVERTED TO ATL UNEVENTFUL LANDING. FSO CABLE RELEASE, PIECES FOUND IN THE TAILPIPE. LPT3 SCUFFED AND NICKED CONSISTENT WITH CABLE DAMAGE. NO EVIDENCE OF A TURBINE FAILURE. LP SYSTEM FREE TO TURN SMOOTHLY. ENGINE IN RRC FOR INVESTIGATION. FURTHER DETAIL WILL BE SUBMITTED.                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FTRA6WE    E00061EN             
             20081107     CE  2008       11         7          CA081027001      120081023G61208930861         SHAFT                                   MTSBSIMU2   MU2B36      5780412CE  GARRTTTPE331TPE33110    01514WP  HARTZLHCB3T HCB3TN5     GL  PROPELLER       BINDING         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA       255085965                                                      (CAN) PROP OVERSEED DURING DESCENT. FOUND ENGINE INNER CONCENTRIC SHAFT TO BE BINDING ON OUTER CONCENTRIC SHAFT. AS POWER LEVER IS RETARDED, INNER CONCENTRIC SHAFT ROTATES SLIGHTLY CLOCKWISE INCREASING PROP GOVERNOR HIGH SETTING. THERE IS NO PROVISION FOR LUBRICATION IN THIS AREA AND IT ONLY RELIES ON SPRING FORCE TO RETURN THE PROP GOVERNOR TO A LOWER SETTING. INNER SHAFT REMOVED, CLEANED, LUBRICATED AND REINSTALLED                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA10SW   E4WE    6  CP15EA    
             20081230     EA  2008       12         30         CA081027002      120080910G243523048016        STARTER GEN                             DHAV  DHC3  DHC3        2800202EA  PWA   PT6   PT6A135     52043NE  HARTZLHCB3T HCB3TN3     GL                  WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            612                                                       (CAN) STARTER GEN HAD LONG LIFE BRUSHES INSTALLED AT OVERHAUL. BRUSHES ONLY LASTED 611.5 HRS WHEN THEY SHOULD HAVE WENT THEIR 1200 HOURS. ONE BRUSH WAS RT AT THE LIMIT WHERE THE OTHER BRUSH WAS ABOUT 40 PERCENT WORN ONLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3R4  T  A815    E4EA    6  CP15EA    
             20081230     EA  2008       12         30         CA081027003      220081025G7321                SHAFT                                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  FCU THROTTLE    STIFF           W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       2888                                                           (CAN) UPON APPROACH, THE LT ENG PWR LEVER WAS RETARDED WITH NO EFFECT ON ENG. THE ENG REMAINED AT 91 PERCENT NG. THE APPROACH WAS ABORTED AND THE ACFT DIVERTED. ON ARRIVAL, AN EMERGENCY WAS DECLARED AND THE LT WAS SHUTDOWN IN ORDER TO CARRY OUT THE LANDING. MX INVESTIGATION DETERMINED THE INPUT SHAFT ON THE FCU WAS VERY STIFF, THE FCU WAS REPLACED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  T  A14CE   E4EA    5  CSTC      
             20081222     EA  2008       12         22         CA081027004      120081024G5280491184          BRACKET                                 CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              RT MLG DOOR     LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INBD MLG RT DOOR ATTACHMENT BRACKET ON STRUT FOUND LOOSE DURING HEAVY MAINT VISIT.  REFERENCE: CMM 32-11-05, FIGURE 1, PAGE 1019, ITEM 290.  IT IS WORTH NOTING THAT THIS IS THE 2ND TIME, IN THE MONTH OF OCTOBER 2008, THAT THIS ISSUE HAS BEEN RAISED. PREVIOUSLY, A MAINT IRREGULARITY REPORT SUBMITTAL, DATED 03 OCTOBER 2008, REVEALED THAT THE SAME PROBLEM WAS FOUND. NO SDR RAISED FOR THIS ONE.                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E00063EN             
             20081229     CE  2008       12         29         CA081027005      120081022G3233ADI79990038     FORK                        ADI7999003  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  ACTUATOR        BROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, RT MLG FAILED TO RETRACT.  GEAR WAS CYCLED WITH NO SUCCESS.  GEAR WAS RETURNED TO DOWN POSITION AND THERE WERE 3 GREEN LIGHTS. DISPATCH AND MX WERE CONTACTED AND IT WAS DECIDED TO RETURN TO BASE.  LANDING WAS UNEVENTFUL. UPON INSP BY MX, THE RT MLG ACTUATOR FORK END THAT ATTACHES TO THE UPPER DRAG BRACE WAS SHEARED OFF, HOWEVER THE DOWNLOCK WAS STILL IN PLACE. IT LOOKED LIKE THE FORK END HAD DEVELOPED A FATIGUE CRACK AND FINALLY LET GO JUST ABOVE THE LOCK NUT THAT HOLDS THE FORK END IN PLACE ON THE ACTUATOR. THE FORK END, AND TAB WASHER WERE REPLACED WITH NEW PARTS. CYCLES OR HRS ON BROKEN FORK END IS UNKNOWN. THE GEAR WAS INSPECTED FURTHER AND NO OTHER DEFECTS FO1L72 4T4  T  A24CE   E4EA    5  CSTC      
             20081230     EU  2008       12         30         CA081027006      120081023G2130                BUTTERFLY VALVE                         AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  CABIN PRESSURE  STICKING        W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) FOLLOWING DEPARTURE, THE ACFT FAILED TO PRESSURIZE IN AUTO OR MANUAL MODE. THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.  THE GROUND AIR CONNECTION CHECK VALVE WAS FOUND TO BE STUCK IN THE OPEN POSITION.  MAINT CLEANED AND LUBRICATED THE VALVE TO RESTORE PROPER FUNCTION.  THE SYS WAS GROUND CHECKED SERVICEABLE AND THE ACFT RETURNED TO SERVICE WITH NO FURTHER PROBLEM REPORTED.                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20081230     CE  2008       12         30         CA081028001      120081001G249770002405D       CIRCUIT BREAKER                         CESSNA680   680CE       2076811CE  PWC   PW306 PW306C      52169NE                              LT POWER FEED   TRIPPED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       81                                                             (CAN) LT POWER FEED CIRCUIT BREAKER (1 OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW.  NOTE: THIS C/B WAS REPLACED AT 261 HRS. AND AGAIN AT 342 HRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRCT00012WIE35NE                
             20081222     SW  2008       12         22         CA081028003      120081024G6320407040035101    BEVEL GEAR      BELL                    BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              TRANSMISSION    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6089 1122                                                      (CAN) TRANSMISSION CHIP LIGHT ILLUMINATED. MECHANIC FOUND SMALL DEBRIS ON THE LWR CHIP PLUG. UPON INSP BY THE OVERAUL SHOP, THEY DISCOVERED THE BEVEL GEAR DAMAGED. A SMALL PIECE OF GEAR TOOTH APPROX. .360X.073 HAD BROKEN OFF THE GEAR ASSY AND DISCOVERED THE BEVEL GEAR CRACKED AT THE DAMAGED GEAR TOOTH ARED.                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  UO H2SW    E1GL                 
             20081230     GL  2008       12         30         CA081028004      120081021G27202227271200      TUBE                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  RUDDER CONTROL  WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1742                                                           (CAN) DURING ROUTINE INSP/OPS CHAEK IT WAS FOUND THAT THE S-TUBE WHICH ALLOWS FOR THE POSITIONING OF THE RUDDER PEDAL ON THE PILOTS RT SIDE, HAD WORN THE CABLE TO THE POINT OF FINDING A FEW BROKEN CABLE STRANDS. THE RUDDER CABLES WERE ONLY DUE FOR REPLACEMENT AT 3000 HRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081230     WP  2008       12         30         CA081028005      120081022G243514924HTH        STARTER GEN                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          DISENGAGED      W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       201                                                            (CAN) STARTER WOULD NOT ENGAGE THE RING GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
             20090102     WP  2009       1          2          CA081028006      120081024G6310C0183           BAR                                     ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              SPRAG CLUTCH    CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       930                                                            (CAN) DURING AN AES MIDLIFE INSP FOUND: SPRAG CAGE CRACKED (2) CROSSBARS SHAFT WORN UNDERSIZE HOUSING WORN OVERSIZE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   E295                 
             20090102     GL  2009       1          2          CA081028007      120081020G5320C2CE329A        BRACKET                                 DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD22D   22D30       NE  FIREWALL        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSP, AN AME FOUND A CRACK IN RADIUS OF MIXTURE CONTROL BRACKET ATTACHED TO FIREWALL, BRACKET WAS REMOVED, REPAIRED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3R3  RRCA806    5E1     5  CP736     
             20090102     EA  2009       1          2          CA081029001      120081027G2820                TUBE                                    CNDAIRCL604 CL604       1900301EA                                                               FUEL SYS        DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) WHILE TROUBLESHOOTING A FUEL TRANSFER PROBLEM ON THE CHALLENGER 604, SERIAL NR 5320,  WE FOUND 3 DAMAGED FUEL TUBES IN THE CENTER FUEL TANKS, 2 IN THE RT SIDE AND 1 IN THE LT SIDE. ALL 3 FUEL TUBES WERE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA21EA                        
             20090102     SO  2009       1          2          CA081029002      120081027G77211020007         PROBE                                   PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  CYLINDER HEAD   MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) PILOT OBSERVED LT ENG CYLINDER HEAD TEMP OVER RED-LINE. OTHER ENG PERIMETERS WERE NORMAL. PILOT CHOSE TO SHUTDOWN THE ENG AND FEATHER THE PROPELLER. LANDED WITHOUT INCIDENT. MAINT TROUBLESHOT AND FOUND LT ENGINE CHT READ 150 DEGREES WHEN ENGINE WAS COLD. CHANGED THE PROBE TO P/N AN5546-1 IAW IPC. THE PROBE REMOVED IS AN FAA/PMA ALTERNATE TO THE REQUIRED P/N IN THE IPC.                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20090102     NM  2009       1          2          CA081029003      120081024G612030005000024     SIGNAL COND UNIT                        DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  PROPELLER       INOPERATIVE     W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       3523635236                                                     (CAN) JUST AFTER TAKEOFF, NR 2 ENGINE WENT TO FEATHER. AUTO FEATHER WAS ARMED/CREW HAD NOT COMMANDED AN ENG FEATHER. CREW COMPLETED SHUT DOWN OF NR2 ENG, DECLARED AN EMERGENCY AND RETURNED TO ORIGINATING AIRPORT. NO OTHER INCIDENTS DURING LANDING. MAINT INTERROGATION OF FDR RECORD SHOWS ELECTRONIC FEATHER SIGNAL WAS GENERATED BY THE TSCU AND SYSTEMS RESPONDED TO THIS SIGNAL AND COMMENCED FEATHERING OF THE NR 2 ENGINE. ENG MFG EXAMINATION OF FDR DATA SHOWS ENGINE AND PROP OVER TORQUE DURING ENGINE FEATHER. DILASTIC TEST OF ENG HARNESS AND TSCU SHOWED NO CONFIRMED FAULTS. ENG HARNESS AND TSCU (TSCU SUSPECTED) REPLACED FOR TROUBLESHOOTING. ENGINE OVER TORQUE INSPECTIONS COMPLETED AND ALLOWED TO CONTINUE IN SERVICE2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090102     EA  2009       1          2          CA081029004      120081026G27508004301         CONTROL UNIT                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        UNSERVICEABLE   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      (CAN) ON DECENT CREW SELECTED FLAPS DOWN AND FLAPS STOPPED AT 3 DEGREES. CREW ELECTED TO DO A GO AROUND AND PERFORMED THEIR CHECKLIST.  ADVISED TOWER THEY WOULD LIKE TRUCKS ON STANDBY BUT DID NOT DECLARE AN EMERGENCY.  CREW BRIEFED F/A AND MADE ANNOUNCEMENT TO PASSENGERS THEY WOULD BE LANDING A LITTLE FASTER THAN USUAL.  FLIGHT LANDED WITHOUT INCIDENT. RESET OF FLAP SYS AND MEL 27-02 APPLIED. NEXT FLIGHT HAD FLAP SNAG INTO. ACFT THEN FLOWN WHERE THE FLAP SKEW DETECT CONTROL UNIT REPLACED AND SYS CHECKED SERVICABLE.                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
             20090105     NE  2009       1          5          CA081029005      220080915G7261                OIL SYSTEM                              STBROSSD3   SD360       8100606EU  PWA   PT6   PT6A65AR    52043NE                              ENGINE          LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE PILOTS OBSERVED ENG TEMPERATURE RISING THRU 800C AND PEAKING OVER 1000C. FLAMES WERE NOTICED FROM THE EXHAUST. THE ENG WAS SHUTDOWN AND FIRE BOTTLES DISCHARGED. A SINGLE ENG LANDING FOLLOWED.  POST FLIGHT INSPECTION REVEALED OIL LEAKING FROM GAS GENERATOR CASE AND EXHAUST AREA. THE ENG WAS REMOVED AND SENT FOR INVESTIGATION WHERE TEARDOWN REVEALED A NR 1 BEARING DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                          2H72 4T4  T  A41EU   E4EA                 
             20090102     NE  2009       1          2          CA081029006      220081016G7250                TURBINE                                 AEROSPATR72 ATR72201    8680943EU  PWA   PW120 PW124B           NE                              LT ENGINE       SEIZED          W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKEOFF, THE PILOT REPORTED LT ENG TQ INCREASE TO 109 PERCENT. THE PLA WAS MOVED TO GI BUT THE ENG SHUTDOWN ITSELF. THE ACFT WAS DIVERTED TO THE GATE. DURING TROUBLESHOOTING, THE ENG PARAMETERS WERE DOWNLOADED AND ANALYZED. REVIEW SHOWED A DROP OF NH FROM 92 PERCENT TO 0, AND FUEL FLOW REDUCING FROM 550 TO 300, AND THEN TO ZERO. THE NL SENSOR AND THE TMM CHIP DETECTOR WERE INSPECTED AND FOUND CONTAMINATED. THE STARTER GEN WAS REMOVED IN ORDER TO ROTATE THE HP SHAFT BUT THE HP TURBINE WAS SEIZED. BORESCOPE INSP PERFORMED AND CONFIRMED THAT THE HP TURBINE WAS NOT ROTATING. SUSPECTING DISTRESS IN THE TOWERSHAFT AREA, THE COVER OF THE AGB DRIVE WAS REMOVED. INSP SHOWED A TOWERSHAFT WITH SIGNIFICANT RAD2H72 4T4  TRTA53EU   E2ONE                
             20090102     CE  2009       1          2          CA081030001      120081012G2160HYLZ503361      CONTROLLER                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  A/C SYSTEM      SMOKE           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      LDLANDING        1                      CA                                                                      (CAN) THE FLIGHT CREW REPORTED SMOKE IN THE CABIN, THE ACFT LANDED SAFELY. MX INSPECTED AND SMOKE WAS THOUGHT TO BE COMING FROM THE VENT BLOWER, THE BLOWER WAS REPLACED, GROUND RUN-UP CHECK WAS CARRIED OUT AND NO SMOKE WAS EVIDENT COMING FROM AIR CONDITIONING SYS. DURING TEST FLIGHT, THERE WAS NO HEATING CONTROL IN AUTO MODE. THE SYS WAS SWITCHED TO MANUAL AND HEAT CONTROLLING WAS POSSIBLE. WHEN THE SYS WAS SWITCHED BACK TO AUTO, A SLIGHT BURNING SMELL WAS NOTICED BUT THERE WAS NO SMOKE IN THE CABIN. THE SYS WAS TURNED OFF AND THE ACFT RETURNED TO BASE. THE CABIN TEMP CONTROLLER WAS REMOVED AND INSPECTED. THERE WAS EVIDENCE OF DAMAGE AND ARCING ON THE UNIT AND IT WAS REPLACED AND THE ACFT RETURNED TO SERVICE.  1L72 4T4  T  A24CE   E4EA    5  CSTC      
             20081230     EA  2008       12         30         CA081030002      120081024G3246472439473232    SEAL            CLEVELANDPNU            DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  WHEEL           WRONG PART      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS PROBLEM WAS IDENTIFIED WHILE CARRYING OUT ROUTING MX ON  AMPHIBIAN FLOAT MAIN WHEELS. THE MFG PARTS BOOK SPECIFIED WHEEL GREASE SEAL THAT WHEN INSTALLED WERE 0.010 TOO SMALL OF A DIAMETER, CAUSING THE SEAL TO FALL OUT OF POSITION.  HAVE CONTACTED THE OEM MFG TO DISCUSS THIS ISSUE AND THEY CONFIRMED THE GREASE SEAL LISTED IN THE PARTS MANUAL IS TOO SMALL OF A DIAMETER AND THAT THEY ARE IN THE PROCESS OF AMMENDING THEIR PARTS MANUAL TO SHOW THE CORRECT SEAL.  THESE FLOATS ONLY HAVE 32 HOURS TSN, MFG FAILED TO INFORM THEIR CUSTOMERS OF THIS PROBLEM WITH THE SIZE OF THE GREASE SEAL.                                                                                                                            1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081230     NM  2008       12         30         CA081030003      120081016G27511817392         TRANSMITTER                             BOEING737   737201      1384454NM  PWA   JT8   JT8D17      52049NE                              LT FLAP POSITIONFAILED          W      L   ABORTED APPROACH                                                                                F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) DURING FINAL APPROACH, WHEN THE PILOTS SELECTED FLAPS 25, THE FLAPS STOPPED SLIGHTLY PAST FLAPS 15. THE PILOTS SELECTED FLAPS UP AND OVERSHOT THE APPROACH. THE FLAPS RETRACTED OK. ON THE NEXT APPROACH, THE FLAPS OPERATED NORMALLY. MX INSPECTED AND OPERATED THE FLAPS SYS AND FOUND NO FAULTS. REPLACED THE COCKPIT FLAP INDICATOR, SUSPECTING THE ACFT HAD A FALSE FLAP ASSYMETRY PROBLEM.  THE ACFT FLEW THE NEXT 2 DAYS WITH NO PROBLEMS.  THE FOLLOWING DAY, THE ACFT EXPERIENCED THE SAME PROBLEM ON APPRAOCH INTO AIRPORT. ON THIS OCCURANCE THE PILOTS HAD TIME TO SELECT THE FLAPS UP AND RESELECT THE FLAPS DOWN. ON THE SECOND TRY, THE FLAPS OPERATED NORMALLY.  MX INSPECTED AND FUNCTIONED THE FLAP SYS A SECOND TIME AN2L72 4F4  F  A16WE   E2EA                 
             20081230     WP  2008       12         30         CA081030004      120080313G7810C1693           EXHAUST DUCT                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          DEFORMED        W      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) VISUAL INSP (CF90-03R2) FOUND DEFORMATION AND CRACK IN MUFFLER ASSY AT THE BASE OF THE EXHAUST PIPE WITH SUBSEQUENT LEAK OF EXHAUST GASES INTO CABIN HEAT SYS, NO CO WARNING LIGHTS OR PILOT REPORTS POSTED. PART REPLACED AS REQ`D.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
             20081230     SW  2008       12         30         CA081031001      120081031G6510327211          COUPLING                                BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              T/R DRIVE SHAFT CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A SHEDULED 100/300 HR INSP OF THE FWD T/R DRIVESHAFT SEGMENT THOMAS COUPLINGS, THE FWD THOMAS COUPLING WAS FOUND CRACKED. UPON FURTHER DISSASSEMBLY ONLY ONE OF THE LAMIATES WAS FOUND CRACKED. THE COUPLING WAS REMOVED FROM SERVICE AND REPLACED NEW. THE AFT COUPLING WAS ALSO INSPECTED FUTHER WITH NO DAMAGE NOTED.                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E1GL                 
             20081230     SW  2008       12         30         CA081031002      120081029G3210ESI2440         HOUSING                                 GULSTM690TP 690A        0141722SW  GARRTTTPE331TPE33110T   29065NE  HARTZLHCB3T HCB3TN5     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9283 53                                                        (CAN) DURING THE REQUIRED 5 YEAR OVERHAUL ON THE LANDING GEAR, A CRACK WAS DISCOVERED ON THE MLG HSG VISUALLY.   IR WAS CONFIRMED USING NDT METHODS LPI AS WELL AS EDDY CURRENT FOR CONFIRMATION.  EDDY CURRENT READING INDICATED A DEPTH OF .040".   THIS WAS THE FIRST OVERHAUL OF THIS LANDING GEAR BY THE OPERATOR SINCE PURCHASE 3 YEARS AGO.                                                                                                                                                                                                                                                                                                                                                                                              1H72 3T4  T  2A4     E4WE    6  CP15EA    
             20081230     SW  2008       12         30         CA081031004      120081031G2710                ROLL PIN                                AIRTRCAT802 AT802A      0390308SW  PWA   PT6   PT6A67A     52043NE                              AILERON PUSHROD MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14                                                             (CAN) LT WING AILERON PUSHROD ASSY FOUND TO BE MISSING ONE ROLL PIN THAT RETAINS THE INBD END ROD END BEARING. THIS IS A DEFECT FROM THE FACTORY (INSIDE OF HOLE IS PAINTED). ALL OTHER ROD ENDS INSPECTED NO OTHER DEFECTS FOUND, ARROW SHOWS MISSING PIN HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TNCA19SW   E26NE                
             20081230         2008       12         30         CA081103001      420081016G2300                DISPLAY                                 BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                                              FAILED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       DEDESCENT        1                      CA                                                                      (CAN) IN FLIGHT DURING DESCENT ACFT LOST ALL RADIOS AND NR 2 MFD. THEY WERE ABLE TO COMMUNICATE TO ATC BY GOING TO THE REVERSIONARY PANEL AND TURNING THE TUNE KNOB TO THE COMM1 121.5 SELECTION.  LANDING WAS UNEVENTFUL.  AFTER LANDING 20 MINUTES LATER CREW INDICATED THAT ALL THE FREQUENCIES WENT AMBER AND LOST THEIR ABILITY TO TUNE THE RADIO THROUGH THE FMS. WHEN THEY WOULD TRY TO TUNE THE RADIOS THE FREQUENCIES WOULD CHANGE ON THERE OWN. THE TRANSPONDER WAS ALSO INTERMITTENT, AND THEN THE COPILOT`S MFD WENT BLACK.  HAD THE CREW GO INTO THE MDC FAULT HISTORY AND THEY CAME UP WITH A LOT OF FAULTS. PLEASE SEE ATTACHED PIC`S BELOW FOR FAULTS AND THE B3 CODES.  CREW THEN DID A COMPLETE POWER DOWN ACFT AND WAIT A FEW2L72 4F4  FRTT00005NYE00010LA             
             20081230     NM  2008       12         30         CA081103002      120080716G3320BR63031023      SOCKET                                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  CABIN LIGHTS    MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A C-CHECK INSP OF THE CABIN LIGHTING SYS IT WAS FOUND THAT THE NR 5 FLOURESCENT CABIN LIGHTING BALLAST WAS MELTED AT THE BULB SOCKET. BALLAST WAS REMOVED AND REPLACED.  TT ON THE BALLAST CAN NOT BE ACURATLY DETERMINED BUT WITH A DATE STAMP OF FEB 11, 1987 IS LIKLEY ORIGINAL EQUIPMENT.  LIGHT WAS FUNCTIONING AT THE TIME THE DEFECT WAS FOUND. ONE OTHER LIGHTING BALLAST WAS ALSO FOUND WITH MINOR DAMAGE OF A SIMILAR NATURE. IT WAS REPLACED AS WELL.  SUBMITTED LATE AS THE C-CHECK WAS COMPLETED BY AN OUTSOURCE FACILITY AND UNTIL RECENTLY WAS NOT AWARE OF THE DAMAGED PARTS.                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     EA  2008       12         30         CA081103003      120081102G291082970009325     LINE                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  HYD SYSTEM      CHAFED          W      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    CRCRUISE         1                      CA       3829438294                                                     (CAN) DURING CRUISE FLIGHT, THE ACFT REPORTED LOSING NR1 HYD SYS FLUID AND ACTIVATION OF NR1 ISO VALVE. COMMERCIAL DECISION MADE FOR ACFT TO RETURN TO ORIGINATING AIRPORT. FLAP (0) DEGREES AND LANDING CARRIED OUT THAT WAS DUE TO ACTIVATION OF NR1 HYD SYS ISO VALVE.  MAINT INSP FOUND HYD LINE FROM ENG DRIVEN PUMP TO PRESSURE MANIFOLD CHAFED AT NACELLE CLAMP. LINE REPLACED. ENG DRIVEN PUMP REPLACED AS PUMP HAD OPERATED AFTER FLUID DEPLETION. LEAK AND FUNCTION CHECKS CARRIED OUT. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230         2008       12         30         CA081103004      420081008G8300310186401       BEARING                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  ACCESSORY G/B   FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       7114 2318                                                      (CAN) NR 1 BRG FAILED WITHOUT OUTSIDE INFLUENCE. RESULTANT METAL CONTAMINATION CONTAINED TO THE GB,  MAIN OIL FILTER AND OIL PUMP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20081230     SW  2008       12         30         CA081103005      120081030G800031057463        IGNITION SWITCH                         SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  ENGINE          CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) OIL LEAK ON THE ENG FROM LWR ENG COWL FOUND. TROUBLESHOOTING REVEALED THE PROBLEM AS A AUTO IGNITION PRESSURE SWITCH LEAKING AT THE BASE WELD.  INSP WITH A MAGNIFYING GLASS FOUND A CRACK APR .7500 AROUND THE CIRCUMFERENCE OF THE WELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
             20081230     EU  2008       12         30         CA081104001      120081028G3231                HOSE                                    BRAERODH125 BAE125800A  1500285EU  GARRTTTFE731TFE7315R    01518WP                              DOOR ACTUATOR   LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) PILOTS REPORTED LOSS OF HYD PRESSURE AFTER LANDING WHILE TAXING BACK TO AMO.  ON INSP, FOUND IN THE RT GEAR WELL A FLEX HYD LINE INSTALLED WITH A SLIGHT TWIST ON IT. THE LOCKWIRE ON THE B-NUT WAS LOOSE, AND THE TWIST ON THE HYD LINE AIDED IN ALLOWING THE B-NUT TO BACK OFF CAUSING THE HYDR LEAK IN THE RT GEAR WELL.  AREA CLEANED UP. THE LINE WAS INSPECTED FOR CRACKS AND PROPER ALIGNMENT RE-INSTALLED RE-TORQUES AND RE-LOCKWIRED. INSPECTED HYDR PRESSURE FILTER AND FOUND IT TO BE SERVICEABLE AND RE-INSTALLED FILTER. CARRIED OUT HYD FUNCTIONS AND LEAK CHECKS ON THE ACFT USING GROUND HYD CART. THERE WERE NO APPARENT LEAKS FOUND. CARRIED OUT GROUND RUNS ON AIRCRAFT, BLED HYD PUMPS AND CHECKED SYS PRESSURE AND CY2L72 4F4  FRTA3EU    E6WE                 
             20081222     NE  2008       12         22         CA081104002      220081031G7230                COMPRESSOR                              DOUG  DC3   DC3C        3021457WP  PWA   PT6   PT6A67R     52043NE  HARTZLHCB5M HCB5MA3     GL  RT EINGE        SEIZED          W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE RT GENERATOR KICKED OFF-LINE. SHORTLY AFTER THAT TEMP INDICATIONS IN THE RT ENG CLIMBED CAUSING THE FLIGHT CREW TO SHUT DOWN THE ENGINE AND CONTINUE ON TO LAND AT THE SCHEDULED POINT OF LANDING. THE STARTER GEN WAS REMOVED AND THE COMPRESSOR SECTION OF THE ENGINE WAS FOUND TO BE SEIZED.                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4R4  T  A669    E26NE   6  CP44GL    
             20081222     GL  2008       12         22         CA081104003      120080927G241007A19474        BRACKET                                 DIAMONDA40  DA40        2990002GL  LYC   O360  IO360M1A         NE  MUHBR MTV   MTV3BC      EU  ALTERNATOR      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       805                                                            (CAN) DURING A ROUTINE INSP, THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE BROKEN ACROSS THE WIDTH OF THE BRACKET ADJACENT ONE OF THE MOUNTING HOLES. (REAR MOUNTING BOLT THAT IS USED TO ATTACH THE BRACKET TO THE ENGINE).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTA47CE   1E10    5  CUSSR     
             20081222     NM  2008       12         22         CA081104004      120081031G555417063073405     FITTING                                 EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              RUDDER          BROKEN          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       6515                                                           (CAN) ON PUSHBACK, RECEIVED FLIGHT CONTROL- NO DISPATCH MESSAGE. INVESTIGATION FOUND THE RUDDER UPPER FTG LUG BROKEN. RUDDER PCU ACTUATOR WAS INSTALLED 2007-05-17.  CAUSE WAS FOUND TO BE MISSING SLIDING BUSHING, P/N 170-62218-003, IPC 27-21-05 FIG.01 ITEM 170. THE ITEM WAS FOUND GREASED BUT NOT WORN IN A NEARBY CAVITY OF THE RUDDER. THIS IS CONFIRMED BY A CUT/SLICED COTTER PIN THAT IS STILL IN THE BOLT, WHICH WAS PULLED THROUGH THE LOWER LUG, AND CAUSED DAMAGE ON THE FLANGED BUSHING IN THE LOWER LUG, BUT NO DAMAGE WAS FOUND ON THE INSIDE OF THE SLIDING BUSHING. THE BUSHING WHEN CORRECTLY INSTALLED, SITS INSIDE THE FLANGED BUSHING, AND PREVENTS SIDE LOADS FROM BEING APPLIED ON THE LUGS WHEN THE ATTACH BOLT IS TO2L72 4F4  FRTA56NM   E00063EN             
             20081222     EU  2008       12         22         CA081105001      120081105G2822D107318D1       PUMP                                    BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              FUEL BOOST      MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) TWICE NOW WE HAD FOUND THE FWD MAIN TANK BOOST PUMPS WHERE INSTALLED IN THE WRONG ORIENTATION, THE TRANSFER TUBES (FEED LINE) WAS PULL OUT OF THE FEED TANK. THE FORWARD TRANSFER PUMP HAS SYMMETRICAL MOUNTING HOLE. THE ORIENTATION OF THE PUMP DETERMINES THE FUEL FEED LINE POSITION. IF THE PUMP IS ROTATED THE FUEL FEED LINE MAY COME OUT OF POSITION. THIS HAS FOR CONSEQUENCE TO REDUCE THE FUEL TRANSFER TO THE FEED TANK. THE PROPER INSTALLATION FOR THE FORWARD FEED PUMP IS THE FEED LINE ATTACHING HARDWARE SHOULD BE ORIENTED 12.00 O`CLOCK, WITH THE LONGITUDINAL AXIS. (SEE FIGURE 62-3 DETAIL F) IN THIS CASE THE HARDWARE WAS LOCATED AT 8.00 O`CLOCK.                                                                1G72 3U3  U  H3EU    E4CE                 
             20081222     NE  2008       12         22         CA081105002      220080908G7200                ENGINE                                  SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                                              OVERTEMP        W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RMJPARTIAL RPM/PWR LOSS      OVER TEMP                 WARNING INDICATION        DEDESCENT        1                      CA                                                                      (CAN)  WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENG N1 LOW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENG LOW OIL PRESSURE LIGHT. A SCAN OF ENG GAUGES REVEALED NR 2 ENG HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. FLT CREW IDENTIFIED PROBLEM AS AN ENG ROLL BACK AND SHUTDOWN OF NR 2 ENGINE CARRIED OUT. ACFT THEN RETURNED TO LANDING AREA AND MADE AN SINGLE ENG LANDING.  A POST FLT INSP OF T5 RECORDING SYS REVEALED ENGINE TEMP HAD REACHED 798 DEGREES C. ENGINE, FREE TURBINE ASSEMBLY AND FUEL CONTROL UNIT REPLACED AND AFTER A COMPLETE GROUND CHECK ACFT RETURNED TO SERVICE.  ENGINE, FREE TURBINE AND FUEL CONTROL UNIT WERE RETURNED FOR AN OVER TEMP I2G72 4U4  U  H4EA    E15EA                
             20081222     EU  2008       12         22         CA081105003      120081102G32505322012040      LANDING GEAR                            PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NOSE            MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE TAXING FOR TAKEOFF, THE NOSE STEERING BECAME VERY STIFF. PILOT RETURNED TO THE RAMP AND MAINT DISCOVERED THAT WITH THE ACFT WEIGHT ON THE STRUT, AND EVEN WITH THE SCISSORS DISCONNECTED, THE STEERING WAS EXTREMELY HARD, AND MADE A RATCHETING SOUND. THE NOSE GEAR ASSY WAS REPLACED AND THE ACFT RETURNED TO SERVICE. AWAITING TEAR DOWN REPORT ON NOSE GEAR ASSY TO ASCERTAIN CAUSE.                                                                                                                                                                                                                                                                                                                                           1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081222     NM  2008       12         22         CA081105004      120081103G2910                LINE                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYD SYSTEM      RUPTURED        W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) CREW NOTICED HYD QTY LOSS ON NR 2 SYS. REPORTEDLY, NR 2 HYD ISOLATON VALVE CAUTION LIGHT CAME ON, BUT HYD PRESSURE REMAINED NORMAL. THE CREW DECIDED TO PERFORM ALTERNATE GEAR EXTENSION FOR LANDING.  ACFT TOWED TO HANGAR, WHERE TECHNICIANS DISCOVERED RUPTURED HYD LINE IN NR 1 MLG GEAR BAY. LINE HAD BEEN CHAFED FROM A BONDING CLAMP (AN735C4). TECH REPORTED BONDING CLAMP WAS LOOSE, AND APPEARED TO BE INSTALLED WITHOUT SEALANT. RUPTURED HYD LINE WAS FOR THE NR 1 MLG DOWNLOCK ACTUATOR. LINE REPAIRED WITH A PERMASWAGED SPLICE SECTION, AND A/C RETURNED TO SERVICE.                                                                                                                                                       2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081219     NM  2008       12         19         CA081105005      120081103G291082974351003     LINE                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              HYD SYSTEM      LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, CREW NOTICED NR 2 HYD ISO VALVE CAUTION LIGHT CAME ON, NR 2 HYDRAULIC PRESSURE REMAINED NORMAL, AND THERE WAS A "SMALL QUANTITY" OF FLUID REMAINING IN NR 2 SYSTEM.  CREW DECLARED EMERGENCY LANDING. CREW PERFORMED AN ALTERNATE GEAR EXTENSION, AND ACFT LANDED.  ACFT TOWED TO HANGAR WHERE TECHNICIANS DISCOVERED HYDRAULIC FLUID DRIPPING FROM NR 2 NACELLE, O/B OF JET PIPE CENTER SECTION.  JET PIPE REMOVED AND TECHNICIANS DISCOVERED A SPLIT IN THE HYDRAULIC LINE, WHERE IT HAD BEEN CHAFFING ON THE FWD JET PIPE SHROUD DAMAGED LINE WAS PART OF MLG `NR 2 GEAR UP` PIPING, P/N 82974351-003.  LINE TO BE REPLACED.                                                                                            2H72 4T4  TRTA13NM   E00062EN             
             20081222     NE  2008       12         22         CA081105006      220081028G7200                ENGINE                                  DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 2            MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB SHORTLY AFTER T/O, THE NR 2 ENGINE HAD AN UNCOMMANDED AUTOFEATHER AND SUBSEQUENT OVERTORQUE. THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE WHERE AN UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE TORQUE SIGNAL CONDITIONER UNIT AND THE TORQUE SENSOR. MM REQUIREMENTS ARE BEING PERFORMED FOR THE OVERTORQUE CONDITION BEFORE A DECISION FOR FURTHER ACTION IS TAKEN.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                             2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     NE  2008       12         30         CA081105007      220081029G7200                ENGINE                                                                     PWA   PT6   PT6A68           NE                                              MAKING METAL    W      BA  EMER. DESCENT           UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) DURING FLIGHT TEST, THE ENG HAD A PARTIAL FEATHERING OF THE PROPELLER LEADING TO A PARTIAL LOST OF THRUST. THE ENGINE "CHIP LIGHT" CAME APPROX 20 SECONDS AFTER LOST OF THRUST. THE PILOT REDUCED POWER TO FLIGHT IDLE AND RETURNED TO BASE. POST FLIGHT INSP REVEALED METALLIC DEBRIS ON THE CHIP DETECTOR AND MAIN OIL FILTER. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED IN DUE COURSE.                                                                                                                                                                                                                                                                                                                   4  T          E26NE                
             20081229     NE  2008       12         29         CA081105008      220081031G7261                CARBON SEAL                             AMD   FALC50FALCON2000  2730170NM  PWC   PW308 PW308C      52182NE                              ENGINE          CRACKED         W      C   ABORTED TAKEOFF                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKEOFF ROLL, AT 90 KNOTS, THE OIL PRESSURE DROPPED TO ZERO AND THE LOW OIL PRESSURE WARNING ANNUNCIATED. THE CREW RETARDED THE POWER TO IDLE, ABORTED THE T/O AND RETURNED TO THE RAMP. TROUBLESHOOTING FOUND AN OIL LEAK FROM A CRACKED CARBON SEAL ON THE FRONT HYD PUMP DRIVE PAD. THE ACFT WAS RETURNED TO SERVICE FOLLOWING ITS REPLACEMENT.                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA50NM   E00065EN             
             20081222     NE  2008       12         22         CA081105009      220081101G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              NR 2            FLAMED OUT      W      A   UNSCHED LANDING                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL270, THE PILOT NOTICED A POWER ROLL BACK ON NR 2 ENGINE.  HE IMMEDIATELY DIVERTED THE ACFT TO AN ALTERNATE AIRPORT.  THE ENGINE THEN FLAMED OUT AND THE PILOT MADE A SINGLE ENGINE LANDING.  THE FUEL CONTROL WAS REPLACED AND THE ACFT RELEASED TO SERVICE.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                            1L72 4F4  F  A22CE   E00053EN             
             20081222     WP  2008       12         22         CA081105010      120081105G5340C8303           ANGLE                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ELT MOUNT       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       2149                                                           (CAN) FOUND CRACKED ANGLE DURING INSPECTION OF ELT MOUNT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
             20081229     EA  2008       12         29         CA081105011      120080924G524033130131        PISTON                                  CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       256                                                            (CAN) DURING ANNUAL INSP, WATER DOOR UNLATCHING JACKS WERE REMOVED FOR INSPECTION. THE PISTONS OF THE JACKS WERE INSPECTED USING LIQUID PENETRANT INSPECTION FOR PRECAUTIONARY REASONS. BOTH PISTONS OF THE ACTUATORS WERE FOUND TO HAVE INDICATIONS SHOWING THERE WERE CRACKS. BOTH SHAFTS WERE SENT TO OUR AMO`S NDT COMPANY FOR MAGNETIC PARTICLE INSPECTION TESTING TO VERIFY THE CRACKS. CRACKS WERE VERIFIED. SERVICE BULLETIN 215-528 WAS CREATED TO ELIMINATE THE POSSIBILITY OF THE PISTONS CRACKING. BOTH OF THESE ACTUATORS HAD BEEN THROUGH OUR OVERHAUL SHOP. ONE ACTUATOR WAS REPAIRED, THE OTHER WAS OVERHAULED. IN BOTH CASES, THE ACTUATORS HAD NEW PISTONS INSTALLED AND ACCUMULATED.                                         2H72 4R3  RRTA14EA   ATC14   6  CP871     
             20081229     EA  2008       12         29         CA081105012      120081020G2751601R930303      TRANSMITTER                             CNDAIRCL600 CL6002B19   1900309EA                                                                               MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       12282                                                          (CAN) UPON REACHING FL280 (CRUISING ALT) THE FLT CREW REPORTED THAT THEY RECEIVED THE SAME INDICATIONS ON EICAS AS THEY WOULD HAVE RECEIVED ON APPROACH (BRAKE TEMP, GEAR ICONS AND FLAP INDICATOR AND SPEED RASTER MOVING DOWN TO 210 KTS) AND THAT DURING THESE INDICATIONS, ACFT WITH AUTOPILOT ENGAGED STARTED TO PORPOSE UP AND DOWN +/- 50 TO 100 FT. THE FLAP DEGRADED (S) MSG WAS POSTED AS WELL.  DURING THESE ALTITUDE FLUCTUATIONS, F/A WAS ASKED TO VERIFY WHETHER FLAPS WERE MOVING. SHE INDICATED TO CREW THAT THE FLAPS WERE NOT MOVING.   ATC WAS NOTIFIED AND ACFT DIVERTED. JUST BEFORE THE FLT CREW STARTED THEIR DEVIATION, THE ACFT NOSED OVER BRIEFLY WITH ABOUT A 500 FT LOSS IN ALTITUDE BUT INSTANTLY RECOVERED BACK TO2L72 4F    RTA21EA                        
             20081229         2008       12         29         CA081106001      420081104G2562E01             ELT                                                                                                                                                     INOPERATIVE     W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) WHILE COMPLETING AN ANNUAL BENCH RECERTIFICATION CHECK ON AN ELT, NO POWER OUTPUT COULD BE MEASURED ON BOTH 121.5 AND 243 MHZ FREQUENCIES. THE UNIT WAS STILL UNDER WARRANTY BY THE MFG AND IT WAS BELIEVED THIS WAS THE FIRST CHECK SINCE BEING PUT INTO SERVICE. THE UNIT WAS RETURNED TO THE MFG FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     
             20081229         2008       12         29         CA081106002      420081104G2562E01             ELT                                                                                                                                                     MALFUNCTIONED   W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE ANNUAL BENCH RECERTIFICATION INSP OF AN ELT THE VALUE OF MEASURED CURRENT DRAW WAS OBSERVED TO EXCEED THE MFG SPECIFICATION BY 50MA. THE UNIT WAS STILL UNDER THE MFG WARRANTY AND IT WAS BELIEVED THIS INSP WAS THE FIRST CHECK COMPLETED SINCE BEING PUT INTO SERVICE. THE ELT WAS RETURNED TO THE MFG FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                     
             20081229     EA  2008       12         29         CA081106003      220081030G8520                CASE                                    CESSNA150   152         2071835CE  LYC   O235  O235N2C     41505EA  SNSNCH72C   72CK        EA  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED MAINT (OIL CHANGE) OIL WAS DISCOVERED LEAKING FROM THE UPPER ENGINE CRANK CASE. FUTHER INSP CONFIRMED A CRACK 3 INCHES LONG BETWEEN CYLINDER NR 2 AND 4.  ENGINE WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A19    E223    5  NP9045    
             20081229     GL  2008       12         29         CA081106004      120081010G2840                FLOAT           GE                      DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  FUEL TRANSMITTERDETACHED        W      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) GENERAL ELECTRIC FUEL TRANSMITTER MODEL NR 56949-248, TYPE TJ-13. FUEL GAUGE READINGS WERE STUCK AT 22 GAL, INDICATING ON CENTER FUEL CELL. INVESTIGATION REVEALED THAT THE FUEL TRANSMITTER. FLOAT HAD BECOME DETACHED FROM THE FUEL TRANSMITTER.  FUEL TRANSMITTER REMOVED, REPAIRED, TESTED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3R3  RRCA806    5E1     5  CP206     
             20081229     SO  2008       12         29         CA081106005      120081031G7820                BAFFLE                                  PIPER PA28  PA28180     7102808SO  LYC   O360  O360A4A     41514EA  SNSNCH76E   76EM8S5     EA  MUFFLER         FAILED          W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      (CAN) POWER LOSS ON TAKEOFF DUE TO BAFFLE FAILURE INSIDE MUFFLER WHICH RESTRICTED EXHAUST OF ENGINE CAUSING PARTIAL POWER LOSS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E286    5  NP4EA     
             20081229     GL  2008       12         29         CA081106006      120081105G3220                ARM                                     DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  NLG WHEEL FORK  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2010                                                           (CAN) BOTH ARMS OF THE NLG WHEEL FORK ASSY WERE FOUND CRACKED APPROXIMATELY 1.75 INCH FWD OF THE WHEEL AXLE BOLT. BOTH ARMS ARE CRACKED THRU THE LOWER PORTION AND A .25 INCH CRACK HAS STARTED ON THE UPPER SIDE OF THE ARMS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081229     EA  2008       12         29         CA081106007      120081103G2440671GA01Y00      POWER UNIT                              CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              APU             BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      CA                                                                      (CAN) NOT ACCEPTING AC EXTERNAL OR APU GEN AC.  MX DETECT A BURNED CONTACTOR.  CURRENTLY ACFT EXTERNAL AVAILABLE LIGHT IS ON.  ACFT ONLY MAINTAINS POWER FOR 3 SECONDS, AND KICKS OFF.  MFG HAS ISSUED A CONCESSION SL STATING NO OBJECTION TO FERRY PROVIDED THE FOLLOWING MTC PROCEDURES BE ACCOMPLISHED.  DISCONNECT CONNECTORS K119-S4 AND K119-S3 2. CAP AND STOW CONNECTORS K119-S4 AND K119-S3 IAW EEC/SPM 20-12-05 3. APU GENERATOR IS INHIBITED IAW MEL 24-22-01 4. EXTERNAL ACFT POWER SYS IS INHIBITED IAW MEL 24-41-03 FROM A FLT OPS PERSPECTIVE, FOR ENGINE START.  START ENG IAW QRH SUPP-2 ENGINE START (BATTERY/EXTERNAL AIR) PROCEDURE.                                                                                       2L72 4F4  FRTA21EA   E00063EN             
             20081222     NM  2008       12         22         CA081107001      120081104G6322B1741           MOUNT                                   ROBSINR22   R22BETAII   7640110NM                                                               FAN WHEEL ASSY  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       162                                                            (CAN) AT REINSTALLATION OF FANWHEEL ASSEMBLY, FOUND TAPERED MOUNTING FLANGE COMPLETELY CRACKED LONGITUDINALLY.  UNIT SENT TO MANUFACTURER FOR WARRANTY EXCHANGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O      H10WE                        
             20081222     WP  2008       12         22         CA081107002      120081104G5340C8303           ANGLE                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ELT MOUNT       SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2197                                                           (CAN) THE ANGLE USED AS PART OF ELT INSTALLATION WAS FOUND SHEARED DURING 2200 HR OVERHAUL TEARDOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20081229     CE  2008       12         29         CA081107003      120081103G5347MC07106582      SEAT TRACK                              CESSNA182   182J        2072722CE  CONT  O470  O470R       17026SO                              LT PILOTS/LTPAS CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2250                                                           (CAN) 3 CRACKS LT PAS RAIL, 1 CRACK LT PILOTS RAIL, SEAT RAILS SOME WEAR, WEAR WITHIN LIMITS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A13    E273                 
             20081222     NE  2008       12         22         CA081107004      220081026G7414106006169       MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAGNETO INTERMITTENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081222     NE  2008       12         22         CA081107005      220081026G74141060064620      MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAGNETO INTERMITTENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
             20081222     WP  2008       12         22         CA081107006      120081029G6310C0511           ACTUATOR                                ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CLUTCH          MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CLUTCH ACTUATOR REMOVED DUE TO FAULTY SWITCHES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   E295                 
             20081229     GL  2008       12         29         CA081107007      220081030G732323076061        DRIVE SHAFT                             BELL  206   206B1       1181503SW  ALLSN 250C  250C20B     03013GL                              TURBINE GOVERNORFAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2021 2021                                                      (CAN) DURING REMOVAL OF THE GOVERNOR FOR SCHEDULED OVERHAUL, AT REMOVAL FROM ENGINE GEARBOX, THE CLIP THAT RETAINS THE DRIVEGEAR ON THE PT SHAFT WAS NOT LOCATED IN THE GROOVE ON THE SHAFT, AND THE WASHERS THAT ARE RETAINED BY THE CLIP AND SET AGAINST THE DRIVE GEAR, WERE FOUND SITTING IN THE MALE SPLINE OF THE GEARBOX DRIVE. IT APPEARS AS THOUGH THE END OF THE DRIVESHAFT WAS WORN DOWN TO ALLOW THE CIRCLIP TO BECOME DISLODGED FROM THE GROOVE AND WORK IT`S WAY OFF THE SHAFT, HOWEVER THE DAMAGE TO THE SHAFT COULD HAVE BEEN DUE TO THE DISLODGED WASHERS SITTING IN THE DRIVE SPLINE. THE ONLY ITEM FOUND RETAINING THE DRIVEGEAR WAS THE SPRING ON THE BACK SIDE OF IT. THE ENGINEER INSPECTED THE GEARBOX DRIVE BUT WAS UNAB1G71 3U3  U  H2SW    E4CE                 
             20081229     EU  2008       12         29         CA081107008      120081104G6220117775P         BALL JOINT                              SNIAS 350   AS350*             EU  LYC   LTS101LTS101*          NE                              STARFLEX        DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       277                                                            (CAN) IT WAS DISCOVERED DURING A DAILY INSP THAT THE TEFLON LINING INSIDE ONE OF THE STARFLEX BALL JOINTS WAS DISPLACED. THE BEARING WAS REPLACED BEFORE FURTHER FLIGHT AND IT WAS NOTICED THAT THE TEFLON WAS STILL GLUED FIRMLY IN PLACE BUT IT WAS MISALIGNED FROM ITS ORIGINAL POSITION.                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H9EU    E5NE                 
             20081222         2008       12         22         CA081110001      420081101G2562C362042702      BATTERY         DHAV                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ULB             INCORRECT       W      K   NONE                                                                                            WL INADEQUATE Q C            NO TEST                                             ININSP/MAINT     1                      CA                                                                      (CAN) WRONG BATTERY INSTALLED IN UNIT.  CORRECT BATTERY INSTALLED INTO ULB. REF WO NR 214939                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081222     CE  2008       12         22         CA081110002      120081105G32601003810061      SWITCH                                  BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              NLG             INTERMITTENT    W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) AFTER PILOT SELECTED GEAR DOWN, THERE WAS NO INDICATION THE NOSE GEAR WAS DOWN AND LOCKED, ACFT DIVERTED BACK TO MX BASE.  ON ROUTE NOSE GEAR INDICATION CAME ON.  ACFT LANDED WITHOUT INCIDENT.  MX REPLACED NOSE GEAR DOWN LOCK INDICATOR SWITCH AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3T4  T  A14CE   E4EA                 
             20081229     GL  2008       12         29         CA081110003      120081106G5311                SPAR                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              FUSELAGE        DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5972                                                           (CAN) DURING THE 6000 HOUR INSP DELAMINATIONS AND CRACKS WERE DISCOVERED ON THE SPAR BRIDGE. THE DELAMINATIONS AND CRACKS WERE FOUND ON THE RT SIDE ON THE AFT UPPER CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUESLAGE AS VIEWED FROM THE GAS TANK AREA. A SERIES OF INTERCONNECTED CRACKS THAT APPREAR TO BE IN THE RESIN ONLY. OVERALL LENGTH IS APPROX 40 MM, VARYING IN DEPTH FROM SURFACE CRACKS TO APPROX 3 MMM DEEP. THE LT SIDE HAD DELAMINATIONS AND CRACKS ON THE UPPER AFT CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUSEALGE (THE OPPOSITE TO THE RT SIDE). LENGTH WAS 6-8MM AND DEPTH 5MM.                                                                                                              1L71 3O3  ONTTA4CH   E7SO                 
             20081222     EA  2008       12         22         CA081110004      120081109G5751                CONTROL CABLE                           DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE                              AILERONS        DISLODGED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) RT WING FWD AILERON CONTROL CABLE FOUND SITTING BEHIND THE AILERON INPUT ROD QUADRANT GUARD.  CABLE MOVED OUT OF ITS LOCATION WITH SLIGHT FINGER ACTION.  CABLE HAS LIGHT RUBBING MARK BUT ALUMINUM QUADRANT GUARD FOUND BADLY GROOVED.  WINGS CONTROL CABLE TENSION TOOK ON BOTH SIDE.  LT SIDE MEASURED AT 30 LBS AND RT SIDE AT 20 LBS.  RIGGING TENSION IS BETWEEN 55 AND 65 LBS AT 20 DEGREES CELSIUS.  TENSION TOOK WITH CABLE MISROUTED AND AT PROPER PLACE,  NO SIGNIFICANT TENSION DIFFERENCE AT 2-3 LBS.  LT SIDE CABLE SECTION INSPECTED AT SAME LOCATION, CABLE FOUND ROUTED PROPERLY.                                                                                                                                        2H72 4T4  TRTA13NM   E20NE                
             20081229     GL  2008       12         29         CA081110005      120081109G3220203220080       FORK                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              NOSE GEAR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1541                                                           (CAN) ON PREFLIGHT OF ACFT, PILOT DISCOVERED CRACKS IN NOSE WHEEL FORKS APPROXIMENTLY 1 INCH FROM AXLE AT RADUS OF MACHINING (MACHINED FOR WEIGHT REDUCTION DURING PRODUCTION), ON SIDE OF FORKS.   RT SIDE IS CRACKED DEPTH OF MACHINE AREA ON TOP AND .7500+ ON THE BOTTOM  LT SIDE OF FORK CRACKED BOTTOM DEPTH OF MACHINING AND .5+ ON TOP.  ACFT WAS HAD PROPELLER STIKE ON LANDING APPROX 1000 HRS AGO, NOSE GEAR LEG WAS REPLACED AT THAT TIME AND FORK VISUALY INSPECTED WITH NO CRACKS DETECTED. NO CRACKS WERE NOTED DURING 100 HR INSP THAT WAS COMPLETED 75 HR AGO.   NO OTHER REPORTED HARD LANDING HAVE BEEN REPORTED. ACFT INSPECTED, NO OTHER DAMAGE DETECTED.   MFG HAS ASKED FOR PARTS TO BE RETURNED FOR ENGINEERING EVALUATI1L71 3O3  ONTTA4CH   E7SO                 
             20081222     WP  2008       12         22         CA081110006      120081030G2432B4151           RELAY                                   ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              BATTERY         FAILED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA       386                                                            (CAN) BATTERY WOULD NOT COME ONLINE ALTHOUGH FULL BATTERY VOLTAGE WAS OBSERVED AT BATTERY CONNECTIONS.  BATTERY RELAY WAS REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   E295                 
             20081222     NM  2008       12         22         CA081110007      120081110G531087140011001     STRUCTURE                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  FUSELAGE        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       51173                                                          (CAN) BIRD STRIKE JUST UNDER NOSE AREA.   FOUND NR 2 LOWER COWL WITH INTERNAL CONE DAMAGE, LOWER COWL REMOVED.  ENGINE BOROSCOPED WITH MINIMAL DEBRIS FOUND INSIDE ENGINE.  NO DAMAGE NOTED NO DEBRIS FOUND ON LP COMPRESSOR.  AIRFRAME INSPECTION STILL TO BE CARRIED OUT.  AIRFRAME INSPECTION COMPLETED AS PER MM CHAPTER 5.  PROP INSPECTED AS PER HS MM.61.10.  NEW LOWER COWL INSTALLED, GROUND RUN COMPLETED FOR POWER ASSURANCE AND TESTING OF LOWER COWL.                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081229     EA  2008       12         29         CA081111001      120081107G21508084402         BYPASS VALVE                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              NR 1 ACM        STUCK           W      O   OTHER                                                                                           BGMSMOKE/FUMES/ODORS/SPARKS  MULTIPLE FAILURE          OVER TEMP                 TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI IN, CREW NOTICED ONE OF THEIR AIR-CONDITIONING PACKS WAS OVER TEMPING. THEY WHERE NOT ABLE TO CONTROL IT, SOON NOTICED SMOKE ON FLIGHT DECK. F/A WAS NOTIFIED AND A RAPID DEPLANEMENT WAS CONDUCTED AT GATE. MX FOUND THE DUAL BYPASS VALVE STUCK IN THE FULL HOT POSITION.  NR 1 ACM WAS ALSO FOUND SEIZED (P/N 782790-15, S/N 930930. TSN 28517 HOURS, CYCLES 14277, TSO 878735).  IN ADDITION COMPRESSOR OUTLET OVERTEMP SWITCHES (P/N 750659-16. RATED TO 415F) WERE FOUND INSTALLED IN THE LT AND RT DUCT OVERTEMP SWITCH POSITIONS INSTEAD OF (P/N 750665-9. RATED TO 220F). THIS WAS REPORTED TO COMPANY MX SAFETY DEPT.  BYPASS VALVE, NR 1 ACM AND THE SWITCHES WERE REPLACED, FUNCTION CHECKED SERVICEABLE AND THE ACF2L72 4F4  FRTA21EA   E15NE                
             20081230     EA  2008       12         30         CA081111002      120081028G2612                FIRE WARNING                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              ILLUMINATED     W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      EXPERIENCED AN EMERGENCY EVACUATION A/P ON TAXIWAY (M), DUE SMALL FIRE EMITTING FROM ENG WHILE TAXIING. LOCAL ARRF RESPONDED, PASSENGERS & CREW EVACUATED ACFT WITHOUT INCIDENT. MX VISUALLY INSPECTED ACFT & ENG WITH NO DEFECTS NOTED. ENGINES WERE RUN UP WITH NO DEFECTS NOTED. MX ISSUED A SPECIAL FLT PERMIT FOR FURTHER INVESTIGATION.  NO INFORMATION TO DETERMINE IF THERE WAS FLAME AS WELL AS SMOKE, ASSUMED FIRE REPORTED RESTRICTED TO ONE OR BOTH ENG JETPIPES. REPORT MENTIONS "LT ENGINE FLAMES/FIRE".                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
             20081222     NM  2008       12         22         CA081111003      120081107G56108SC0043014      WINDSHIELD                              DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB OUT, THE CREW WITNESSED THE RT COCKPIT HEATED WINDSHIELD CRACK.  THE CRACK SLOWLY KEPT PROGRESSING TO A LENGTH OF ABOUT 5 INCHES.  THE CREW INITIATED A RETURN TO BASE AND LANDED WITHOUT FURTHER INCIDENT.  MX R&R THE WINDSHIELD.  NO CAUSE AS TO THE FAILURE COULD BE DETERMINED, OTHER THAN IT APPEARS TO HAVE ORIGINATED AT THE EDGE OF THE WINDOW AT A HEATING ELEMENT.  THE TOTAL TIME ON THIS WINDSHIELD COULD NOT BE DETERMINED.                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081222     EA  2008       12         22         CA081111004      120081110G2750                CONTROL UNIT                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) FLAPS SELECTED TO 20 DEGREES FOR TAKE-OFF.  AFTER TAKE-OFF, FLAPS WERE SELECTED TO 8 DEGREES AND THE FLAPS LOCKED AT 20 DEGREES.  FLAP FAIL CAUTION EICAS MSG AS WELL.  FOUND SKEW DETECT FAULT LIGHTS ILLUMINATED, BOX RESET CARRIED OUT ALONG WITH BREAKER RESET.  FLAPS CYCLED NUMEROUS TIMES WITHOUT FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20081229     NM  2008       12         29         CA081111005      120081104G3230483003          SELECTOR VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  MLG             SHORTED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) CREW REPORTED A NOSE STEERING CAUTION ON TAKEOFF. UPON LANDING, ALL 3 GEARS SHOW RED WITH GEAR DOWN SELECTION. ALTERNATE EXTENSION USED IAW QRH. ALL GREEN WITH ALT EXTENSION. FAULT CODES HAVE BEEN RETRIEVED AND ENTERED INTO THERE COMPUTER SYS. MX FOUND A SHORT TO GROUND IN THE UP SOLENOID OF THE LANDING GEAR SELECTOR VALVE.                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081229     EA  2008       12         29         CA081111006      120081020G29169604501         RESERVOIR                               CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5B1   30052NE                              HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) NR3 HYD SYS LOW PRESSURE CAUTION MESSAGE DURING CLIMB. INBD SPOILERS CAUTION MESSAGE ALSO PRESENT DUE TO HYD LOW PRESSURE.  ACFT DECLARED EMERGENCY, ALTERNATE EXTENSION USED TO DEPLOY LANDING GEAR, AND RETURNED TO FIELD.   FLUID LOSS WAS DISCOVERED FROM HYD SYS NR 3 RESERVOIR.  HYD RESERVOIR WAS CHANGED AND ALL SYS TESTED AND FUNCTIONED SATIS. ACFT RETURNED TO SERVICE.  NO P/N`S OR S/N`S AVAILABLE AT THIS TIME. UPDATE: 17-NOV-08, 08:08, "P/N 960450-1 S/N OFF: 239 S/N ON: 484".                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E00063EN             
             20081229     NM  2008       12         29         CA081112001      120081110G3260401020101       PROXIMITY SENSOR                        BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  LT MLG          UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       6338                                                           (CAN) PILOTS REPORT:  AFTER GEAR SELECTED UP, LT MAIN GEAR DOOR REMAINED OPEN WITH AMBER ADVISORY LIGHT. CONTINUED CLIMB NOT ABOVE 185KTS, CONDUCTED AFTER TAKE-OFF CHECKLIST. QRH CONSULTED AND ACTIONED ALTERNATE GEAR EXTENSION.  LINE MX CONFIRMED DEFECT AND INVESTIGATION REVEALED THE `LT GEAR DOOR CLOSED` PROX SENSOR TO BE UNSERVICEABLE. UNSERVICEABLE SENSOR REPLACED WITH A NEW ITEM AND THE INSTALLED SENSOR WAS RIGGED IAW THE ACFT MM.  ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081229     NM  2008       12         29         CA081112002      120080529G571485730800002     SHROUD                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              WING BOX        MISMANUFACTURED W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       9    9                                                         (CAN) DURING PRODUCTION OF 4208 IT WAS DISCOVERED THAT THE CENTER WING LOWER SHROUD RT DRAIN HOLES WERE NOT PRESENT. A DISCREPANCY WAS RAISED AND CLEARED BY DRILLING NEW HOLES IN SITER. UPON THE DELIVERY/ACCEPTANCE FLIGHT, IT WAS DISCOVERED THAT THE AFT COFFEE MARKER WAS UNSERVICEABLE. A TECHNICAL INVESTIGATION REVEALED 6 OF 9 (115 VAC) WIRES DAMAGED. A REPAIR WAS MADE IAW WDM 20-16-00. A SMS/SRS WAS RAISED.                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN             
             20081229     EU  2008       12         29         CA081112003      120081030G75009550170290      PRESSURE SWITCH                         UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  LDLANDING        1                      CA                                                                      AFTER A LANDING AND COOLDOWN THE PILOT PRESSED THE START/DETENT SWITCH TO MOVE THE TWIST GRIP TO CUTOFF. THE ENGINE IMMEDIATELY FLAMED OUT WHEN THE SWITCH WAS DEPRESSED (TWIST GRIP WAS NOT TURNED).  THEN ATTEMPTED TO RECREATE THIS PROBLEM AND IT HAPPENED AT ALL ENGINE SPEEDS. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE P3 PRESSURE SWITCH WAS THE PROBLEM.                                                                                                                                                                                                                                                                                                                                                                       1G72 3U3  UNCR0001RD E34NE                
             20081229     GL  2008       12         29         CA081112004      120081110G5755GT41501009      SPOILER SYS                             BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF AND DURING CLIMB, A LATERAL CONTROL MOVEMENT TO THE LT WAS NOTICED . ONE SPOILERON DEPLOYED ON THE LT WING (2 PAIR OF MULTI-FUNCTION SPOILER (MFS) IAW WING ON THIS ACFT). THE LT NR 2 MFS WAS AMBER LINE ON THE FLIGHT CONTROL SYNOPTIC PAGE. SEVERAL EXTRACT AND RETRACT ACTIONS ON THE SPOILERS SYS PERFOMED, WITHOUT SUCCESS AND AILERON TRIM WAS ADJUSTED TO CORRECT THE ACFT LEVELING. CREW DECIDED TO ABORT THE FLIGHT AND LAND TO THE AIRPORT DEPARTURE .  AFTER LANDING ,THE LT NR 2 MFS WAS STILL FULLY DEPLOYED AND RETRACTED BY ITSELF WITH THE BLEED DOWN OF HYD PRESSURE OF THE SYSTEM. (HYD OFF)                                                                                                             2L72 4F4  FRTT00003NYE00061EN             
             20081229     NM  2008       12         29         CA081112005      120081107G2697FRF6E12S3S      CONNECTOR                               BOEING727   727247      138408FNM  PWA   JT8   JT8D15A     52051NE                              FIRE WARNING SYSDAMAGED         W      F   ACTIVATE FIRE EXT.                                                                              N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AT APPROX 700 FT, AGL T/O YHZ FIRE WARNING LIGHTS ON GLARE SHIELD WERE DIMMLY ILLUMINATED. NO AURAL WARNING. APU FIRE HANDLE ILLUMINATED. SWITCH PULLED AND BOTTLE  DISCHARED.  ACFT RETURNED TO DEPARTURE.   RECTIFICATION AFTER TROUBLESHOOTING FOUND APU FIRE SENSOR/RESPONDER CONNECTOR D1428 SEVERELY CORRODED.  INTERIOR OF CONNECTOR FOUND PACKED WITH GREENISH REDIDUE.  BOTH ENDS OF CONNECTOR (SOCKETS AND PINS) CLEANED AND INSPECTED.  APU FIRE DETECTION SYS TESTED IAW AMM 26-15-00  FOLLOWUP:  REF: WRI 26-11/3077 APU FIRE SENSOR/RESPONDER CONNECTOR D1428 TO BE REPLACE. FOUND CONNECTOR WEATHER GASKET DAMMAGED CAUSING CORRROSION IN SOCKETS.                                                                         2L73 4F4  F  A3WE    E2EA                 
             20081222     SO  2008       12         22         CA081112006      120081106G324540140           TUBE                                    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              MLG TIRE        FLAT            W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AFTER LANDING, IT WAS NOTICED THAT THE NOSEWHEEL WAS FLAT. DISASSEMBLY OF THE NOSEWHEEL HUB SHOWED A POSSIBLE WEAR SPOT BETWEEN THE TIRE AND TUBE.  THE TUBE WAS DAMAGED DURING THE LANDING AND TAXI SO IT IS NOT KNOWN IF THIS WAS THE ACTUAL CAUSE OF THE PROBLEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A20SO   E14EA                
             20081222     NE  2008       12         22         CA081112007      220081031G7200                ENGINE                                  PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A66      52043NE                                              MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) DURING FLIGHT, THE ENGINE LOST TORQUE AND OIL PRESSURE.  THE PILOT SHUT IT DOWN AND PERFORMED A SINGLE ENGINE LANDING.  POST FLIGHT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE EXHAUST.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 3O4  TRTA59EU   E26NE                
             20081229     CE  2008       12         29         CA081112008      120081112G3210130909B19       BOLT            BEECH                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  SUPPORT         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3428                                                           (CAN) SUPPORT ASSY BRACKET ON BOTH SIDES OF THE NLG ACTUATOR PIVOT HAD 5 OF THE 6 BOLT HEADS SHEARED OFF LEAVING THE BOLT SHANK AND CAPTURE NUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
             20081229     EA  2008       12         29         CA081112009      220081031G7200                ENGINE                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              NR 2            FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL180, THE CREW FELT A STRONG JOLT AND VIBRATIONS THROUGH THE AIRFRAME. A QUICK REVIEW OF THE GAGES SHOWED A POWER LOSS ON NR 2 ENG.  THE ENG WAS SECURED AND THE CREW PERFORMED A SINGLE ENGINE LANDING. GROUND INSP FOUND NOTHING OF SIGNIFICANCE AND THE ACFT WAS FERRIED BACK TO BASE. DURING FINAL APPROACH OF THE FERRY FLIGHT, THE ENGINE LOST TORQUE BUT RECOVERED WITHOUT ANY PILOT INPUTS. THE ACFT  LANDED SAFELY AT DESTINATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                       2L72 4T4  TRTA24CE   E4EA                 
             20081229     NE  2008       12         29         CA081112010      220081104G7532                BLEED VALVE                                                                PWA   305   PW305B      52128NE                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  LDLANDING        1                      CA                                                                      (CAN) DURING LANDING, THE ENGINE FLAMED OUT. RE-START ATTEMPT WAS UNSUCCESSFUL. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE COMPRESSOR BLEED VALVE ASSY.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       4  F          E35NE                
             20081229     WP  2008       12         29         CA081112011      120081031G2421                GENERATOR                               DOUG  DC3   DC3C        3021457WP  PWA   PT6   PT6A67R     52043NE  HARTZLHCB5M HCB5MA3     GL  NR 2            INOPERATIVE     W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE CREW OBSERVED THE NR 2 GENERATOR GO OFF LINE WITH AN INCREASE IN ENG TEMP.  IT WAS SHUTDOWN AND A SINGLE ENG LANDING FOLLOWED. POST FLIGHT INSP FOUND THE COMPRESSOR HARD TO ROTATE. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                      2L72 4R4  T  A669    E26NE   6  CP44GL    
             20081229     EU  2008       12         29         CA081112012      120081111G32305322012289      DRAG LINK                               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  MLG             BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9376                                                           (CAN) ON CALL MAINT RECEIVED A PHONE CALL FROM CAPTAIN, PILOT REPORTED HEARING A LOUD NOISE FROM THE NOSE GEAR AREA WHEN DEPARTING THE NORTHERN AIRPORT. HE SAID THE NOSE GEAR TRANSIT LIGHT DID NOT EXTINGUISH AND HE THEN PROCEEDED TO RESWING THE GEAR WHICH THEN CAUSED THE LIGHT TO EXTINGUISH. ON DECENT, HE EXTENDED THE GEAR AND SAID THE NOSE GEAR TOOK LONGER THAN NORMAL TO FULLY EXTEND AND GIVE GREEN DOWN AND LOCKED INDICATION. MX INSTRUCTED HIM TO VISUALLY INSPECT THE NOSE GEAR AND GEAR BAY AND FOUND NOTHING UNUSUAL. THE DESISON WAS MADE TO RETURN TO DEPARTURE WITH THE GEAR EXTENDED.  MX WAS THERE TO MEET THE ACFT WHEN IT RETURNED. THE ACFT WAS HANGERED AND PLACED ON JACKS. MX THEN DID A GEAR SWING AND THE NOSE1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081229         2008       12         29         CA081113001      420081113G34600710159803      CONTROLLER                              PILATSPC12  PC1247      7090552EU  PWA   PT6   PT6A67      52043NE                              MFD             FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       147  147                                                       (CAN) WE HAVE JUST EXPERIENCED THE 4TH FAILURE OF THE KMC 2220 MFD CONTROLLER.   THE JOYSTICK FUNCTION FAILS TO ALLOW CURSOR MOVEMENT ON THE FLIGHT SCREENS AND DOES NOT ALLOW FLIGHT CREWS TO ENTER OR MODIFY ROUTING IN FLIGHT.  THE REPLACEMENT UNIT CLEARED PROBLEM FOR NOW.   HAVE BEEN TOLD MFG IS LOOKING INTO THE PROBLEM AS WE ARE NOT THE ONLY CUSTOMER HAVING THIS ISSUE.                                                                                                                                                                                                                                                                                                                                                            1L71 4T4  TRTA78EU   E26NE                
             20081229         2008       12         29         CA081113002      220081113G7497                WIRE                                                                                                                                    MAGNETO         CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COIL TO POINTS WIRE WORN THROUGH TO STRANDS DUE TO RUBBING ON FRAME OF DISTRIBUTOR BLOCK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
             20081229         2008       12         29         CA081113003      220081022G7414K3822           DISTRIBUTOR GEAR                                                                                                                        MAGNETO         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DISTRIBUTOR FINGER LOOSE ON GEAR ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
             20081229     NM  2008       12         29         CA081113004      120081112G7500ZZ84M46P01      DUCT                                    EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              BLEED AIR SYS   SPLIT           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT PRECOOLER INLET RUBBER DUCT SHOWS SIGNS WHERE THE SEAM HAS COME APART, AS A RESULT THE FAN AIR HAS FROM THE SPLIT SEAM HAS CAUSED DAMAGE TO THE THRUST REVERSER HEAT SHIELD. T/R FIRE BLANKET PN 104M1031-22, SN6011203-013 THIS HAS ALSO OCCURRED ON ACFT FIN 317 C-FHKI SN 190-0052 AND FIN 342.C-FNAP SN 190-00142.                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA57NM   E00070EN             
             20081229     EA  2008       12         29         CA081113005      120081112G27518004301         DETECTION SYS                           CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              FLAP SYSTEM     FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       18700                                                          (CAN) FLAP FAIL, SELECTED 20, FAILED AT 8 DEGREES. ON APPROACH, CREW UNAWARE OF OAT DUE TO WORK LOAD.   FLAP SKEW DETECTION UNIT REPLACED IAW AMM 27-51-15, PG 401. FLAPS CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20081230     SO  2008       12         30         CA081113006      120081107G324606104700        WHEEL                                   PIPER PA34  PA34200     7103405SO  LYC   O360  IO360C1E6   41514EA  HARTZLHCC2Y HCC2YK2     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6560                                                           (CAN) DURING A TIRE CHANGE, THE AME NOTICED A 4 INCH CRACK ALONG THE WHEEL, WHERE THE TIRE BEAD SITS. THIS TYPE OF FINDING IS RATHER UNUSUAL AT THE AMO. NO HARD OR UNUSUAL LANDINGS WERE REPORTED. THE WHEEL HALF WAS REPLACED, AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A7SO    1E10    5  CP920     
             20081230     SW  2008       12         30         CA081113007      120081104G6420407012108101    BUSHING                                 BELL  407   407         1182206SW                                                               PITCH HORN ASSY DEFORMED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WASHER BETWEEN THE T/R PITCH HORN AND PITCH LINK FOUND DEFORMED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U    O H2SW                         
             20081230     SW  2008       12         30         CA081113008      120081016G6210206010200133    TAB                                     BELL  206   206B        1181511SW                                                               ROTOR BLADE     DEFORMED        W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA       11                                                             (CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND THAT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TRIM TAB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U      H2SW                         
             20081230     NM  2008       12         30         CA081114001      120081113G3297464605          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  PROXIMITY SWITCHSHORTED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) CREW SELECTED GEAR DOWN AND GOT 3 GREENS AND LT MLG DOOR AMBER LIGHT.  ALTERNATE EXTENSION C/O AND CREW OBSERVED ALTERNATE INDICATION SHOWED LT MLG (UNSAFE). CREW DECLARED EMERGENCY AND LANDED. PAX DEPLANED ON RUNWAY AND AFTER GEARS WERE PINNED ACFT TAXIED TO GATE. FAULT CONFIRMED BY PSEU TO BE LT LGDNLK2 OPEN CIRCUIT.  PROXIMITY SWITCH HARNESS ASSY PN 46460-5 REPLACED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081230         2008       12         30         CA081114002      420081111G34134067644901      INDICATOR                               DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  IVSI            FAILED          W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKOFF, CAPTAINS SIDE IVSI FAILED, ACFT RETURNED TO AIRPORT - IVSI REPLACED AND FUNCTION CHECK SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     GL  2008       12         30         CA081114003      120081112G27202227271300      PEDAL                                   DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3313                                                           (CAN) DURING ROUTINE INSP THE RUDDER PEDAL WAS FOUND CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081230     NE  2008       12         30         CA081114004      120081103G6320S613522032001   GEARBOX                                 SKRSKYS61   S61N        8142104NE                                                               MAIN ROTOR      MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA  CFCLM                                                               (CAN) MGB HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB AND RETURNED IT TO MANUFACTURER WHO DISASSEMBLED THE MGB TO FIND THAT THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT, P/N: S6135-22032-001  THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT.                                                                                                                                                                                                                                                                                                                                                                                                              2G72 4U      1H15                         
             20081230     NE  2008       12         30         CA081114005      220081104G72308934825         IMPELLER                                SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   29073NE                              COMPRESSOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2407                                                           (CAN) HOT SECTION INSPECTION WAS BEING CARRIED OUT BY ENGINE SHOP ON ENGINE SN P44659C AND IT WAS NOTED THAT THE IMPELLER WAS CRACKED. THIS IMPELLER IS NOT TRACKED. THE TIMES ON THE IMPELLER SINCE INSTALL ARE 2407.0 AND 3434 CYCLES. THIS IS NOT THE 1ST INSTANCE OF PROBLEMS IN THIS 2ND STAGE IMPELLER.                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA8SW    E4WE                 
             20081230         2008       12         30         CA081114006      220081113G7200SB3208A1        BEARING                                                                                                                                 ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RECEIVED NEW BEARING FROM WHS 290 WITH CORROSION ON BEARING JOURNAL AND ROLLERS. CURE DATE ON PACKAGE IS 0206, BEARING PN SB3208A-1. BATCH PN 0605118341.  HSI HAVE BEEN INFORM OF VARIOUS BEARINGS DELIVERED THAT HAVE SIGNS OF CORROSION ON THEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 
             20081230     NM  2008       12         30         CA081114007      120081114G571085720013006     STRUCTURE                               DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT WING LE      DAMAGED         W      O   OTHER                                                                                           C  F.O.D.                                                                        LDLANDING        1                      CA       45006                                                          (CAN) BIRD STRIKE ON LANDING RT WING ENGINE AREA.  LE NR 3,  ACFT INSPECTED IAW AMM 05-50-26. IMPACT DAMAGE CONCENTRATED AT RT NR 3 LE.  RT NR 3 LE REPLACED IAW AMM, LEAK AND FUNCTION CHECKED.  SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     EA  2008       12         30         CA081114008      120081113G5714                FASTENER                                DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  WING BOX        LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5636                                                           (CAN) DURING INSP, THERE WAS SEVERAL CHERRY MAX RIVETS FOUND TO BE LOOSE ON THE UNDERSIDE OF THE RT WING BETWEEN STATION 35.15 AND 97.50. THE RIVETS WERE ALL LOCATED ON A TRIPLE ROW OF RIVETS AT THE AFT SPAR. FURTHER INSPECTION REVEALED A TOTAL OF 160 RIVETS NEEDING REPLACEMENT. THE RIVETS WERE REPLACED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                              1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20081230     NM  2008       12         30         CA081114009      120081112G5310                STRUCTURE                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  FUSELAGE        DAMAGED         W      O   OTHER                                                                                           C  F.O.D.                                                                        DEDESCENT        1                      CA                                                                      (CAN) FLT ENCOUNTERED MULTIPLE BIRD STRIKES AT 4000 FT, DURING AN APPROACH FOR LANDING INTO AIRPORT. CREW CONTINUED ON DESCENT PATH AND LANDING UNEVENTFUL. MX REQUESTED. SUBSTANTIAL DAMAGE TO THE RT SIDE OF RADOME AND STRUCTURE IMMEDIATELY BEHIND RADOME FROM IMPACT OF GOOSE. ALSO EVIDENCE OF ANOTHER GOOSE HAVING STRUCK THE LT SIDE OF ACFT. POINT OF IMPACT BEING JUST ABOVE LT ENGINE INTAKE. GOOSE HAD SUBSEQUENTLY ENTERED INTAKE AND EXITED THROUGH THE OPEN ENG INTAKE BYPASS DOOR THAT WAS DAMAGED AS WELL.  ACFT INSPECTED IN AIRPORT. RADOME REPLACED AND ACFT WAS THEN FERRIED TO MX BASE, UNDER A FERRY FLT PERMIT. RADOME REMOVED AGAIN TO FACILITATE REPAIRS TO BULKHEAD ON NOSE BEHIND RADOME. WEATHER RADAR ALSO REPLACE2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230         2008       12         30         CA081115001      420081112G2312G340ENI         CONTROL HEAD                            CVAC  340   340CVAC     242270AWP  ALLSN 501D  501D13D     03004GL  ALLSN A6441 A6441FN606  GL  COCKPIT         CONTAMINATED    W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH COM BECAME TEMPORARILY UNUSABLE DUE TO WATER CONTAMINATION IN COMM CONTROL HEAD. PART REMOVED AND DRIED OUT AND FUNCTION TESTED SERV, NO FURTHER PROBLEMS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4R4  T  6A6     E282    6  CP898     
             20081230     EA  2008       12         30         CA081117002      120081114G2750865D1007        DRIVE SYSTEM                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) FLAP FAIL MESSAGE AFTER SELECTING FLAP, FLAPS FAILED AT 8 DEGREES.  ACFT LANDED SAFELY WITH FLAPS AT 8 DEGREES.   REPLACED PDU, COMPLETED FLAP TORQUE CHECK, CHECKED FOR ACTUATOR OVER TEMP IAW AMM 27-52-01-000-8001 AND AMM 27-53-00-750-802. FLAP SYS CHECKS SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20081230     SW  2008       12         30         CA081117003      120081113G801231057463        IGNITION SWITCH                         SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE3311     01514WP  MCAULY4HFR344HFR34C652  NE  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ACFT DEPARTED AIRPORT AND CREW NOTICED SMOKE IN THE CABIN. THE CREW TURNED THE TEMP CONTROLLER OFF - THE BLEEDS WERE TURNED OFF WHICH DUMPED THE CABIN PRESSURIZATION.  THE LOW OIL PRESSURE LIGHT CAME ON ALONG WITH THE EGT STARTING TO RISE.  ENGINE WAS THEN SHUTDOWN AND FEATHERED AT THIS POINT. ACFT RETURNED TO POINT OF ORIGIN AND LANDED WITHOUT INCIDENT. MX WAS CONTACTED AND THEY DISCOVERED THE AUTO IGNITION SWITCH WAS CRACKED ALLOWING THE ENGINE OIL TO BLEED OUT OF THE ENGINE. THE SWITCH WAS REPLACED - GROUND RUNS CARRIED OUT IAW EMM AND ACFT RETURNED TO SERVICE.                                                                                                                                                2L72 4T3  TRTA8SW    E3WE    6  C3PNE     
             20081230     EU  2008       12         30         CA081117004      120081114G6700ASNA013735E2    BEARING RACE                            SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              INNER R ACE     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) A 12 YEAR INSP WAS BEING CARRIED OUT ON THE HELICOPTER.  2 CRACKS WERE FOUND ON THE INNER RACE OF A BALL BEARING ASSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 RIVETS TO THE PILOT`S CYCLIC FOR AND AFT TORQUE TUBE LOCATED UNDER THE CABIN FLOOR. THIS IS THE SECOND 12 YEAR INSPECTION FOR THIS HELICOPTER.                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H9EU    E19EU                
             20081230         2008       12         30         CA081117005      420081113G2210103791101       CIRCUIT BOARD                           BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  AUTOPILOT       INTERMITTENT    W      H   DEACTIVATE SYST/CIRCUITS                                                                        J  WARNING INDICATION                                                            CLCLIMB          1                      CA            428                                                       (CAN) ACFT IN NORMAL CLIMB CONFIGURATION WITH FCS DISPLAYING CLIMB (GREEN) AND ALT ARM (WHITE.) THE VERTICAL MODE DISPLAY MAY THEN CHANGE TO ALT (GREEN) EVEN THOUGH THE TARGET ALTITUDE IS SEVERAL THOUSAND FT ABOVE (E.G. WITH THE ALT SELECT SET FOR 20,000 FEET, THRU, SAY, 12,000 FT THE VERTICAL MODE WILL CHANGE FROM CLIMB TO ALT) WITH THE VERTICAL MODE IN ALT AND STILL SEVERAL THOUSAND FT BELOW SELECTED ALTITUDE THE ACFT WILL BEGINNING PITCHING UP SEVERAL DEGRESS (+10 DEGREES OR HIGHER) REQUIRING AUTOPILOT DISCONNECT, RESET AND MONITORING BY THE PILOT. ALTITUDE ALERTER REMOVED FOR INSP.   INTERNAL PRINTED CIRCUIT BOARD IDENTIFIED AS THE PROBLEM SOURCE AND SUBSEQUENTLY REPLACED.                                   1L72 4T4  T  A24CE   E4EA    5  CP10NE    
             20081230     EA  2008       12         30         CA081117006      120080926G7160CT2EC10221      YOKE                                    DHAV  DHC2  DHC2MK3     2800107EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  INTAKE          BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSP, THE YOKE LT INTAKE COWL BROKE AT MACHINED LOCKING TAB EAR CUT OUT UPON INSTALLATION WHILE RIVETING, LT YOKE-INTAKE COWL WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T4  T  A806    E4EA    6  CP15EA    
             20081230     SO  2008       12         30         CA081117007      220081115G8530                CYLINDER                                                                   CONT  O300  O300C       17022SO                              NR 3            CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) NR 3 CYLINDER ASSY WAS FOUND CRACKED BETWEEN THE CYLINDER HEAD AND THE BARREL, APPROX .7500 AROUND THE CICUMFERENCE OF THE ASSY. THIS RESULTED IN LOSS OF COMPRESSION AND ENGINE VIBRATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      3  O          E253                 
             20081230     CE  2008       12         30         CA081118001      120081115G3040MS24166DI       RELAY           BEECH                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  WINDSHIELD HEAT UNSERVICEABLE   W      H   DEACTIVATE SYST/CIRCUITS                                                                        MJ OVER TEMP                 WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) CREW DEFECT PILOT WINDSHIELD HEAT NOT WORKING, TROUBLESHOOT TO LOW HEAT RELAY, TERMINAL A2 MELTED OFF THE RELAY ASSY, DAMAGING WIRES ATTACHED TO THE TERMINAL APPROX 3 INCHES BACK THE WIRE COVER MELTED OFF. RELAY WAS REPLACED AND SYS OPERATES PROPERLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20081230     SW  2008       12         30         CA081118003      120081103G7603701981          LOCK TAB        AIRTRC                  AIRTRCAT500 AT502B      0390307SW  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  POWER LEVER     CRACKED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       4325                                                           (CAN) FCU FUEL CONDITION LEVER LOCK SPRING TAB THAT IS USED TO PREVENT THE LEVER MOVING TO FUEL CUT-OFF HAS FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TNCA17SW   E4EA    6  CP15EA    
             20081230     NM  2008       12         30         CA081118004      120081116G291082970009325     LINE                                    DHAV  DHC8  DHC8201     2809001NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  NR 2 HYD SYS    CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA       24324                                                          (CAN) ON DESCENT AT NIGHT IN HEAVY RAIN, FLIGHT CREW GOT NR 2 HYD PUMP CAUTION FOLLOWED BY TOTAL LOSS OF QUANTITY IN NR 2 HYD SYS.  LEVELED AT F110 FOLLOWED QRH, DECLARED PAN, BRIEFED F/A AND PASSENGERS ON RETURN TO BASE FOR NORMAL LANDING WITH PRECAUTIONARY SERVICES IN ATTENDANCE. LINE MAINT INVESTIGATION AND CONFIRMED DEFECT, TRACED LEAK TO `RIGID LINE` P/N  82970009-325. WALL OF LINE FOUND CRACKED ADJACENT TO AN END FITTING. RIGID LINE REPLACED WITH NEW ITEM. AS ENGINE DRIVEN HYD PUMP WAS RUN IN FLIGHT FOR LONGER THAN FIFTEEN MINUTES, IT WAS ALSO REPLACED AS REQUIRED BY ACFT MANUAL. ALL SYS FUNCTIONED IAW THE AIRCRAFT`S MM.  THE ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     GL  2008       12         30         CA081118005      120081117G2720                TUBE                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  RUDDER PEDAL    WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4521                                                           (CAN) INSP OF THE RUDDER PEDAL ASSY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUBBER CABLE. THE WEAR WAS DETECTED BY VISUALLY CHECKING THE OUTSIDE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA WHERE THE CABLE CAUSES THE MOST FRICTION ON THE INSIDE OF THE TUBE. THE RUDDER PEDAL ASSY AND CABLE WERE REPLACED WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081230     NM  2008       12         30         CA081118006      120081114G322082253           TUBE            MESSIER     8200103     DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NLG             BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ON SELECTING LANDING GEAR DOWN-PILOT REPORTED A LOUD CRACKING NOISE FROM THE NLG AREA. COULD NOT CONFIRM THAT THE GEAR WAS DOWN AND LOCKED USING NORMAL OR ALTERNATE VERIFICATIONS. AN EMERGENCY LANDING WAS MADE SUCCESSFULLY AFTER A FLYBY INSP SHOWED THAT THE NLG WAS EXTENDED.  ACFT MADE A SUCCESSFUL LANDING AND WAS SECURED ON NOSE JACK INSPECTED . INSP REVEALED THAT THE PIVOT TUBE HAD CRACKED AND THAT THE DOWN LOCK HAD NOT GONE FULLY OVERCENTER. PART REPLACED AND ACFT WAS REMOVED OFF THE RUNWAY. AN PHYSICAL INSP OF THE PIVOT TUBE REVEALED THAT THIS WAS A PRE-MOD PIVOT TUBE AND NOT IAW AD CF-95-15. MFG`S ARE INVESTIGATING THE EVENT.                                                                            2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     CE  2008       12         30         CA081118008      120081115G33101015245001      PANEL                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  COCKPIT         SMOKE           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA       1488214882                                                     (CAN) ACFT RETURNED SHORTLY AFTER DEPARTURE DUE TO AN ELECTRICAL ODOR AND A WISP OF SMOKE AT THE CO-PILOTS CONTROL WHEEL. IT LASTED FOR A FEW SECONDS AND THEN DISAPPEARED. MX INSPECTED THE ACFT UPON ARRIVAL AND FOUND THAT THE EDGE-LIGHTED PANEL AT THE CO-PILOTS CLOCK WAS AT FAULT. THE LIGHTING WAS DISABLED AND DEFERRED IAW THE MEL UNTIL REPLACEMENT PARTS ARRIVE. THE AREA WAS INSPECTED AND ADJACENT SYS TESTED WITH NO ADDITIONAL FAULTS NOTED AND THE ACFT RELEASED.                                                                                                                                                                                                                                                              1L72 4T4  T  A24CE   E4EA    6  CP15EA    
             20081230     SW  2008       12         30         CA081118010      120081118G71205082119         MOUNT                                   AIRTRCAT602 AT602       0390309SW  PWA   PT6   PT6A65AG    52043NE  HARTZLHCB5M HCB5MP3     GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2498                                                           (CAN) DURING THE 300HR/ANNUAL INSP,  ENGINE MOUNT WAS BEING INSPECTED IAW AD2008-10-12 AND AIR TRACTOR`S SL NR 253C, A CRACK WAS FOUND ON THE LT LOWER ENGINE ATTACH POINT VIA 10X MAGNIFYING GLASS.  ACFT HAS BEEN NOTIFIED ABOUT THE CRACK AND A NEW ENGINE MOUNT HAS BEEN SINCE INSTALLED WITH THE GUSSET UPGRADE IAW AD2008-10-12 AND SL NR 253C WHICH WAS SUPPLIED BY THE MFG.                                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TNCA19SW   E4EA    6  CP44GL    
             20081230     NM  2008       12         30         CA081119001      120081119G5330                SKIN                                    EMB   ERJ170ERJ170100SE 3260406NM                                                               FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACKS WERE SUSPECTED AFTER GVI AND CONFIRM BY NDT RADIATING FROM ONE FASTENER HOLE IN LT FUSELAGE SKIN PANEL AT FRAME 94 STR 03 AND 04 LT AND SAME AT FRAME 94 STR 03 AND 04 RT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA56NM                        
             20081230     EA  2008       12         30         CA081119002      120081118G2751800440304       PROXIMITY SENSOR                        CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) FLIGHT WAS SET UP FOR LANDING AND SELECTED FLAPS TO 8 DEGREES. FLAPS ON 1 SIDE CAME DOWN TO 2 DEGREES AND FLAPS ON THE OTHER SIDE REMAINED AT 0 DEGREES. AN EMERGENCY WAS DECLARED AND PASSENGERS WERE BRIEFED. FLIGHT LANDED WITHOUT FURTHER INCIDENT AND STOPPED ON RUNWAY FOR FIRE CREWS TO DO A WALK AROUND AND THEN TAXIED TO THE GATE. MX TROUBLESHOOTING IAW FAULT CODES AND SKEW DETECTOR INDICATION LED TO REPLACEMENT OF THE LT L3 (P/N 8044-04, S/N 2676) AND L4 (P/N 80-044-03, S/N 2676) SKEW DETECTOR PROXIMITY SENSORS. FLAP OPERATION AND SKEW DETECTOR SYS OPS CHECKS CARRIED OUT WITH NO FURTHER FAULTS AND THE ACFT WAS RETURNED TO SERVICE.                                                                           2L72 4F4  FRTA21EA   E15NE                
             20081230     NE  2008       12         30         CA081119003      220081118G72610292507350      BEARING                                 SNIAS 350   AS350B      8680801EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENGINE          BLOCKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3412 660                                                       (CAN) OIL WAS COMING OUT OF TURBINE EXHAUST AND M03 BEARING VENT TUBE ON START UP. DISASSEMBLED THE ENGINE AND FOUND M03 REAR BEARING CAKED WITH BURNED OIL. M03 REAR BEARING OIL RETURN TUBE PARTIALLY BLOCKED WITH BURNED OIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E19EU                
             20081230     NM  2008       12         30         CA081119004      120081118G2750MS391130Z       MOTOR                                   BOEING727   727225      1384077NM  PWA   JT8   JT8D9A      52048NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      (CAN) ENROUTE, SYS A HYD QTY DROPPED TO ZERO.  MX FOUND OTBD FLAP HYD MOTOR FAILED.  MOTOR REPLACED AND SYS CHECKED SERVICABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F4  F  A3WE    E2EA                 
             20081230     EU  2008       12         30         CA081120001      120081119G2560SL12            BUCKLE          GROB                    GROB  G115  G115C       1660303EU  LYC   O320  O320D1A     41508EA                              SEAT BELT ASSY  UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       437                                                            (CAN) BUCKLE WOULD NOT RELEASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA57EU   E274                 
             20081230     CE  2008       12         30         CA081120002      120081118G2840                MONITOR                                 BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  MCAULY4HFR344HFR34C762  NE  FUEL QTY        FAULTY          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PILOT REPORT ERRATIC ON FUEL QTY INDICATION. TROUBLESHOOTING REVEALED FAULTY CONTROL MONITOR.  MONITOR REPLACED BY REPAIRED UNIT THAT FAILED 2 DAYS LATER, REPLACED WITH OTHER ONE FROM SAME VENDOR THAT DOESN`T WORK, SWAPPED WITH AN SERVICEABLE UNIT FROM AN OTHER ACFT (FLTS) TO CONFIRMED TROUBLESHOOTING. IT TAKES 3 DIFFERENT UNIT TO FINALLY FIXED THE PROBLEM.                                                                                                                                                                                                                                                                                                                                                                   1L72 3T4  T  A14CE   E4EA    6  C3PNE     
             20081230     NM  2008       12         30         CA081120003      120081107G3240900005831PR     BRAKE SYS                               EMB   ERJ170ERJ170200SU NIR    NM  GE    CF34  CF348E5A1   30062NE                              MLG             DISINTEGRATED   W      D   RETURN TO BLOCK                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING PUSHBACK, GRND PERSONNEL REPORTED SMOKING BRAKES. FOUND NR3 BRAKE ROTORS HAD FAILED. REPLACED BOTH NR3 WHEEL AND BRAKE ASSY IAW AMM 32-49-05 AND 32-49-11.  S/N OF THE BRAKE IS JAN05-0530.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA56NM   E00063EN             
             20081230     SW  2008       12         30         CA081120004      120081116G6220K974004107      MOUNT                                   KAMAN K1200 K1200       05625F6SW  LYC   T53   T5317A      41549NE                              M/R HEAD        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 4F4  UNTTR7BO   E17EA                
             20090102     NE  2009       1          2          CA081120005      220081106G7532BRH10211        BLEED VALVE                             BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              ENGINE          BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENG WAS REMOVED IN UNSERVICEABLE CONDITION DUE TO BOOSTER BLEED VALVE MECHANISM MALFUNCTION.  ENG IN RRC FOR REPAIR.  DURING INITIAL INSP, IT WAS CONFIRMED THAT BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-400) WAS NOT OPERATING PROPERLY. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER BLEED VALVE MECHANISM AND IT WAS NOTED THAT ONE PIN (ATA 72-38-19 01-408) AND ONE RETAINING RING (ATA 72-38-19 01-409) WERE MISSING. THIS PIN IS AT THE CONNECTION BETWEEN THE BELL CRANK LEVER ASSY (ATA 72-38-19 01-100) AND THE BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-409) AT TOP DEAD CENTER POSITION (ACTUATING ROD POSITION).  (6) REMAINING PINS 2L72 4F4  FTRA6WE    E00061EN             
             20081230     EU  2008       12         30         CA081120006      120081119G6220350A37116200    STOP                                    SNIAS 350   AS350B2     8680813EU  LYC   LTS101LTS101*          NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2834                                                           (CAN) CRACK DISCOVERED ON 2 OF THE 3 YOKE, STOP, ASSYS REMOVED FROM THE ACFT DURING NDT. THE CRACKS ARE ALLONG THE SECOND RADIUS FROM THE TOP, AND WERE NOT VISIBLE TO THE NAKED EYE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E5NE                 
             20081230     EU  2008       12         30         CA081120007      120081119G6220350A37116200    STOP            SNIAS                   SNIAS 350   AS350B1     8680811EU                                                               ROTOR SHAFT     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10002                                                          (CAN) CRACK DETECTED IN 2 OF THE 3 YOKE, STOP, ASSYS ON THE MAST. FOUND DURING A 6 YEAR CORROSION INSPECTION OF THE MAST. THE PARTS WERE SENT FOR NDT AS PART OF THE AVIATION INSP PROCEDURES FOR THE MAST ASSY (NO MFG REQUIREMENT IN THE TECHNICAL PUBLICATIONS TO NDT THESE PARTS). CRACK NOTED IN THE SECOND RADIUS FROM THE TOP.                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U      H9EU                         
             20081230         2008       12         30         CA081121001      420081120G34207004544314      SYMBOL GENERATOR                        DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 1            FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       30171458                                                       (CAN) SHORTLY AFTER TAKEOFF, THE CAPT`S PRIMARY FLIGHT DISPLAYS WERE MALFUNCTIONING, CAPTS EADI AND EHSI ARE BLANKING OUT INTERMITTENTLY , CREW ELECTED TO RETURN TO ORIGINATING AIRPORT.  MX REPLACED NR 1 SYMBOL GENERATOR AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     EA  2008       12         30         CA081121002      120081120G2750855D1009        CONTROL UNIT                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        FAILED          W      D   RETURN TO BLOCK                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       2777027770                                                     (CAN) DURING PUSH BACK FROM THE GATE, FLAP LEVER WAS MOVED TO 8 DEGREES BY THE FLIGHT CREW BUT THE FLAP DIDN`T EXTEND AND "FLAP FAIL" CAUTION MESSAGE APPEARED ON THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS). THE ACFT WAS TOWED BACK TO THE GATE. FLAP ELECTRONIC CONTROL UNIT (FECU) FAULT CODES WERE RETRIEVED AND DECISION WAS MADE TO REPLACE THE RT BRAKE POSITION SENSOR UNIT (BPSU). THE UNIT WAS REPLACED AND THE ACFT RETURNED INTO SERVICE.                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
             20081230     NM  2008       12         30         CA081121003      120081119G21508209063         ACM                                     BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  RIGHT           ODOR            W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE F/A CALLED TO REPORT SMELL AND MIST. ASKED FOR AN UPDATE IF IT WORSENED, THEN PREPARED FOR OXYGEN DRILL IAW QRH. ON APPROACH TO LAND THE (CABIN PACK HOT CAUTION) LIGHT CAME ON. THE QRH WAS CONSULTED AGAIN AND THEN THE CAUTION LIGHT WENT OUT. WE THEN LANDED AND COMPLETED THE FLIGHT NORMALLY.  ON-SITE LINE MX INVESTIGATION IDENTIFIED THE RT (CABIN) AIR CYCLE MACHINE (ACM) TO BE NON-OPERATIONAL DUE BEING SEIZED. FUNCTIONAL CHECK AIR CONDITIONING SYS SATISFACTORY WITH FLIGHT COMPARTMENT PACK ONLY WITH TEMP COMTROL AT 1 O`CLOCK POSITION. ACFT POSITIONED BACK TO MX BASE UNDER MEL 21-50-1PROVISIONS. ACM REPLACED AND TESTED IAW THE MM 21-51-21. ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.         2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081230     EU  2008       12         30         CA081121004      120081121G5751                SEAL                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  LT AILERON      SPLIT           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7654 7654                                                      (CAN) THE AILERONS WERE REMOVED AT THE ANNUAL INSP FOR BEARING REPLACEMENT. A SMALL RIP WAS FOUND IN THE INNER SEAL OF THE LT AILERON WHICH ATTACHES BETWEEN THE WING AND THE AILERON BALANCE WEIGHT ATTACHMENT. WHEN THE MS35207-XXX SCREWS WERE REMOVED THE WERE FOUND TO BE CORRODED. THE AREA WAS INSPECTED FOR CORROSION CLEANED AND NEW SCREWS INSTALLED WITH CPC GRADE 2 COMPOUND. THE RT AILERON WAS INSPECTED AND FOUND WITH SIMILAR CORROSION.                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20081230     CE  2008       12         30         CA081121005      120081119G243523080023A       STARTER GEN                             LEAR  35    31A         5170531CE  GARRTTTFE731TFE73123B        WP                              NR 1            FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA            235                                                       (CAN) GENERATOR FELL OFF, INE AND A SLIGHT VIBRATION WAS FELT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA10CE   E6WE                 
             20081230     GL  2008       12         30         CA081121006      120081120G27202227271200      TUBE                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  RUDDER PEDAL    WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2794                                                           (CAN) DURING THE ACFT PRE-FLIGHT THE PILOT REPORTED THAT THE RUDDER PEDAL ASSY ON THE RT SIDE WAS DIFFICULT TO ADJUST ALONG THE SLIDE TUBE ASSY. CLOSER INSPECTION BY MAINT REVEALED THAT THE RT OTBD FWD RUDDER CABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TO THE PEDAL ASSY.  CABLE WAS EXPOSED THROUGH THE LOWER BEND OF THE S-TUBE TO A POINT WHERE IT WAS JAMMED IN ITS WEAR HOLE THUS RESRICTING THE SLIDE ACTION OF THE PEDAL ASSY. THE DEFECTIVE PARTS ARE BEING REMOVED FOR REPLACEMENT WITH NEW.                                                                                                                                                                                                                                1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081230     GL  2008       12         30         CA081121007      120081107G29101005354226007   LINE                                    BOMBDRBD100 BD1001A10   1390044GL                                                               HYDRAULIC SYS   CHAFED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA       5443                                                           (CAN) ACFT LOST ALL HYD FLUID IN THE RT SYS DURING FLIGHT. NO INFO ON FLIGHT PROFILE, CAS MESSAGES OR QTY`S NOTED.  CREW UNAVAILABLE FOR DEBRIEF AT THIS TIME. REPLACED AFFECTED LINE, CLAMP AND HARDWARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTT00005NY                     
             20081230     GL  2008       12         30         CA081121009      120080711G29101005354226007   LINE                                    BOMBDRBD100 BD1001A10   1390044GL                                                               HYDRAULIC SYS   CHAFED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       5162                                                           (CAN) DURING CRUISE FLIGHT, THE AMBER (R HYD PRESS LOW) CAS MESSAGE ILLUMINATED. PILOT OBSERVED THE HYD SYNOPTIC PAGE AND NOTED THE FLUID LEVEL IN THE RT HYD RESERVOIR BEGAN DROPPING. ACFT BEGAN DESCENT. DURING APPROACH, PILOT NOTED THE RT HYD RESERVOIR QUANTITY WAS READING (4 PERCENT). AFTER LANDING, VISUAL INSP OF THE ACFT REVEALED HYD FLUID STREAMING FROM THE WHEEL WELL AREA TO THE TAIL OF THE ACFT.  FOUND LINE IN THE AFT EQUIPMENT BAY HAD A HOLE CHAFED INTO IT BY A FAIRLEAD BLOCK.                                                                                                                                                                                                                                       2L72 4F    RTT00005NY                     
             20081230         2008       12         30         CA081121010      120081119G341120131421B       STATIC LINE                                                                                                                             PITOT/STATIC SY UNBONDED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FITTING GLUE AND LINE GOING TO IT IS ALUMINUM WITH A COMPRESSION FITTING WHEN LINE WAS TIGHTEN TO ENSURE NO STATIC LEAK THE GLUE THAT ADHEARS THE FITTING LET GO THIS SUBMITTED ON BEHALF OF SKYLINE MAINT AND AVIONICS AMO 21-80.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20081230     NM  2008       12         30         CA081121011      120081120G3230656021132       ACCESSORY UNIT                          BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              MLG             FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) JUST AFTER TAKEOFF, THE CREW ATTEMPTED TO SELECT GEAR UP, THE GEAR HANDLE WOULD NOT GO PAST THE OFF POSITION.  ACFT RETURNED TO WHERE MAINT REPLACED THE LANDING GEAR ACCY UNIT. A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F4  F  A3WE    E2EA                 
             20081230     EU  2008       12         30         CA081121012      120081120G2913S40             COUPLING SLEEVE                         SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              HYD PUMP        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING DISASSEMBLY FOR OTHER WORK THE HYD PUMP WAS REMOVED AND THE SPLINE DRIVE WAS FOUND EXTREMELY WORN. PART S40 WAS FOUND TO HAVE ALMOST NO SPLINE AT ALL REMAINING AND THE JOINING HYD PUMP PN A5026780 HAD IT`S SPLINES WORN TO HALF THEIR NORMAL WIDTH. THERE IS ALREADY AN AD CF2004-10 AND AN SB 29.00.04 ON THIS ISSUE. ESTIMATED TIME TO FAILURE OF HYD DRIVE WAS LESS THAT 100 HOURS.                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H9EU    E19EU                
             20081230     NM  2008       12         30         CA081122001      120080929G5312                BULKHEAD                                BOEING727   727225      1384077NM  PWA   JT8   JT8D9A      52048NE                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING WALK-AROUND INSP, FOUND BELTFRAME AT 9G BULKHEAD CRACKED BY LT CARGO CAN CUTOUT. TEMPORARY REPAIR CARRIED OUT. A/C FERRIED. PERMANENT REPAIR CARRIED OUT.  ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  F  A3WE    E2EA                 
             20081230     EA  2008       12         30         CA081122002      120081117G2752852D10021       ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA                                                               TE FLAPS        FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       2078                                                           (CAN) FLAP FAIL IN APPROACH WHEN SELECTED FROM 0 DEGREE. FLAP FAILED AT 0 DEGREE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA21EA                        
             20081230     EA  2008       12         30         CA081122003      120081117G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA                                                               TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) DECENDING THROUGHT 10,000 FT, FLT CREW REPORTED FLAP FAIL MSG WITH FLAPS AT 0 DEG, AIRSPEED WAS 250 KTS.  QRH FOLLOWED AND ACFT LANDED WITHOUT FURTHER INCIDENT.  COMPLIED WITH FLAP RESET IAW SUPPLEMENT 98-018B (CB RESET) AND FLAPS OPS CHECKED NORMAL. ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA21EA                        
             20081230     EA  2008       12         30         CA081122004      120081116G2742AV67023105      ACTUATOR                                CNDAIRCL600 CL6002C10   1390015EA                                                               HORIZONTAL STAB LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AV670-23105-003 (LT) AND -004 (RT)  DURING ROUTINE MX ON THE HORIZONTAL STAB TRIM ACTUATOR (HSTA), LOOSE BOLTS (ITEMS 24 AND 35) WERE FOUND IN THE UPPER BOLT LOCATIONS OF THE RT AND LT HSTA UPPER ATTACHMENT FITTING ASSY ITEM 33).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA21EA                        
             20081230     EA  2008       12         30         CA081122005      120081111G2120                UNKNOWN                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              SMOKE           W      C   ABORTED TAKEOFF                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) "A08C0232: AS FLIGHT WAS ON THE TAKEOFF RUN, WHEN THE CREW RECEIVED A CAUTION MESSAGE FOR SMOKE IN THE LAVATORY. THE TAKEOFF WAS REJECTED AT 60 KTS AND ARFF WAS CALLED OUT. THE FLIGHT RETURNED TO THE APRON, PASSENGERS WERE DEPLANED, AND MX INSPECTED THE AIR CONDITIONING PACKS AND THE ACFT WAS RETURNED TO SERVICE. AFTER DE-ICING AGAIN, ANOTHER TAKEOFF WAS ATTEMPTED, BUT WAS REJECTED AT 100 KTS WHEN THE SMOKE IN THE LAVATORY CAUTION MESSAGE OCCURRED AGAIN. THE ACFT WAS INSPECTED AND FERRIED, WHERE MX IS CHANGING THE RT ENGINE (GE CF34-3B1).                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
             20081230     EA  2008       12         30         CA081122006      120081110G5610NP13922001      WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) F/O SIDE WINDOW IS CRACKED. INNER PLY. ALSO SMALL SLIVER FROM RT WINDOW HAS CHIPPED OFF APPROX  2 INCHES BY .25 INCH AT THE WINDOW EDGE. CALLED TO VERIFY THE CRACKED PLY.  ACFT TO FERRY UNPRESSURIZED FOR REPAIRS".                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA21EA                        
             20081230     WP  2008       12         30         CA081124001      120081006G3246                BUNGEE          FEDERAL                 DOUG  DC3   DC3CS4C4G   3021460WP  PWA   PT6   PT6A67R     52043NE                              SKI             MISMARKED       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) DURING AERIAL WORK WITH SKIS INSTALLED THE RT MAIN GEAR DID NOT EXTEND FULLY. WITH THE ASSISTANCE OF A BELLY MOUNTED CAMERA THE CAUSE WAS DETERMINED TO BE THE SKI FWD LIMIT CABLE ASSY. THE LANDING GEAR WAS CYCLED AND EXTENDED SUCCESSFULLY. BOTH LT AND RT SKI FWD LIMIT CABLE ASSEMBLIES WERE REPLACED. THE ENSUING INVESTIGATION DETERMINED THAT THE BUNGEE ASSEMBLIES ON THE FWD LIMIT CABLE ASSEMBLIES WERE TOO LONG ALLOWING THE CABLE TO HOOK ITSELF UNDER THE SKI PIVOT BOLT NOT ALLOWING THE LANDING GEAR TO EXTEND FULLY. THE PROPER LENGTH BUNGEE WOULD NOT ALLOW THE CABLES TO BE LOCATED IN THAT AREA. THE ORIGINALLY INSTALLED BUNGEE ASSEMBLIES WERE UNITS SUPPLIED BY THE ACFT STC HOLDER, WHO HAS BEEN NOTIFIED OF THE2L72 4R4  T  A669    E26NE                
             20081230     EA  2008       12         30         CA081124002      120081123G2497D3899920MJ43SN  CONNECTOR                               CNDAIRCL600 CL6002D24   1390016EA                                                                               BURNED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) AT APPROX 1540Z AT 15000 FT 220 KIAS AS THE PF WAS CHECKING THAT THE PITCH DISCONNECT SYS WAS RE-ENGAGED. A LOUD NOISE WAS HEARD IN THE COCKPIT, AT THE SAME TIME THE PILOTS WINDSHIELD WIPER MOVED .2500 DISPLACEMENT AND THE A/SKID INBD, INBD BRAKE BRESS AND OB BRAKE PRESS CAUTION MESSAGES POSTED. MDC WAS CHECKED FOR FAULTS AND INDICATED TRU 1, ESS TRU 1 AND A/SKID INBD HAD FAILED. CB`S CHECKED, 1B5 TRU 1, 1G4 ANTI-SKID, 1G5 WIPER PILOT, 1G10 MAINT LIGHT, 1T2 ESS TRU 1, AND 2G3 BRAKE PRESS IND FOUND TO BE POPPED. DUE TO ELECTRICAL FAILURE AND NO INDICATIONS OF BRAKE PRESSURE, EMERGENCY DECLARED AND EMERGENCY VEHICLES REQUESTED FOR LANDING. AFTER LDG, ACPC CB`S FOR HYD PUMP 1B, 2B, 3A POPPED.                2L72 4F    RTA21EA                        
             20081230     SW  2008       12         30         CA081124003      120081121G3260MS243314        SWITCH                                  SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF CREW WAS UNABLE TO RETRACT THE ACFT LANDING GEAR. THE CREW ELECTED TO RETURN TO AIRPORT OF ORIGIN AND CONTACT MX. THE ACFT WAS FERRIED HOME WITH THE GEAR DOWN.  UPON INSP FROM MX, THE MLG SAFETY SWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE LANDING CONTROL SYS WAS FOUND TO BE INOPERATIVE. MX CHANGED THE SWITCH AND THE GEAR FUNCTIONED CHECKED SERVICEABLE.  TOTAL TIME ON THE SWITCH COULD NOT BE DETERMINED.                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081230     SW  2008       12         30         CA081124004      120081117G3260MS243314        SWITCH                                  SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110U   29066NE  HARTZLHCE4N HCE4N3      NE  INTERNAL        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AN ATTEMPTED ENGINE START THE CREW WAS UNABLE TO GET ENGINE ROTATION OR LIGHT OFF. MX INVESTIGATED AND DETERMINED THE MLG SAFETY MICROSWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE ENGINE START CONTROL SYS TO BE INOPERATIVE. MX REPLACED THE SWITCH AND RETURNED THE ACFT TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081230     SW  2008       12         30         CA081124005      120081120G32601EN516          SWITCH                                  SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  NLG             FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) THE CREW COULD NOT GET A NOSE GEAR DOWN AND LOCKED INDICATION AFTER SEVERAL DOZEN GEAR POSITION CYCLES OR WITH MANUAL GEAR EXTENSION. WITH THE LAST ATTEMPT IT ILLUMINATED WITH ELECTRICAL SELECTION. EMERGENCY SERVICES AT AIRPORT WERE ON STANDBY.  THE ACFT LANDED AND MX DISCOVERED THAT ONE OR BOTH OF THE NOSE LANDING GEAR DOWNLOCK SWITCHES WAS INOPERATIVE. MX REPLACED BOTH SWITCHES AS A PRECAUTION AND GEAR FUNCTIONAL CHECKS COMPLETED. NO FURTHER PROBLEMS WITH THE LANDING GEAR SYS HAVE OCCURED.                                                                                                                                                                                                                          2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081230     SW  2008       12         30         CA081124006      120081121G32601EN516          SWITCH                                  SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  NLG             FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH TO LAND THE FLIGHT CREW COULD NOT GET THE GREEN DOWN AND LOCKED LIGHT FOR THE NLG TO ILLUMINATE. THE GEAR WAS CYCLES SEVERAL TIMES AND THE EMERGENCY GEAR EXTENSION USED. AFTER SEVERAL MINUTES THE NOSE GEAR DOWN AND LOCKED GREEN LIGHT ILLUMINATED AND THE ACFT LANDED WITHOUT FURTHER INCEDENT.  MX TRACED THE PROBLEM TO A INOPERATIVE NOSE LANDING GEAR DOWNLOCK MICRO SWITCH. BOTH DOWNLOCK MICROSWITCHES WERE REPLACED AS A PRECAUTION AND THE LANDING GEAR FUNCTION TESTED. THERE HAS BEEN NO FURTHER RECURRANCE OF THIS ISSUE.                                                                                                                                                                                      2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
             20081230     NM  2008       12         30         CA081124007      120081121G5751                SUPPORT BRACKET                         DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  AILERONS        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING HEAVY CHECK INSPECTION FOR ACFT (316), BOTH THE LT AND RT AILERON INPUT QUADRANT SUPPORT BRACKET ASSEMBLIES, ON BOTH THE INBD AND OTBD SIDES, WERE FOUND TO HAVE SIGNIFICANT CRACKING.   FLEET CAMPAIGN HAS BEEN INITIATED TO INSPECT THE AFOREMENTIONED ASSEMBLIES ON THE DHC8-300 SERIES ACFT. REFERENCE IPC 27-12-00, FIGURE 10, PAGE 0, ITEM 130.                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     NM  2008       12         30         CA081125001      120081125G2497                WIRE HARNESS                            BOEING757   75728A      1384976NM  RROYCERB211 RB211535E43754555NE                                              CHAFED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) IN FLIGHT CREW NOTICED SMOKE AND FLASHES ABOVE ROW 4DEF.  MX FOUND WIRING HARNESS CHAFED BY CEILING PANEL RESULTING IN EXPOSED WIRES ARCHING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA2NM    E12EU                
             20081230     NM  2008       12         30         CA081125002      120081125G2910DSC252A40272    FLEX LINE                               DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  HYD SYSTEM      BROKEN          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       16282                                                          (CAN) AFTER LANDING AND PARKING, VISIBLE SMOKE FROM RT LDG. SMOKE DUE TO AN HYD LEAK FROM BRAKE NR 3 BOKEN FLEXIBLE HOSE. HOSE REPLACED IAW AMM 32-42-52.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081230     NM  2008       12         30         CA081125003      120081118G561080260008        WINDSHIELD                              BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       568                                                            (CAN) AT ABOUT 500 FT ON FINAL APPROACH TO THE AIRPORT THE RT WINDSHIELD SHATTERED.  THE FLIGHT CREWS INITIAL REACTION WAS THAT THE WINDSHIELD HAD SUFFERED A BIRD STRIKE, BUT THIS WAS NOT THE CASE. THERE WAS NO EVIDENCE OF A BIRD STRIKE AND IT WAS THE INNER GLASS PLY THAT SHATTERED AND COVERED THE COPILOT WITH FINE GLASS DEBRIS. THE RESISTANCE OF THE HEATING ELEMENT (TERMINAL L1 AND L2) AND THE TEMPERATURE HEAT SENSORS (TERMINALS CB, DA AND FE) WAS CHECKED AND ALL FOUND TO BE WITHIN THE SPECIFICATIONS THE TEST REQUIREMENTS OF CMM 56-10-12. RT WINDSHIELD REMOVED AND REPLACED WITH A NEW WINDSHIELD IAW AMM TASKS 56-10-01-000-801, 56-10-01-400-801 AND 30-41-00-710-802.                                               2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
             20081230     SO  2008       12         30         CA081125004      220081112G8500IO360KB         ENGINE                                  CESSNA172   R172K       2072431CE  CONT  O360  IO360KB     17025SO  MCAULY2A34C 2A34C203    GL                  MAKING METAL    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       2050                                                           (CAN) LOSS OF OIL PRESSURE DURING FLIGHT. PRECAUTIONARY LANDING ON NEARBY LAKE. INSP REVEALED HEAVY METAL CONTAMINATION IN OIL SCREEN, POSSIBLY CRANKSHAFT BEARING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A17    E1CE    5  CP3EA     
             20081230     SW  2008       12         30         CA081125005      120081124G65001400191         WASHER                                  BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              PITCH CHANGE    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE VERTICAL FIN WAS REMOVED TO FACILITATE SEAL REPLACEMENT OF THE PITCH CHANGE MECHANISM. THE RADIUS WASHERS THAT ARE USED ON THE VERTICAL FIN ATTACHMENT WERE INSPECTED, AND IT WAS NOTED THAT 3 OF THE 4 WASHERS HAD CRACKS ON THE OUTSIDE PERIMETER OF THE WASHER. THE WASHERS P/N 140-019-1 WERE REPLACED AND THE FIN RE-INSTALLED. IT IS NOT KNOWN IF THIS CONDITION IS DUE TO OVERTIGHTENING OF THE FASTENER, OR THE INCREASE IN TORQUE VALUE FOLLOWING ISSUANCE OF ASB 206-06-107.                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E4CE                 
             20081230     NE  2008       12         30         CA081125006      220081111G7200                ENGINE                                  CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  LDLANDING        1                      CA                                                                      (CAN) DURING SHORT FINAL, UPON REDUCING THE POWER TO IDLE, THE ENGINE FLAMED OUT. THE EVENT OCCURRED AT AN ALTITUDE OF APPROX. 100 FEET AND THE CREW LANDED THE ACFT SINGLE ENGINE.   NOV. 12 2008: ENGINE FLAME-OUT EVENT OCCURRED WHILE DEPLOYING THE THRUST REVERSERS DURING LANDING ROLLOUT. THIS IS THE SECOND EVENT IN 2 DAYS ON THE SAME ENGINE. TROUBLESHOOTING IS ON-GOING WITH THE HELP OF MFG`S.                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E25EA                
             20081230     NE  2008       12         30         CA081125007      220081104G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              VIBRATION       W      O   OTHER                                                                                           ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) AT FL100 IN STEADY STATE, THE PILOT HEARD A STRONG NOISE COMING FROM THE ENG AND THE INSTRUMENTS INDICATED TEMP AT 800C, NG AT 100 PERCENT AND TORQUE AT 2000 FT-LB. THE POWER LEVER WAS RETARDED AND PARAMETERS CAME BACK TO (NORMAL).  THE FLIGHT CONTINUED AND DURING FINAL APPROACH, THE POWER REDUCED TO IDLE UNCOMMANDED AND THE ENG STOPPED RESPONDING TO POWER LEVER INPUTS. THE PILOT WAS ABLE TO LAND SAFELY WITH IDLE POWER. ONCE ON THE GROUND, THE COWLING WAS OPENED AND SMOKE WAS OBSERVED COMING OUT OF THE ENGINE. THE ENG WILL BE REMOVED AND FWD FOR INVESTIGATION. UPDATES WILL BE PROVIDED TO TC.                                                                                                                   1H71 3T3  T  A37CE   E4EA                 
             20081230     NE  2008       12         30         CA081125008      220081112G7200                ENGINE                                                                     PWA   PW120 PW127            NE                              NR 2            MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         EJ VIBRATION/BUFFET          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE CREW FELT A SUDDEN YAW AND OBSERVED NR 2 ENGINE TEMP GAGE AT MAX. READING ACCOMPANIED BY AN EEC FAULT. NO UNUSUAL NOISES WERE REPORTED BUT PERSONNEL IN THE REAR OF CABIN REPORTED A SPIKE OF FLAME FROM THE EXHAUST. THE CREW ELECTED TO SHUT THE ENGINE DOWN AND A SINGLE ENGINE LANDING WAS PERFORMED. GROUND INSP FOUND ALL 3 ENGINE ROTORS NOT CAPABLE OF ROTATION. ENGINE WILL BE REMOVED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                          4  T          E20NE                
             20081230     NE  2008       12         30         CA081125009      220081017G7323                GOVERNOR                                AEROSPATR42 ATR42300    8680920EU  PWA   PW121 PW121       52124NE                              OVERSPEED       LEAKING         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) TEN MINUTES AFTER TAKEOFF, THE CREW GOT A RT ENG LOW OIL PRESSURE WARNING. THE PROPELLER DID NOT AUTO FEATHER AND THE CREW ATTEMPTED TO FEATHER THE PROPELLER MANUALLY WITHOUT SUCCESS. THE ENGINE REMAINED FUNCTIONING FOR FIVE MINUTES BEFORE THE CREW ELECTED TO SHUT IT DOWN. THE PROP HOWEVER DID NOT FEATHER AND THE ACFT FLEW FOR 60 MINUTES WITH THE ENGINE SHUTDOWN BUT PROP WINDMILLING AT AROUND 70 PERCENT NP. A SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND AN OIL LEAK AT THE OVERSPEED GOVERNOR HYD PUMP MOUNTING PAD. CHIP DETECTOR CONTAMINATION AND SEIZED LP IMPELLER WAS ALSO OBSERVED. ENGINE WAS REMOVED AND FWD FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS2H72 4T4  TRTA53EU   E20NE                
             20081230     NE  2008       12         30         CA081125010      220081113G7200                OIL SYSTEM                              BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              ENGINE          LEAKING         W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL270, THE PILOT NOTICED OIL ODOR AND SMOKE IN CABIN. HE ELECTED TO SHUTDOWN THE ENG AND SHORTLY AFTER, PERFORMED A UNEVENTFUL SINGLE ENGINE LANDING. POST FLIGHT INSP AND GROUND RUNS REVEALED OIL COMING OUT OF THE INLET AND COMPRESSOR BLEED VALVE.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  T  A24CE   E4EA                 
             20081230         2008       12         30         CA081125011      120081113G6100                SLEEVE                                                                     PWA   PT6   PT6A68           NE                              PROP TRANSFER   DAMAGED         W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          APAPPROACH       1                      CA                                                                      (CAN) WHILE IN THE VFR PATTERN THE ACFT EXPERIENCED A LOSS OF POWER ACCOMPANIED BY A CHIP LIGHT. THE ENG STABILIZED AT A REDUCED POWER SETTING AND 85 PERCENT NP AND THE CREW MADE AN EMERGENCY LANDING. AN INSP OF THE PROPELLER TRANSFER SLEEVE REVEALED BLUING. THE ENGINE IS TO BE REMOVED AND REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                      4  T          E26NE                
             20081230     NE  2008       12         30         CA081125012      220081116G7200                ENGINE                                  DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE                              LEFT            FAILED          W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, WITH NO WARNING THE LT ENG SHUTDOWN ACCOMPANIED WITH A LOUD NOISE. THE FIRE WARNING FOLLOWED AND THE CREW DISCHARGED BOTH FIRE BOTTLES BEFORE DIVERTING THE FLIGHT WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED. POST FLIGHT INSP REVEALED THAT THE PROPELLER WAS HARD TO ROTATE AND DEBRIS WERE FOUND IN THE ENG TAILPIPE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE                
             20081230     NE  2008       12         30         CA081125013      220081115G7321                EEC                                     AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              LT ENGINE       FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB PASSING FL110, A SEVERE YAW TO THE LT WAS FELT AND THE CREW NOTED THAT THE LT ENG INDICATED 0 TORQUE (ENGINE STILL RUNNING). ATTEMPTS TO REGAIN ENG PWR WERE UNSUCCESSFUL AND THEY ELECTED TO RETURN TO THE POINT OF DEPARTURE. SHORTLY AFTER, VIBRATIONS WERE FELT AND THE CREW SHUT THE ENGINE DOWN. A SINGLE ENGINE LANDING FOLLOWED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE ENGINE ELECTRONIC CONTROL BEFORE THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                    2H72 4T4  TRT        E20NE                
             20090102     EA  2009       1          2          CA081125014      120081011G2822RR12830         PUMP                                    DHAV  DHC6  DHC6100     2802610EA  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  FUEL BOOST      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            6                                                         (CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON.  PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST PUMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES.  FAILED PUMP RETURNED TO INSTALLER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
             20090102     NE  2009       1          2          CA081125015      220081115G7200                ENGINE                                  UROCOPEC135 EC135P1     8680990EU  PWA   PW206 PW206B      0    NE                              NR 1            MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE FLIGHT, THE NR 1 ENG CHIP DETECTOR LIGHT ILLUMINATED. THE PILOT "BURNED" THE CHIP DETECTOR AND THE LIGHT WENT OUT. SHORTLY AFTER THE LIGHT CAME ON AGAIN AND THE PILOT BURNED AGAIN AND THE LIGHT WENT OUT. HE DECIDED TO ABORT THE MISSION AND RETURN TO BASE DURING WHICH TIME HE HEARD A LOUD NOISE FROM THE ENGINE WITH PARAMETER DECAYING. THE ENG WAS SECURED AND AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND HEAVY METAL CONTAMINATION AND FRACTURED POWER TURBINE BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                  1G72 3U3  UO H88EU   E42NE                
             20090102     NE  2009       1          2          CA081125016      220081117G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              SHUTDOWN        W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL190, THE ENGINE SPOOLED DOWN UNCOMMANDED. EMERGENCY WAS DECLARED AND THE FLIGHT DIVERTED AND A SINGLE ENGINE LANDING WAS ACCOMPLISHED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA10CE   E35NE                
             20090102     EA  2009       1          2          CA081125017      220081107G7230                BLADES                                                                     PWA   PT6   PT6A28           EA                              COMPRESSOR      FRACTURED       W      A   UNSCHED LANDING                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE AT FL170, THE LT ENG LOST POWER AND THE TEMP INCREASED TO 850 DEGREES C.  (1) PASSENGER SAW FLAMES OUT THE EXHAUST. THE ENG WAS SHUTDOWN AND A SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND FRACTURED COMPRESSOR TURBINE BLADES. THE ENG WILL BE INVESTIGATED AT IN PRESENCE OF A MFG REP AND UPDATES WILL BE PROVIDED.                                                                                                                                                                                                                                                                                                                                                                                                  4  T          E4EA                 
             20090102     EA  2009       1          2          CA081125018      220081116G7250                BLADES                                                                     PWA   PT6   PT6A6       52043EA                              POWER TURBINE   FAILED          W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT TYPE ID PC-9. WHILE APPLYING POWER DURING A TOUCH AND GO, THE ENGINE STARTED VIBRATING. THE PILOT REDUCED THE POWER TO IDLE AND ABORTED T/O.   AS THE A/C SLOWED DOWN ON THE RUNWAY, OIL BEGAN TO SPRAY OVER THE CANOPY. ONCE CLEARED OF THE RUNWAY, THE PROPELLER SLOWED DOWN RAPIDLY AND THE ENG WAS IMMEDIATELY SHUTDOWN. POST FLIGHT INSP FOUND FRACTURED PT BLADES, THE EXHAUST DUCT HAS A HOLE THROUGH THE INNER "SKI JUMP", THE EXHAUST STACK HAS MULTIPLE HOLES AND DENTS AND THE ENGINE COWLING IS DENTED. MFG IS REQUESTED THE ENG BE FWD TO PLT 5 FOR INVESTIGATION.                                                                                                                                                             3  T          E4EA                 
             20090102     NE  2009       1          2          CA081125019      220081119G7261                OIL SYSTEM                              LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              RT ENGINE       LEAKING         W      B   EMER. DESCENT                                                                                   KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            DEDESCENT        1                      CA                                                                      (CAN) APPROX 20 MILES SOUTH OF AIRPORT, THE PILOT REPORTED SMOKE IN CABIN. HE DECLARED AN EMERGENCY AND THEY WERE GIVEN PRIORITY TO LAND. MX  PERFORMED GROUND RUNS AND FOUND THE RT ENG OIL LEAKING INTO THE BYPASS AIR AND REACHING CABIN BLEED AIR DUCTS. THE ENG IS BEING REMOVED.                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA10CE   E35NE                
             20090102     NE  2009       1          2          CA081125020      220081121G7200                ENGINE                                  AGUSTAA109  A109E       0260119EU  PWC   PW206CPW206C           NE                              NR 2            MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RR PARTIAL RPM/PWR LOSS      PARTIAL RPM/PWR LOSS                                CLCLIMB          1                      CA                                                                      (CAN) PILOT REPORTED NR 2 ENG CHIP LIGHT ILLUMINATED AT TOP OF CLIMBOUT, IMMEDIATELY FOLLOWED BY A SURGE AND POWER LOSS. PILOT PREPARED FOR A RUN-ON LANDING. NR 2 ENG WAS SECURED, PASSENGERS WERE BRIEFED AND TRAFFIC AND DISPATCH WERE ALERTED.  NR 1 ENG WENT TO 124 PERCENT TORQUE AFTER NR 2 ENG POWER LOSS. SUCCESSFUL RUN-ON LANDING WAS ACCOMPLISHED AND ACFT WAS GROUND-TAXIED TO PARKING AREA. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                  1G72 3U3  URTH7EU    E42NE                
             20090102     NM  2009       1          2          CA081126001      120081120G27203985001007      CONTROL UNIT                            BOMBDRDHC8  DHC8402     1390042NM  PWC   150   PW150A           EA                              RUDDER          FAILED          W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA       4779                                                           (CAN) WHILE PERFORMING TASK 27-21-28-710-801 OPS TEST OF THE RUDDER SHUT-OFF VALVES, NR1 RUDDER SHUT-OFF VALVE FAILED TO CLOSE WHEN SELECTED OFF.  THE FLIGHT CONTROL ELECTRONIC CONTROL UNIT (FCECU) WAS REPLACED. THE TASK WAS PERFORMED AND PASSED THE TEST. THE FCECU WAS TESTED IAW AMM 27-00-01.                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E00062EN             
             20090102     NM  2009       1          2          CA081126002      120081116G5230                DOOR                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              CARGO           NOT CLOSED      W      A   UNSCHED LANDING                                                                                 WJ INADEQUATE Q C            WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AIR TURNBACK: AFTER T/O FUSELAGE DOOR WARNING LIGHT CAME ON. AFT CARGO DOOR INDICATION.  ON INSP AFTER LANDING IT WAS NOTICED THE THE AFT CARGO DOOR HANDLE WAS POPPED OUT. THE DOOR WAS CLOSED BUT NOT LOCKED.  AFT CARGO DOOR WAS FUNCTIONED AND CLOSED AND LOCKED.  SUSPECT THAT THE GROUND CREW DID NOT FULLY PUSH THE HANDLE INTO THE CORRECT POSITION.                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN             
             20090102     NM  2009       1          2          CA081126003      120081124G5270                SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              DOOR LOCK       OUT OF RIG      W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AIR TURNBACK: FUSELAGE DOOR WARNING LIGHT IN FLIGHT.  RIGGED EMERGENCY EXIT DOOR PROXIMITY SENSOR EDRCLLK IAW AMM 52-71-01. INDUCTANCE 8.600MH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E00062EN             
             20090102         2009       1          2          CA081126005      420081104G3457S67157520       ANTENNA                                 CESSNA750   750         2076810CE  ALLSN AE3007AE3007C     03047GL                              NR 2 GPS        MALFUNCTIONED   W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       LDLANDING        1                      CA                                                                      (CAN) FLIGHT CREW REPORTED NR 2 FMS DRIFTED 8NM AT END OF THE LEG.  NR 2 GPS ANTENNA REPLACED AND TESTED SERVICEABLE IAW 34-54-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4J4  FRTT00007WITE6CH                
             20090102     NM  2009       1          2          CA081126006      120081010G291082920010263     LINE                                    DHAV  DHC8  DHC8103     1386005NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA       6726                                                           (CAN) DURING CRUISE FLIGHT SEVERAL DROPS OF HYD FLUID WERE DISCOVERED COMING FROM THE RT OVERHEAD CEILING. SOME FLUID FELL ON THE PASSENGERS IN THE AREA. NO INJURIES REPORTED.  NO EMERGENCY ACTION/PROCEDURES CONDUCTED.  AFTER AN UNEVENTFUL LANDING MX DETERMINED THE LEAK TO BE FROM A HYD TUBE FITTING.  THE TUBE WAS REPAIRED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090102         2009       1          2          CA081126007      420081021G31007014300901      DISPLAY                                 CESSNA750   750         2076810CE  ALLSN AE3007AE3007C     03047GL                              NR 4            FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        H  ELECT. POWER LOSS-50 PC                                                       CLCLIMB          1                      CA                                                                      (CAN) RE-OCCURRING DEFECT 2008/10/21 -FLIGHT CREW REPORTED NR 4 DISPLAY UNIT FLICKED ON START-UP. FAULT COULD NOT BE DUPLICATED AND WAS SWAPPED TO NR4 POSITION FOR TROUBLESHOOTING PURPOSES.  2008/10/22 -FLIGHT CREW REPORTED NR3 DISPLAY UNIT FAILED AT THE TOP OF DESCENT. NR 3 DISPLAY UNIT DEFERRED IAW MEL.  2008/10/24 -NR 3 DISPLAY UNIT REPLACED WITH REPAIRED UNIT FROM MFG AND CHECKED SERVICEABLE IAW AMM 34.  2008/10/30 -MX REPORTED NR 3 DISPLAY UNIT STARTING FLASHING INTERMITTENT WHITE DIAMONDS AND BLACK SCREEN DURING EXTENDED OPERATION. NR 3 DISPLAY UNIT DEFERRED IAW MEL. RE-OCCURRING DEFECT FORM GENERATED.  TEAR DOWN REPORT OF THIS UNIT IDENTIFIED THIS AS BEING THE REASON FOR REMOVAL FROM PREVIOUS AIRCRAFT.  2L72 4J4  FRTT00007WITE6CH                
             20090102     WP  2009       1          2          CA081126008      120081121G243514924HTH        CASE                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER GEN     CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       41                                                             (CAN) STARTER CASING CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
             20090102     NE  2009       1          2          CA081127001      120081103G6320S613520670043   HOUSING                                 SKRSKYS61   S61N        8142104NE                                                               M/R GEARBOX     CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CRACK FOUND ON THE FRONT/RT SIDE OF LWR HSG  REPAIR TO LWR HSG CARRIED OUT IAW RDC NO: P-RH07-038 H1E-02.  THIS AREA OF THE HSG IS ALWAYS HIGHLY SCRUTANIZED DURING NDT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2G72 4U      1H15                         
             20090102     NE  2009       1          2          CA081127002      120081103G6230                BEARING                                 SKRSKYS61   S61A        814210CNE                                                               MAST            FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) S61MGB S/N: A14-J-10-79-1119 SUPPLIED, HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB FROM THE ACFT, AND RETURNED IT TO HELI-ONE TSN: 15634:00 TSO: 772:29 HELI-ONE DISASSEMBLED THE MGB TO FIND THAT THE MAST DUPLEX BRG P/N:SB1357-103 ,S/N: J0359 WAS THE CAUSE OF THE CONTAMINATION.  REPLACEMENT OF BRG REQUIRED. MAST DUPLEX BRG P/N:SB1357-103 ,S/N: J0359 COMPANY SQID NR08-07990.                                                                                                                                                                                                                                                                                                                    2G72 4U      H2EA                         
             20090102     NE  2009       1          2          CA081127003      120081030G6230                GUIDE                                   SKRSKYS76   S76A        8143006NE                                                               SWASHPLATE      MISMANUFACTURED W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MGB PN: 76351-09600-043 S/N:A231-00085 FOLLOWING INSP OF SWASHPLATE GUIDE PN:76351-09029-101,SN:A028-00343 FROM ABOVE MENTIONED MGB,THE MEASUREMENT TAKEN AT RADIUS (J ) (REF:SA4047-76-7-8,CHG.9) INDICATES BELOW MINIMUM REQ`D RADIUS OF.040 INCH.  IAW O/H MANUAL REF,  SWASHPLATE GUIDES ARE AMONG THE LIST OF ITEMS CLASSIFIED AS FLIGHT SAFETY PARTS. PART HAS BEEN TAGGED REJECTED AS THIS MINIMUM .040 INCH RADIUS IS CONSIDERED A CRITICAL CHARACTERISITIC. RETURN TO VENDOR FOR WARRANTY (THIS PART HAS A TIME LIFE OF 20,000 HRS AND HAS ONLY BEEN IN SERVICE FOR ONE MGB O/H OF 3242.7 HRS, SEE MGB LOG CARDS)  MOST LIKELY MACHINED INCORRECTLY DURING MFG PROCESS.  SQID NR 08-07896.                                       1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127004      120080911G6230SB3354102       CONE                                    SKRSKYS76   S76         8143010NE                                                               M/R GEARBOX BRG DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSPECTION OF CAGE SHAKE ON TAPERED ROLLER BRGS PN: SB3354-102 WAS DIMENSIONALLY INSPECTED IAW (SA4047-76-7-8 CHANGE 9, 31/MARCH/2006 IAW PARA. 2-52A) AND DETERMINED TO EXCEED AVERAGE MAXIMUM ALLOWABLE CAGE SHAKE LIMITS (.017 INCH) PRIOR TO INSTALLATION ON MGB PN: 76351-09600-044 SN:A231-00184.  RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG CONE RETURNED TO VENDOR AWAITING WARRANTY RMA NR.  (COMPANY SQID NR 08-06654)                                                                                                                                                                                                                                                                                                   1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127005      320081112G6114E6468           HUB                                     BEECH 56    56TC        1152736CE                                   HARTZLHCE4A HCE4A3A     NE  PROPELLER       WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            2209                                                      (CAN) PROPELLER CAME IN FOR SHIFTED PRELOAD PLATES. HUB DID NOT SEEM TO SEAL (MATE) PROPERLY. THERE WERE HEAVY WEAR MARKS ON THE CENTER SECTION OF THE MATING SURFACES ONLY. TEFLON WAS WORN THROUGH ON ALL (4) BLADES. ONE OTBD BRG RACE WAS BADLY CHIPPED AND SHOWED SIGNS OF CRACKING.                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      3A16            5  CP10NE    
             20090102     NE  2009       1          2          CA081127007      120080708G63207635109626      SHAFT                                   SKRSKYS76   S76         8143010NE                                                               M/R GEARBOX     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MGB PN:76351-09600-044 SN:A231-00044 IN FOR OVERHAUL. FOLLOWING CLEANING AND INSP OF NEW SPLINE SHAFT, CORROSION WAS FOUND AT INNER AND OUTER SPLINES.  ALL REMAINING SPLINES SHAFTS (QTY:6) PULLED FROM STOCK AND INSPECTED, NO EVIDENCE OF CORROSION FOUND.  CORROSION PITTING FOUND ON NEW SPLINE SHAFT PULLED FROM STOCK.  RETURN TO VENDOR FOR FULL WARRANTY  COMPANY SQID NR 08-05027.                                                                                                                                                                                                                                                                                                                                              1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127008      120080620G63207635109058102   PINION GEAR                             SKRSKYS76   S76         8143010NE                                                               M/R GEARBOX     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORROSION PITTING FOUND ON BORE ID OF (2) HELICAL PINIONS  HSI (P.A.P) MGB PN:76351-09500-044 SN:A081-00196 REC`D FOR O/H. PRIOR TO ASSY INSP OF NEW CUSTOMER SUPPLIED HELICAL PINIONS (X2), REVEALED CORROSION PITTING IN BORE ID OF BOTH PINIONS AT AREA OF FWD ROLLER PATHWAY. COMPANY SQID NR08-04520.                                                                                                                                                                                                                                                                                                                                                                                                                                1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127009      120080611G63207635109028105   SHAFT                                   SKRSKYS76   S76         8143010NE                                                               M/R GEARBOX     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORROSION FOUND ON NEW QUILL SHAFT MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00110 FOLLOWING CLEANING AND INSPECTION OF NEW QUILL SHAFT (P/N,S/N LISTED BELOW), MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G72 3U      H1NE                         
             20090102         2009       1          2          CA081127010      120080611G63207635109028105   SHAFT                                                                                                                                   M/R GEARBOX     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) EXCESSIVE CORROSION FOUND ON NEW QUILL SHAFT. MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00058 DURING CLEAN-UP AND INSP OF NEW QUILL SHAFT (PN, SN MENTIONED BELOW) MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF PART.  RETURN TO VENDOR FOR FULL WARRANTY UNSERVICEABLE QUILL SHAFT RETURN TO VENDOR AWAITING WARRANTY RMA NR  COMPANY SQID NR 08-04306.                                                                                                                                                                                                                                                                                                                                                                                              
             20090102     NE  2009       1          2          CA081127011      120080606G6320SB3202A2        BEARING                                 SKRSKYS76   S76A        8143006NE                                                               M/R GEARBOX     FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PERFORMED CAGE SHAKE ON NEW BRGS IAW MFG ACFT ENGINEERING INSTRUCTION EI NR E76-702-35-1601. RESULTS FAILED INSP RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG RETURN TO VENDOR AWAITING WARRANTY RMA NR COMPANY SQID NR 08-04194.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127012      120080417G63207635109008056   HOUSING                                 SKRSKYS76   S76A        8143006NE                                                               M/R GEARBOX     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GEARBOX REMOVED FOR EXCESSIVE CORROSION AROUND OIL FILTER HSG FITTING. MAIN GEARBOX RECEIVED AT HELI-ONE FOR REPAIR AT TT:10961:18 HRS. TSO:2969:48 HRS. FLUID ADAPTER (FITTING) REMOVED FROM LWR HSG OIL FILTER AREA AND CORROSION WAS CLEANED/REMOVED TO ALLOW FOR INSPECTION.  EXTENSIVE CORROSION WAS FOUND AT FLUID ADAPTER PORT AND LOCK RING AREA BEYOND MAXIMUM REPAIRABLE LIMITS IAW REF:SA4047- 76-7-8,CHG.9-31MAR2006.  REPLACE UNSERVICEABLE LOWER HOUSING P/N:76351-09008-056 S/N:C065-00098 (T.T: UNK) WITH NEW/OVERHAULED EQUIPPED WITH NEW VERSION FLUID ADAPTER P/N:RFSK9812-13. MOST LIKELY INSUFFICIENT SURFACE PROTECTION AT DAMAGED AREA.                                                                            1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081127013      120080320G6320SB2151107       BEARING                                 SKRSKYS76   S76A        8143006NE                                                                               UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GEARBOX MAKING METAL TSN:2969:43 HRS. GEARBOX RECIEVED FOR PREMATURE OVERHAUL DUE TO METAL CONTAMINATION.  DURING INSP PROCESS , RT SPUR PINION ALIGNMENT ROLLER BRG SB2151-107 S/N:2659 (LOCATED AT UPPER HSG COUNTERBORE) WAS FOUND TO BE BREAKING UP AT OUTER RACE ROLLER PATHWAY. FOLLOWING COMPLETION OF GB INSP THIS BRG WAS CONSIDERED AS THE SOURCE FOR THE METAL CONTAMINATION.  REPLACE BRG DURING OVERHAUL.                                                                                                                                                                                                                                                                                                                    1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081128001      220081125G7250PW120A          TURBINE                                 DHAV  DHC8  DHC8101     2809002NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 2 ENGINE     FAILED          W      L   ABORTED APPROACH                                                                                O  OTHER                                                                         APAPPROACH       1                      CA       2784617199                                                     (CAN) PRIOR TO TAKEOFF, THE CREW FELT A THUD AND GRINDING NOISE FROM THE NR 2 ENGINE AT 70 PERCENT TORQUE. THE ENGINE WAS IMMEDIATELY SHUTDOWN, BUT BY THE TIME THE TORQUE REDUCED TO ZERO PSI AND THE ITT OF THE ENG REACHED UP TO 1200 DEGREE CELSIUS. ENG WAS IMMEDIATELY SHUTDOWN AND TAKEOFF WAS ABANDONED. ON RETURN AT THE RAMP, BROKEN PIECES OF BLADES OF PWR TURBINE WERE FOUND IN THE TAIL EXHAUST PIPE. ALL PARAMETERS OF BOTH ENGINES WERE WITHIN LIMIT. AS SOON AS THE TAKEOFF ROLL INITIATED AND PWR WAS ADVANCED THROUGH 70 PERCENT TORQUE, A THUD AND GRINDING NOISE WAS HEARD FROM RT SIDE (NR 2 ENG) AND ACFT STARTED SWINGING TO THE RT. IMMEDIATELY, THE TAKEOFF WAS REJECTED AND WHILE LOWERING THE POWER LEVERS THE TORQU2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090102     NE  2009       1          2          CA081128002      120081103G6320S613723053102   BEVEL GEAR                              SKRSKYS61   S61A        814210CNE                                                               M/R GEARBOX     UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA            770                                                       (CAN) BROKEN GEAR TOOTH FOUND IN FILTER REPAIR-BROKEN GEAR TOOTH FOUND IN FILTER OF S61 MGB SN: A14-215. MGB WAS REMOVED FROM ACFT HS-HTA AND REURNED TO HELI-ONE TO BE REPAIRED TSN: 31804:41 TSO: 769:56 DISASSY DONE AT HELI-ONE TO FIND THAT THE INPUT BEVEL GEAR PN: S6137-23053-102 SN: E128-00271WAS THE DAMAGED PART. INPUT BEVEL GEAR PN: S6137-23053-102 SN: E128-00271.  COMPANY SQID NR 08-08045.                                                                                                                                                                                                                                                                                                                                   2G72 4U      H2EA                         
             20090102     NE  2009       1          2          CA081128003      120081127G6320                GEARBOX                                 SKRSKYS76   S76         8143010NE                                                               MAIN ROTOR      FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MGB CHIP LIGHT INDICATION MGB PN:76351-09600-044,SN:A231-00107 REC`D AT HELI-ONE FOR REPAIR. TSN:8638:39 TSO:2516:54 FOLLOWING DISASSEMBLY AND INSPECTION OF MGB, RT OUTPUT ALIGNMENT BRG WAS IDENTIFIED AS THE CAUSE FOR METAL GENERATION WITH HEAVY SPALLING EVIDENT AT ROLLER PATHWAY OF OUTER RACE.  FLUSH MGB AND REPLACE DISCREPANT BEARING.  COMPANY SQID NR 08-8606.                                                                                                                                                                                                                                                                                                                                                              1G72 3U      H1NE                         
             20090102     NE  2009       1          2          CA081128004      120081127G6320SB2151107       BEARING                                 SKRSKYS76   S76         8143010NE                                                               M/R GEARBOX     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2037                                                           (CAN) MGB CHIP LIGHT INDICATIONS MGB P/N:76351-09600-044 S/N:A231-00299 REC`D AT HELI-ONE FOR REPAIR. TSN:2037:48 HRS. FOLLOWING DISASSY AND INSP OF MGB THE RT OUTPUT ALIGNMENT BRG WAS FOUND TO BE THE CAUSE FOR THE METAL GENERATION WITH HEAVY SPALLING AT ROLLER PATHWAY OF BRG OUTER RACE.  ADDITIONAL BRS INDICATE INITIAL STAGES OF SPALLING. REPLACE WITH SERVICEABLE BRS.  COMPANY SQID NR 08-08605.                                                                                                                                                                                                                                                                                                                                  1G72 3U      H1NE                         
             20090102         2009       1          2          CA081128005      420081127G3120285T08551       FDAS                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              COCKPIT         ODOR            W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) ON CRUISE THE F/A REPORTED A STRONG ODOR IN THE CABIN, PILOT CONFIRMED THE STRONG SMELL AND DIVERTED FLIGHT TO BASE AND DECLARE AN EMERGENCY LANDING. AFTER MX INVESTIGATION, FOUND THE FDAS "FLIGHT DECK ACCESS SYS" AT FAULT.  ELECTRICAL ODOR COMING FROM THIS COMPONENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20090102     EA  2009       1          2          CA081128006      220081126G8530                VALVE SEAT                              PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1452                                                      (CAN) INTAKE VALVE STAYING OPEN, INTAKE VALVE AND SEAT WORN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A20SO   E14EA   5  CP33EA    
             20090102     EA  2009       1          2          CA081129001      120081125G5610NP1393229       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       9278                                                           (CAN) IN FLIGHT LT SIDE WINDOW SHATTERED. FLIGHT DIVERTED MX REPLACED SIDE WINDOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20090102     EA  2009       1          2          CA081129003      120081122G3260                WARNING LIGHT                           CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              MLG             ILLUMINATED     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT WHEN SELECTED UP. LANDING GEAR LIGHT REMAINED GREEN. FLT CREW ALSO REPORTED INBD ANTI-SKID (C) AND PARK BRAKE SOV (C) MSG. ALL MSGS CLEARED WHEN GEAR SELECTED DOWN. ACFT RETURNED TO DEPARTURE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20090102     EA  2009       1          2          CA081129005      120081116G2150GG670950093     ACM                                     CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5B1   30052NE                              LEFT            SEIZED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA       5579                                                           (CAN) AFTER LANDING AND TAXI TO GATE, FLT CREW REPORTED SMOKE STARTED COMING FROM VENTS IN COCKPIT. CREW ELECTED TO STOP SHORT OF THE GATE AND EVACUATE THE ACFT. ACFT WAS EVACUATED WITHOUT INCIDENT.  MX INSPECTED ACFT AND FOUND THAT THE LT ACM HAD SEIZED. NO OTHER DEFECTS WERE NOTED. LT PACK WAS DEFERRED IAW THE MEL AND ACFT RETURNED TO SERVICE.  17 NOV 08: MX REMOVED AND REPLACED THE LT ACM AND OPS CHECKED. NO FURTHER DEFECTS NOTED. LT PACK REMOVED FROM DEFERRAL AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E00063EN             
             20090102     NM  2009       1          2          CA081201001      120081128G2510412310416       SEAT BACK                               EMB   ERJ190ERJ190100IGW3260408NM  GE    CF34  CF3410E5A1  30022NE                              COCKPIT         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE ATTACH SCREWS HOLDING SEAT BACK BRACKET TO SEAT ARM ARE LOOSE, THE BRACKET ATTACHES THE SEAT BACK TO THE ARM. THE SCREWS ARE 0.5 INCHES IN LENGTH, THE SWIVEL BRACKET ATTACH POINT WAS ALSO LOOSE. REF: 4/MM 41402003, IPL 25-22-90 PAGE 10044 FIGURE 7 ITEMS 5 & 10. CHAIR PN ARE414140003-105, 41414003-111,41414003-113,41404003-103 & 41404003-105.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA57NM   E00070EN             
             20090102     CE  2009       1          2          CA081201002      120081201G33400713035         SWITCH                                  CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA                              LANDING LIGHT   OVERHEATED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LANDING LIGHT SWITCH MAY BE ORIGINAL (8865 HRS) DETENTS BECAME "STICKY" AND NOT AS POSITIVE AS NORMAL. SWITCH FUNCTION DID NOT FAIL.  INSP REVEALED PWR SUPPLY WIRE END AND LUG ON SWITCH OVERHEATED. DISASSY SHOWED LUG CONTACT RIVET DETERIORATED AS WELL AS MYCARTA TYPE BOARD MATERIAL DISINTEGRATING DUE TO HEAT DAMAGE AROUND THE RIVET.  MFG REQUIRES NEWER STYLE (1970 AND NEWER) LANDING LIGHT SWITCHES TO BE REPLACED EVERY 5 YEARS THIS OLDER STYLE SWITCH THOUGH LIKELY ABLE TO CARRY MORE CURRENT SHOULD BE INSPECTED VISUALLY ANNUALLY TO DETERMINE IF OVERHEATING IS AN ISSUE.                                                                                                                                             1H71 3O3  ONT3A12    E274                 
             20090203     CE  2009       2          3          CA081201003      120081009G3597P108            CONNECTOR                               LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              O2 SYSTEM       MISINSTALLED    W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) PASSENGER O2 MASK WOULD NOT DEPLOY WHEN TESTED.  SYSTEM TROUBLESHOT AND FOUND CONNECTOR P108 WAS NOT INSTALLED CORRECTLY.  CONNECTOR REMOVED, INSPECTED AND REINSTALLED .O2 MASK FUNCTION CHECKED SERVICEABLE IAW AMM 35.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTT00008WIE6WE                 
             20090102         2009       1          2          CA081201004      120081201G8011                BOLT                                                                                                                                    STARTER         MISSING         W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       498  498                                                       (CAN) STARTER CASE THROUGH BOLTS. BOLTS HAVE LOOSENED OFF TO THE POINT OF CAUSING ELECTRICAL SHORTING WITHIN THE STARTER DUE TO THE HALVES BEING LOOSE FROM EACH OTHER. ONE BOLT COMPLETELY MISSING. SPARKS AND ARCING VISUALLY OBSERVED AT BENDIX HSG DURING STARTER OPERATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
             20090102     WP  2009       1          2          CA081201005      220081130G720031037505        GASKET                                                                     GARRTTTPE331TPE33110UA  01514WP                              ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       24                                                             (CAN) THIS ENG WAS NOTED TO HAVE A OIL LEAK COMING FROM THE BOTTOM OF THE DIAPHRAGM AT THE 2 BOTTOM BOLT HOLES CLOSEST TO THE CHIP DETECTOR. THE GASKET WAS NOTED TO BE STICKING OUT AND NOT SEALING PROPER. UPON FURTHER INVESTIGATION THE OLD STYLE GASKETS PN 3103750-1/-3/-4 WERE CHANGED UP TO A 3103750-5 TO PREVENT THIS ISSUE. REF: SB TPE331-72-2084 FOR THE UPGRADED GASKETS. THE 3103750-5 GASKET WAS INSTALLED ONLY 23.5 HRS PRIOR TO THIS OIL LEAK AT A REPAIR. THE CASE BOLTS WERE CHECKED AND WERE AT THERE PROPER TORQUE.                                                                                                                                                                                                              4  T          E4WE                 
             20090102     CE  2009       1          2          CA081201006      120081201G5310NAS1473A3K      DOME NUT                                CESSNA750   750         2076810CE  ALLSN AE3007AE3007C     03047GL                              WINDSHIELD POST CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE REPLACEMENT OF THE RT WINDSHIELD, DUE TO A BROKEN OUTER PANE, HEAVY CORROSION WAS NOTED COMING OUT OF THE DOME NUTS. THE WINDSHIELD IS INSTALLED FROM THE OUTSIDE AND THE SCREWS ARE HELD IN PLACE BY THESE DOME NUTS THAT RIVETED IN PLACE AROUND THE PERIMETER OF THE FRAME. EACH DOME NUT WAS BOROSCOPED AND FOUND THAT A MAJORITY WERE SPLIT OR CRUMBLED DUE TO CORROSION. ALL DOME NUTS WERE REPLACED AND THE WINDSHIELD RE-INSTALLED.                                                                                                                                                                                                                                                                                    2L72 4J4  FRTT00007WITE6CH                
             20090102     CE  2009       1          2          CA081201007      120081128G272004115264        RUDDER BAR                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  SNSNCH72C   72CK        EA  RT RUDDER       CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10660                                                          (CAN) SCREWS ATTACHING CENTER CONTROL CONSOLE COVER PN 0413463-5 WERE TOO LONG AND CHAFING IN TO THE RT SIDE OF THE RUDDER PEDAL TORQUE TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A19    E223    5  NP9045    
             20090102     NM  2009       1          2          CA081201008      120080919G6320B7936S          CHIP DETECTOR                           DOUG  600N  600N        3027377NM  ALLSN 250C  250C47M     03013GL                              TRANSMISSION    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       800                                                            (CAN) BOTH TEDESCO B7936S CHIP DETECTOR BASES FOUND CRACKED AT BASE OF O-RING FLANGE. CAUSED BY OVERTORQUE DURING AN EARLIER INSTALLATION. CRACKS NOT VISIBLE UNTIL CHIP DETECTORS WERE REMOVED TO DRAIN TRANSMISSION OIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UNCH3WE    E1GL                 
             20090102     NM  2009       1          2          CA081201009      120081128G5302500N34247       ANGLE                                   DOUG  600N  600N        3027377NM  ALLSN 250C  250C47M     03013GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       800                                                            (CAN) FUSELAGE ANGLE FOUND CRACKED DURING A TAILBOOM INSPECTION. PART IS NOT READILY VISIBLE OR A PLACE OF INTEREST DURING INSPECTIONS AND MAY HAVE GONE SOME TIME AS CRACKED. PART IS TO BE REPLACED BEFORE FURTHER FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  UNCH3WE    E1GL                 
             20090203     SW  2009       2          3          CA081201010      120080901G2910                HOSE                                    BELL  206   206B        1181511SW                                                               HYD SYSTEM      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) UPON ENGINE SHUTDOWN WALK-AROUND, PILOT REPORTED A TRANSMISSION OIL LEAK ON MACHINE.  LEAK INSPECTED AND FOUND TO BE FROM THE MAIN HYDRAULIC PUMP HOSE.  HOSE HAD CHAFED THROUGH ON A MS21919WDG CLAMP HOLDING IT DOWN TO THE TOP DECK OF A/C.  WDG CLAMP SERIES IS NOT DESIGNED FOR USE AROUND OILS AND THIS IS BELIEVED TO HAVE CAUSE THE RUBBER CUSHION ON THE CLAMP TO DETERIORATE AGAINST THE STAINLESS STEEL BRAIDED HOSE AND CAUSE A METAL ON METAL CONTACT THAT WENT UNDISCOVERED UNTIL HOSE FAILURE.  WDG CLAMP AND HOSE ASSY WERE SUBSEQUENTLY REPLACED.                                                                                                                                                                        1G71 3U      H2SW                         
             20090204     SW  2009       2          4          CA081201011      120081001G6320206031554003    SPINDLE         BELL                    BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              TRANSMISSION    WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) TRANSMISSION MOUNTS REMOVED DUE TO BEARING WEAR.  UPON FURTHER INSP, SPINDLE ALSO FOUND DAMAGED IN LOCATION OF WASHER P/N 206-030-507-001.  HARD WASHER MOVEMENT DUE TO BEARING WEAR HAD WORN INTO THE RADII OF THE SPINDLE MOUNTING AREA.  SPINDLE SCRAPED.  SPINDLE HARDNESS NOT TESTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E4CE                 
             20090102     NM  2009       1          2          CA081201012      120081129G3251651781412       ACTUATOR                                BOEING727   727225      1384077NM  PWA   JT8   JT8D9A      52048NE                              STEERING UNIT   WORN            W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) A "CLUNK" IN THE NOSE WHEEL STEERING TILLER WAS REPORTED. BOTH STEERING ACTUATOR ROD ENDS WERE FOUND PULLING OUT OF THE PISTONS. BOTH STEERING ACTUATORS WERE REPLACED. A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L73 4F4  F  A3WE    E2EA                 
             20090102         2009       1          2          CA081202001      120081201G3244301003530       TIRE                                                                                                                                    MLG             BULGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) A BULGE WAS NOTICED ON THE TIRE DURING A PRE-FLIGHT INSP. SUBSEQUENT INSP UPON REMOVAL REVEALED A RIP IN THE INNER TIRE CARCASS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
             20090102     NM  2009       1          2          CA081202002      120081129G3250C247360011      STEERING SYS                            AIRBUSA319  A319114     3930350NM  CFMINTCFM56 CFM565A1         NE                              NLG             MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       33128                                                          (CAN) NW STEERING SWING TO THE LT DURING TO ROLL AT APPROX 100 KTS. NEEDED FULL RUDDER AND RT BRAKE TO MAINTAIN CENTERLINE. STEERING CONTROL UNIT 6GC REPLACED IAW MM S/N H0714.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA28NM   E29NE                
             20090102     NE  2009       1          2          CA081202003      220081106G7250311074102       RETAINING RING                                                             PWA   PT6   PT6A114A    52043NE                              TURBINE SECTION DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2760 2760                                                      (CAN) ENGINE WAS RECEIVED FOR INVESTIGATION/REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS. THE CT SHROUD SEGMENT-RETAINING RING WAS OF POST SB 1627 CONFIGURATION AND THE CT SHROUD SEGMENTS (P/N 3035673CL12) POST SB 1628. DURING INVESTIGATION, HEAVY RUB SPOTS WERE NOTED ON QTY. 1-CT SHROUD SEGMENT AND ALL THE CT BLADES. THE CT SHROUD SEGMENTS RETAINING RING WAS FOUND DISENGAGED FROM THE RETAINING CAVITY OF CT SHROUD HSG, CAUSING LOOSENING AND DROOPING OF CT SHROUD SEGMENT. THIS RESULTED IN HEAVY RUB BETWEEN THE CT BLADES AND SHROUD SEGMENT. THE CT TIP CLEARANCES WERE INCREASED TO APPROX 0.048 INCH, WHICH ADVERSELY AFFECTED ENGINE PERFORMANCE. NO CURLING/BOWING OF CT SHROUD SEGMENTS WAS OBSERVED. NO OVER HEATING/B       3  T          E4EA                 
             20090204     EU  2009       2          4          CA081202004      120081113G6710350A27035106    CONTROL TUBE                            SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              COLLECTIVE      FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14378                                                          (CAN) EVERY 12 YEARS THE HELICOPTER GOES INTO THE SHOP FOR A MAJOR INSPECTION AS PART OF THE INSP, IS A HARDNESS TEST ON THE COLLECTIVE CONTROL TUBE.  THE TUBE IS TESTED AND IT FAILED THE HARDNESS TEST.  THE HARDNESS TEST REQUIRED IS 230 HV-5 KG LOAD.  THE AVERAGE LOAD FOR THIS COLLECTIVE TUBE WAS 168.1 HV, (FAILED THE HARDNESS TEST).                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E19EU                
             20090102     CE  2009       1          2          CA081203001      120081120G2840100380006119    PROBE                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  RT AUX TANK     SEPARATED       W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 3RD PHASE 600 HR INSP, A SNAG WAS CREATED TO FIX A DISCREPANCY IN THE RT FUEL QUANTITY INDICATING SYS. THE RT FUEL TANK READING WAS 300 LBS LOW.  MAINT INSPECTED SYS AND ISOLATED THE PROBLEM TO THE RT AUX FUEL TANK PROBE. UPON A CLOSER INSP IT WAS DISCOVERED THAT THE PROBE HSG AT SEPARATED FROM THE SENDING UNIT. THE PLASTIC RIVETS HAD SHEARED. THE PARTS WERE RECOVERED FROM THE AUX TANK AND WERE ALL ACCOUNTED FOR. A NEW SERVICEABLE UNIT WAS INSTALLED AND THE SYS WAS TESTED SERVICEABLE.                                                                                                                                                                                                                        2L72 4T4  T  A24CE   E4EA    6  CP56GL    
             20090106     NE  2009       1          6          CA081203002      220081125G7200                ENGINE                                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE                              RIGHT           MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA                                                                      (CAN) ON TAKEOFF ROLL WITH PASSENGERS ON BOARD POWER WAS ADVANCED THROUGH 70 PERCENT TORQUE. A THUD AND GRINDING NOISE WAS HEARD FROM THE RT SIDE. TAKEOFF WAS ABORTED AND AC RETURNED TO THE GATE.  ENG TO BE REMOVED AND SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE                
             20090106     EA  2009       1          6          CA081203003      220081125G7200                ENGINE                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                                              MALFUNCTIONED   W      BA  EMER. DESCENT           UNSCHED LANDING                                                         KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            CLCLIMB          1                      CA                                                                      (CAN) SHORTLY AFTER TAKE OFF OIL MIST IN CABIN WAS DETECTED. THE ACFT IMMEDIATELY TURNED BACK, DECLARED AN EMERGENCY, AND LANDED. THE LOCAL AIRWORTHINESS AUTHORITIES ARE INVESTIGATING THE EVENT. POST FLIGHT INSP REVEALED OIL IN THE VICINITY OF THE P2.2 BLEED VALVE. INSP AND BORESCOPE SHOWS LP COMPRESSOR AND BLEED VALVES WET. NO EVIDENCE OF DISTRESSED COMPONENTS. EMU DATA REQUESTED. ENGINE BEING REMOVED FOR INVESTIGATION AT MFG. UPDATES WILL BE PROVIDED.                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E00062EN             
             20090106         2009       1          6          CA081203004      120081118G6420S611033406101   SPINDLE                     S61TRH                                                                                                      TAIL ROTOR      UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3464 1747                                                      (CAN) S61 TAIL ROTOR SPINDLE FAILED NITAL ETCH INSP IAW SB61B10-18J  S/N`S K071-00144, K071-00132, K071-00137.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
             20090107     EA  2009       1          7          CA081203005      220080502G7250                TURBINE                                 BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              RT ENGINE       DAMAGED         W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA                                                                      (CAN) ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. DURING THE FLT, THE PILOT RADIOED THAT HE HAD A LOSS OF PWR FROM ONE ENG FOLLOWED BY A "MAYDAY" CALL, APPROX 14 MIN LATER, DURING WHICH HE SAID THE SECOND ENGINE STOPPED OPERATING. THE ACFT WAS EQUIPPED WITH A FDR AND CVR. EXAMINATION OF ENGINES, REVEALED THE LT ENGINE DISPLAYED ROTATIONAL SIGNATURES CHARACTERISTIC OF THE ENGINE DEVELOPING POWER AT IMPACT. NO PRE-IMPACT ANOMALIES EVIDENT. THE RT ENGINE DISPLAYED EVIDENCE OF PRE-IMPACT DISTRESS CONSISTING OF THE FRACTURE AND RELEASE OF COMPRESSOR TURBINE (CT) BLADE MATERIAL DUE TO CONTACT WITH A PROTRUDING CT BLADE SHROUD SEGMENT. THE CT DISK, VANE AND SHROUD ASSY WAS REQUESTED TO BE RETURNED TO MFG FOR DETAILED EX2L72 4T4  TRTA24CE   E4EA                 
             20090106         2009       1          6          CA081203006      120081202G6420S611033406      SPINDLE                                                                                                                                 TAIL ROTOR      UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1748 1747                                                      (CAN) S61 TAIL ROTOR SPINDLE FAILED INITIAL ETCH INSP IAW SB61B10-18J  S/N`S K071-00394, K071-00392.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      
             20090102     NE  2009       1          2          CA081203007      220081126G7200                ENGINE                                  EMB   120   EMB120      3260201SO  PWA   118   PW118            NE                                              MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB AT FL60, THE CREW NOTICED A LOW ENGINE OIL PRESSURE LIGHT, FOLLOWED BY A POPPING NOISE. THE ENG WAS SHUTDOWN AND THE ACFT WAS DIVERTED BACK TO BASE. GROUND INSP FOUND THE TURBOMACHINE CHIP DETECTOR COVERED WITH METAL SHAVINGS AND THE LP AND HP ROTORS INCAPABLE OF ROTATION. THE ENG HAD RECENTLY UNDERGONE A HOT SECTION INSP. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA31SO   E20NE                
             20090102     NE  2009       1          2          CA081203008      220081128G7323                GASKET                                  FOKKERF27   F27MK50            EU  PWA   PWA120PW125B           NE                              OVRSPD GOVERNOR TORN            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AT TOP OF CLIMB, OIL PRESSURE FLUCTUATION WAS REPORTED FOLLOWED BY LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHUTDOWN BY THE PILOT. ON RETURN TO GATE, THE ENG COWL WAS FOUND COVERED WITH OIL. OVERSPEED GOVERNOR GASKET FOUND DETERIORATED. GASKET WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA817    E20NE                
             20090102     NE  2009       1          2          CA081203009      220081125G73217898422009L6    EEC                                     DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE                              ENGINE          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) PILOT REPORTED SHUTTING ENGINE DOWN IN FLIGHT DUE TO EXCESSIVE TORQUE FLUCTUATIONS. EEC WAS REPLACED AND DEFECT RECTIFIED. THE SUSPECT EEC HAS BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE                
             20090102     NE  2009       1          2          CA081203010      220081027G7297                WIRE HARNESS                            AEROSPATR42 ATR42*      8680900EU  PWA   PW120 PW127            NE                              ENGINE          DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 RF PARTIAL RPM/PWR LOSS      FLT CONT AFFECTED                                   CRCRUISE         1                      CA                                                                      (CAN) THE ENG EXPERIENCED REPEATED EVENTS OF TORQUE FLUCTUATIONS BETWEEN THE 20TH AND 24TH OF OCTOBER FOR WHICH TROUBLESHOOTING HAD BEEN DONE. ON OCT. 27, THE PROBLEM RE-APPEARED AND WAS ACCOMPANIED BY NO RESPONSE TO THROTTLE MOVEMENTS. THE ENGINE WAS SHUTDOWN AND RE-STARTED IN MANUAL MODE WITH NO FURTHER PROBLEMS TILL THE FLIGHT ENDED. FURTHER TROUBLESHOOTING LED TO THE REPLACEMENT OF THE FUEL CONTROL AND ENGINE WIRING HARNESS, WHICH HAVE BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                   2H72 4T4  TRTA53EU   E20NE                
             20090102     NM  2009       1          2          CA081203011      120081202G271085711569001     BRACKET                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  AILERON CONTROL CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       42293                                                          (CAN) LT AILERON INPUT BRACKET FOUND CRACKED.  LT AILERON QUADRANT BRACKET REMOVED P/N 85711569-001.  POST S/B 8-57-27 QUADRANT BRACKET TO BE INSTALLED.  NEW BRACKET IS IN SHEET METAL SHOP.  REMOVED AND REPLACED NEW LT AILERON QUADRANT BRACKET IAW SB 8-57-27. LT WING AILERON TERMINAL QUADRANT,  PREVIOUSLY REMOVED FOR SHEET METAL ACCESS, INSTALLATION COMPLETED AS IAW AMM 27-12-31 TOTHE END OF STEP 12.  INDEPENDENT INSP CARRIED OUT ON DEFECT 814228. M7109 FUNCTION TEST 1.C. COMPLETED FOR THOSE PORTIONS OF THE SYS THAT HAVE BEEN DISTURBED AND FOUND TO WORK NORMALLY M7128.                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090102     WP  2009       1          2          CA081203012      120081126G61206506196         VALVE                                   CVAC  580   580         2422806WP                                                               PROP PITCH LOCK FAILED          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) IN FLIGHT, CREW EXPERIENCED A FAILURE OF THE NR 2 ENG PITCH LOCK VALVE. ENGINE WAS E-HANDLED AND AC LANDED WITHOUT INCIDENT. MAINT REPLACED THE NR 2 PITCH LOCK VALVE AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T    RT                             
             20090102     EA  2009       1          2          CA081204001      120081202G2820CN6273003001    PIPE                                    CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              FUEL FLOW       CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       9796 9796                                                      (CAN) MX FOUND NR1 ENGINE MOTIVE FLOW PIPE CHAFED LEAKING FUEL. PIPE WAS REPLACED, ENGINE RUNS AND LEAK CHECKS COMPLETED SATISFACTORY. CAUSE OF CHAFING COULD NOT BE CONFIRMED. IT WAS REPORTED THAT THE NEAREST DRAIN LINE WAS AT LEAST .5 INCH AWAY AND ALL SEEMED PROPERLY SECURED.                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E00063EN             
             20090102     NM  2009       1          2          CA081204002      120081108G2497                WIRE                                    DHAV  DHC8  DHC8201     2809001NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ALTERNATOR      DAMAGED         W      D   RETURN TO BLOCK                                                                                 H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA                                                                      (CAN) NR1 AND NR2 AC GEN ANNUNCIATIONS ILLUMINATED DURING TAXI. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE FOLLOWING DISCREPANCY HAD OCCURED.  FOUND WIRE 2421-10002FILB-1 AND WIRE 2421-2000IGI2A-1 WORN THROUGH AND SHORTED AT STA YH59:00 ON LT WING REAR SPAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090102     EU  2009       1          2          CA081204003      120081204G271004820203        SENSOR                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  LT AILERON      UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FDR CORRELATION CHECK REVEALED LT AILERON ROLL SENSOR UNSERVICEABLE.  SENSOR INSPECTED.  OPERATING CABLE FRAYED AND BINDING. SENSOR REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20090102     NE  2009       1          2          CA081204005      320081204G6111SFA13MIROASK112 BLADE                                   AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            6717                                                      (CAN) LEADING EDGE NICKEL SHEATH VISUALLY INSPECTED AND A CRACK NOTED. IF PRESSURE APPLIED TO BLADED CRACK BECAME MORE NOTICEABLE. BLADE REMOVED FROM SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
             20090102     NM  2009       1          2          CA081204006      120081203G3397                WIRE                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  CABIN LIGHT     SHORTED         W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA       42386                                                          (CAN) SPARKS/SMOKE FROM SIDEWALL LIGHT 1C, BALLAST CONFIRMED THE SOURCE. CREW DROPPED PSU PANEL TO FUND THE SOURCE AND CONFIRM SHORTING OF THE FORE/AFT WIRES TO THE AFT JUNCTION BOX.  WIRING REPAIRED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090204     EA  2009       2          4          CA081204007      120081202G3234                SHAFT                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              MLG HANDLE      WORN            W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) DURING MX OPERATION OF THE LANDING GEAR MANUAL RELEASE HANDLE IT STUCK IN THE RELEASE POSITION.  MX TROUBLESHOOTING FOUND THE RELEASE HANDLE SHAFT BINDING DUE TO INTERNAL WEAR AND SLIGHTLY BENT.  RELEASE HANDLE ASSY WAS REPLACED IAW AMM 32-34-01.  ACF TT 14745 HOURS, 123110 CYCLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
             20081229     SW  2008       12         29         CA081204008      120081127G52104744            HINGE PIN                               BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2A     41514EA  MCAULY1A200 1A200*      GL  PAX DOOR        RUSTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AN ATTEMPT TO REMOVE THE ENTRANCE DOOR USING THE EMERGENCY EXIT HANDLE FOUND THAT THE SYS HAD BECOME SEIZED.   UPON CLOSER INSP, IT WAS FOUND THAT THE HINGE PIN (DISPITE PERIODIC LUBING) HAD BECOME RUSTED TO THE AIRFRAME PIN TABS. THE DOOR CONTINUED TO OPEN AND CLOSE PROPER USING THE NORMAL SYS. THE ONLY SYS THAT FAILED IS THE JETTISON PORTION OF THE SYS. THE MM DOES NOT CALL FOR LUBBING OR FUNCTION CHECKING THIS SYS. IT HAS BEEN APPROXIMATELY 2000 HRS SINCE THE LAST RECORDED REMOVAL OF THE DOOR.                                                                                                                                                                                                                     1H71 3O3  O  A21CE   E286    5  NP874     
             20081219     CE  2008       12         19         CA081204009      120081201G7820175400125       MUFFLER                                 CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       799                                                            (CAN) WHILE CARRYING OUT AD CF90-03R2 A SMALL LEAK WAS NOTED AT THE TOP OF THE EXHAUST PIPE JUNCTION WITH THE MUFFLER BODY.  THIS IS A COMMON PLACE FOR THESE MUFFLERS TO FAIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    E274    5  NP910     
             20081219     CE  2008       12         19         CA081204010      120081201G7820175400122       MUFFLER                                 CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1611                                                           (CAN) DURING PREFLIGHT INSPECTION, A 2" CRACK IN THE END OF TAILPIPE WAS NOTED, RUNNING PARALLEL TO THE PIPE AXIS. THE CRACK APPEARS TO BE AT THE EDGE OF A HOT SPOT CAUSED BY THE WAY THE EXHAUST GASES FLOW OUT OF THE PIPE AND MAY HAVE BEEN A RESULT OF THERMAL STRESSES SET UP BY UNEVEN HEATING.                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E274    5  NP910     
             20081222     NM  2008       12         22         CA081204011      120081129G29317G773           PRESSURE SWITCH                         DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) NR 2 EDP AMBER LIGHT CAME ON AT 30 KTS. DURING TAKE-OFF ROLL.  ABORTED TAKE-OFF.  PRESS WAS NORMAL ON THE INDICATOR, BUT THE NR 2 EDP AMBER CAUTION LIGHT IS ON. TR128.  CONNECTOR ON PRESSURE SWITCH CLEANED.  NR 2 SYSTEM HYD PRESSURE SWITCH REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090204     EA  2009       2          4          CA081204012      120081202G5610NP139321003     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         BROKEN          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, RT (F/O) WINDSHIELD SHATTERED, WITH NO LOSS OF PRESSURIZATION.  CAPTAIN DESCENDED AND DECLARED AN EMERGENCY LANDING RT WINDSHIELD (P/N OFF: NP139321-003) CHANGED IAW AMM 56-11-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA21EA                        
             20090204     NE  2009       2          4          CA081204013      220081127G7261GE6087T04P0     SCREEN                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              SCAV PUMP       OBSTRUCTED      W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       21013                                                          (CAN) IFSD EN ROUTE FROM PHL - PIT.  LOSS OF ENGINE OIL PRESSURE AT FLIGHT FL340.  LEFT ENGINE RED OIL PRESSURE CAS MESSAGE ILLUMINATED.  OIL PRESSURE READ 23 PSI PRIOR TO ENGINE SHUTDOWN.  OIL TEMP WAS NORMAL PRIOR TO ENGINE SHUTDOWN.  AIRCRAFT WAS DIVERTED MADE AN UNEVENTFUL LANDING AT PIT.  INSPECTION BY MAINTENANCE REVEALED COKING AROUND THE SCREEN.  LUBE PUMP WAS REMOVED AND REPLACED IAW TO 70-21-01.  AIRCRAFT RETURNED TO SERVICE WITH NORMAL OPERATION.  (TC NR 20081204013)                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20081219     NE  2008       12         19         CA081205001      220080723G7200                ENGINE                                  DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 2            DAMAGED         W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CLCLIMB          1                      CA            9400                                                      (CAN) AN ACFT RETURNED TO BASE DUE TO ENGINE NR 2 FIRE WARNING LIGHT ILLUMINATE.  ENGINE FOUND DAMAGED AND REMOVED FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081229         2008       12         29         CA081205002      420081123G34008221577202      DISPLAY                                 CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              MFD 1           INOPERATIVE     W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       DEDESCENT        1                      CA                                                                      (CAN) 30 MINUTES PRIOR TO LANDING, THE PILOT PRIMARY FLIGHT DISPLAY(PFD 1) WENT BLANK. THEN IAW AFM (SECTION 05-15-1) THE CREW SELECTED THE REVERSION MODE TO HAVE THE MULTIFUNCTION DISPLAY (MFD 1) IN COMPRESSED MODE, AT THAT TIME THE MFD 1 ALSO WENT BLANK. THE CREW RESELECTED REVERSION TO NORMAL, BOTH DISPLAY RETUNED TO NORMAL. APPROXIMATELY 10 MINUTES LATER, THE PFD 1 BLANK AGAIN AND OPERATED ON AND OFF EVERY 2- 3 MINUTES UNTIL LANDING. CONDITION WAS NO LONGER PRESENT AFTER FLIGHT AND REVERSION SYS WORKED NORMALLY. WIRING VERIFICATION DONE NO ANOMALY NOTED. AFD (PFD 1 POSITION) REPLACED IAW AMM 31-61-00. THE MFD 1 (P/N: 822-1917-202 S/N: 2NKRG) WAS ALSO REPLACED BUT A PRECAUTIONARY MEASURE . ACFT RETUNED TO SE2L72 4F4  FRTA21EA   E15NE                
             20081222     EA  2008       12         22         CA081205003      120081204G5720                SUPPORT BRACKET                         DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE                              AILERONS        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT AND RT WING AILERON INPUT QUADRANT SUPPORT BRACKETS AT YW414.00 CRACKED.  QUADRANT SUPPORT BRACKETS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE                
             20090203     SW  2009       2          3          CA081205004      120081126G7603C8102415        CONTROL CABLE                           SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              POWER LEVER     BROKEN          W      C   ABORTED TAKEOFF                                                                                 F  FLT CONT AFFECTED                                                             TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAXI, CREW SELECTED SPEEDS HIGH & APPLIED POWER.  AS POSITIVE TORQUES WERE CALLED TROUGH ABOUT 1200FT/LBS, A SNAP WAS HEARD & THE LT POWER LEVER ADVANCED FORWARD WITH NO FURTHER ENGINE POWER INCREASE.  TAKEOFF ABORTED & CREW SLOWLY REDUCED POWER TO FLIGHT IDLE.  LT ENGINE DID NOT RESPOND TO FURTHER POSITIVE POWER LEVER INPUTS BUT WOULD RESPOND WHEN REDUCED TO FLT IDLE.  ACFT TAXIED BACK TO APRON & SHUTDOWN.  MX DETERMINED LT ENGINE POWER LEVER CABLE SECTION FROM POWER LEVER QUADRANT TO WING ROOT HAD BROKEN.  NO DEFINITIVE CAUSE FOR BREAK DETERMINED BUT IT WAS AT THE POINT WHERE PROPER ROUTING OF CABLE REQUIRES A SIGNIFICANT BEND IN CABLE ASSY.  CABLE REPLACED & ACFT RETURNED TO SERVICE.            2L72 4T4  TRTA8SW    E4WE                 
             20081229     NM  2008       12         29         CA081205006      120081202G3240244300          STATOR          BFGOODRICH              BOEING727   727223      1384074NM  PWA   JT8   JT8D15      52051NE                              BRAKE ASSY      BROKEN          W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING PUSHBACK ON C-FCJF EXCESSIVE FORCE WAS REQUIRED TO MOVE ACFT AND DETERMINED NR2 MAIN WHEEL WAS DEFLATED. ACFT PULLED BACK TO GATE FOR INVESTIGATION.  MAINT WAS UNABLE TO REMOVE NR2 WHEEL. AFTER SEVERAL EFFORTS WITHOUT SUCCESS IT WAS DECIDED THE TIRE AND POSSIBLY THE WHEEL WOULD HAVE TO BE CUTOFF.  AFTER CUTTING A SECTION OF THE TIRE OFF IT WAS DETERMINED A PIECE OF THE BRAKE STATOR HAD BROKEN OFF AND PENETRATED THE WHEEL HUB AS THE ACFT WAS TOWED DEFLATING THE TIRE AND MAKING IT IMPOSSIBLE TO REMOVE WHEEL. THE BROKEN PIECE OF THE STATOR WAS REMOVED ALLOWING REMOVAL OF THE WHEEL.   WHEEL AND BRAKE ASSY REPLACED.                                                                                         2L73 4F4  F  A3WE    E2EA                 
             20081222     CE  2008       12         22         CA081205007      120081204G37105100106377      LINE                                    CESSNA414   414A        2075907CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF32C3AF32C505   GL  VACUUM SYS      CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       5291                                                           (CAN) UPON REACHING CRUISE FLIGHT AND ACTIVATING AIRFRAME PNEUMATIC DE-ICE SYSTEM, THE BOOTS WOULD REMAIN PARTIALLY TO MOSTLY INFLATED.  THIS PROBLEM WOULD NOT DUPLICATE ON A GROUND RUN.   THE VACUUM LINE TO THE FLOW VALVES WAS INSPECTED AND A LINE ASSEMBLY TO THE TAIL FLOW VALVE WAS FOUND CORRODED WHERE IT PASSED OVER AN ENVIRONMENTAL DUCT AT APPROX. MID CABIN.  THE LINE ASSEMBLY WAS REPAIRED.   THE ACFT WAS GROUND RUN AND FLOWN TO CRUISE ALTITUDE TO MAX. CABIN PRESSURE DIFFERENTIAL, AND THE PNEUMATIC DE-ICE SYSTEM FUNCTIONED PROPERLY.                                                                                                                                                                                  1L72 3O3  O  A7CE    E8CE    5  CP22EA    
             20081229     SW  2008       12         29         CA081205008      120081204G5610HYLZ88821       WINDSHIELD                              FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   29073NE  MCAULY4HFR344HFR34C652  NE  COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE LT WINDSHIELD SHATTERED. MX WAS DISPATCHED TO REPLACE THE WINDSHIELD. THE TEMP CONTROLLER WAS FOUND TO BE DEFECTIVE ALSO.  TEMP CONTROLLER REPLACED ALONG WITH WINDSHIELD AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
             20081219     EA  2008       12         19         CA081207001      220081202G7414106006169       MAGNETO                                                                    LYC   O540  O540F1B5    41532EA                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CA            302                                                       (CAN) AFTER START MAG CHECK PERFORMED AND LT MAG FAILED.  MX WAS NOTIFIED AND WHEN MAG WAS LOOKED AT FOUND THAT THE BREAKER POINT WIRES HAD VIBRATED OFF.  WIRES REPAIRED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             3  O          E295                 
             20081219     CE  2008       12         19         CA081208001      120081119G3222SK1759          FORK                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  NOSE GEAR       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       1514615146                                                     (CAN) ON ROLL OUT FROM LANDING NOSE WHEEL BROKE OFF.  ACFT SLID APPROX. 400` ON NOSE AND CAME TO A STOP.  APPARENT CAUSE METAL FATIGUE OF NOSE WHEEL FORK.  TSB HAS SECURED FAULTY PARTS AND INVESTIGATING FURTHER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E274    5  NP910     
             20081222     NM  2008       12         22         CA081208002      120081207G3231483023          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              LT MLG DOOR     MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA            1398                                                      (CAN) FLIGHT CREW REPORT: LT MAIN AMBER GEAR DOOR LIGHT FAILED TO EXTINGUISH ON GEAR RETRACTION (VISUALLY OPEN). ALT EXTENSION PERFORMED.  REPLACED LT MLG SSV IAW 32-31-41                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN             
             20081222     SO  2008       12         22         CA081208005      120081208G8120                BEARING                                 PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              TURBOCHARGER    FAILED          W      AD  UNSCHED LANDING         RETURN TO BLOCK                                                         ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CLCLIMB          1                      CA            36                                                        (CAN) SHORTLY AFTER TAKE-OFF THE PILOT HEARD A "BANG" FROM THE RT ENGINE AND NOTICED A LOSS OF MANIFOLD PRESSURE.  HE THEN RETURNED TO THE AIRPORT WITH NO PROBLEMS ENROUTE.  MX FOUND THE TURBO CHARGER SHAFT BEARING HAD FAILED.  THE TURBO CHARGER WAS REPLACED, OIL SUMP CLEANED, OIL FILTER REPLACED AND GROUND RUN ACCEPTABLE.                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A20SO   E14EA                
             20090204     EU  2009       2          4          CA081208007      120081201G243523085024        STARTER GEN                             PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NR 1            MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            54                                                        (CAN) PILOT REPORTED WAS NR 1 GENERATOR WENT OFF LINE PRIOR TO TAKEOFF.  WAS UNABLE TO RESET RETURNED TO BLOCKS.  NR 1 GENERATOR REPLACED AND GROUND RUN PERFORMED, ALL FOUND SATISFACTORY. (TC NR  20081208007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20090205     CE  2009       2          5          CA081208008      120081208G2435200SGL119Q2     STARTER GEN                             CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL                  FAILED          W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA            110                                                       (CAN) GENERATOR FAILED IN FLIGHT 12 MILES FROM YWG ENROUTE TO YQT.  AIRCRAFT RETURNED TO YWG (TC NR 20081208008).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA    5  CP60GL    
             20090205     NM  2009       2          5          CA081208009      120081201G5751                BRACKET                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE                              AILERONS        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING MAINTENANCE INSPECTION BOTH THE LT AND RT AILERON QUADRANT SUPPORT BRACKETS WERE FOUND CRACKED.  PART NUMBERS INCLUDED, LT END PIECE P/N 85711570-101, RT END PIECE P/N 85711570-102, LT BOTTOM PLATE P/N 85711572-101, RT BOTTOM PLATE 85711572-102, OF NOTE WHEN THE RT END PIECE WAS REMOVED THERE APPEARED TO BE EVIDENCE OF AN APPARENT PREVIOUS WELD REPAIR OF UNKNOWN ORIGIN.  A CHECK OF THE AIRCRAFT MAINTENANCE HISTORY COULD NOT FIND A RECORD OF SUCH A REPAIR.  ALL CRACKED BRACKETS WERE REPLACED.  (TC NR 20081208009)                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE                
             20081222         2008       12         22         CA081208011      120081126G78309007M60G46      COWLING                                                                    GE    CF6   CF650C2     30018NE                              THRUST REVERSER DELAMINATED     W      E   ENGINE SHUTDOWN                                                                                 ED VIBRATION/BUFFET          INFLIGHT SEPARATION                                 DEDESCENT        1                      CA                                                                      (CAN) ON DESCENT INTO YYC, WITH POWER LEVERS AT IDLE, THE ACFT SHUDDERED MOMENTARILY.  THE NR 2 THRUST REVERSER UNLOCK LIGHT ILLUMINATED AND IN-FLIGHT SHUT DOWN OF NR 2 ENGINE WAS CARRIED OUT.  THE ACFT LANDED WITHOUT INCIDENT AND AN INSPECTION WAS CARRIED OUT ON NR 2 ENGINE.  NR 2 ENGINE RT TRANSLATING COWL WAS FOUND DELAMINATED WITH A SECTION OF THE COWL MISSING.  THE COWL WAS REPLACED, FUNCTION CHECKED AND THE ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                             4  F          E23EA                
             20090203     EA  2009       2          3          CA081209005      120081208G5711215003268       SPAR CAP                                CNDAIRCL215 CL2151A10   1900320EA                                                               WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4895                                                           (CAN) WHILE PERFORMING AD 92-26R1 NO DEFECTS WERE FOUND DURING ULTRASONIC INSPECTION OF REQUIRED INSPECTION AREA.  DUE TO PREVIOUS CONCERNS (3) WITH FINDING CRACKS OUTSIDE OF INSPECTION AREA FURTHER INVESTIGATION WAS PERFORMED.  CRACKS WERE FOUND IN LOWER SPAR CAP, LOWER WING SKIN AND BOTH REINFORCING STRAPS.                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4R    RTA14EA                        
             20081222     SW  2008       12         22         CA081209006      120080611G6300206040015103    DRIVE SHAFT                             BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              M/R DRIVE       FAILED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA                                                                      (CAN) ON DESCENT PILOT SMELLED BURNING GREASE.  AFTER LANDING AND POST FLIGHT INSPECTION FOUND GREASE THROWN FROM DRIVESHAFT COUPLING. DRIVESHAFT WAS REPLACED AND FOUND ISOLATION MOUNT TO BE WEAK.  REPLACED ISOLATION MOUNT AND PROBLEM WENT AWAY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
             20081222     CE  2008       12         22         CA081210001      120081108G32455005            TUBE                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              MLG TIRE        TORN            W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THE NOSE TIRE INNER TUBE HAD 195 HRS SINCE NEW.  IT WAS FOUND RIPPED. NO HARD LANDING WAS REPORTED.  THE INSIDE OF THE TIRE WAS FOUND FREE OF ANY DEFECTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274                 
             20081222     CE  2008       12         22         CA081210002      120081208G32455005            TUBE                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              NLG TIRE        TORN            W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THE NOSE WHEEL TIRE INNER TUBE HAD 220 HRS SINCE NEW.  IT WAS FOUND TORN ON THE SIDE WALL.  NO HARD LANDING WAS REPORTED.  THE INSIDE OF THE TIRE WAS FOUND FREE OF DEFECTS.  THIS TO ME IS AN OBVIOUS MANUFACTURING PROBLEM.  IT HAPPENED ON TAXI FROM THE RUNWAY AFTER NORMAL LANDING.                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    E274                 
             20081222     SO  2008       12         22         CA081210003      120081208G32455005            TUBE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              NLG TIRE        TORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       391                                                            (CAN) THE NOSE WHEEL TIRE INNER TUBE WAS FOUND TORN.  THE ACFT SAT OVER NIGHT.  THE INNER TUBE HAD 391 HRS SINCE NEW.  THE NOSE TIRE WAS INSP, NO DEFECTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A13    E274                 
             20090203     GL  2009       2          3          CA081210004      120081209G2421A3579101        GENERATOR                               BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                              APU             FIRE            W      O   OTHER                                                                                           ABJFLAME/FIRE                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        DEDESCENT        1                      CA                                                                      (CAN) AFTER APU START AT FL100 JUST BEFORE APU GEN ON LINE APU FIRE CAS MESSAGE POSTED.  PILOTS ARM APU BOTTLE MESSAGE DISAPPEARED.  PILOTS SHUTDOWN APU AND LAND A/C SAFELY.  IN AFT EQUIPMENT BAY PILOTS NOTED AN ODOR OF BURNED WIRE.  AFTER INSPECTION OF APU GENERATOR FOUND GENERATOR ON FIRE.  FIRE WENT OUT VIA COOLING DUCT TO EDUCATOR SENSING ELEMENT OF APU FIRE DETECTION SYSTEM.  APU DOOR SHOWING SIGNS OF FIRE.                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTT00005NYE00010LA             
             20081222     NM  2008       12         22         CA081210005      120081209G3213654611635       CYLINDER                                BOEING737   737232      1384475NM  PWA   JT8   JT8D17      52049NE                              STRUT           WORN            W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       3795216636                                                     (CAN) RT MLG LOST FLUID.  DURING ATTEMPTED SEAL CHANGE, THE INNER CYLINDER OF THE GEAR HAD A 6" BY 2" PIECE OF CHROME MISSING FROM THE INNER CYLINDER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16WE   E2EA                 
             20090203     CE  2009       2          3          CA081210006      120081208G5220115430100661A   SKIN                                    BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              EMERGENCY EXIT  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9902                                                           (CAN) WHEN COMPLYING WITH SPECIAL INSPECTION "ESCAPE HATCHES AND ASSOCIATED AREAS", A CRACK WAS FOUND AT THE LOWER FORWARD CORNER OF THE BONDED RT EMERGENCY EXIT DOOR SKIN, EXACTLY AS PICTURED IN THE MAINTENANCE MANUAL.  REPLACED SKIN ASSEMBLY WITH NEW.  CRACKS ARE DIFFICULT TO DETECT DUE TO FILLER USED BY THE MANUFACTURER TO BLEND THE RADIUS AFTER FITTING THE SKIN.  OUR INSPECTION TSK IS AMENDED TO INDICATE THE INTERIOR PANEL IS TO BE REMOVED AND INSPECTED FROM THE INSIDE.  HIGH TIME/HIGH CYCLE B300 OF OUR FLEET OF FIVE AIRCRAFT.                                                                                                                                                                                        2L72 4T4  T  A24CE   E4EA                 
             20081229     NE  2008       12         29         CA081210008      220081204G7250FW45914         TURBINE BLADES                          BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              ENGINE          FAILED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA            5094                                                      (CAN) SURGE/IFSD/ENGINE SHUTDOWN IN FLIGHT WITH TGT CLIMBING THROUGH 1100 C.   BOROSCOPE OF ENGINE 13299 TODAY FOUND THAT 2 OFF HPT STAGE 1 BLADES SUFFERED FROM A BELOW-PLATFORM FAILURE. THE 2 FAILED BLADES ARE SEPARATED BY 28 BLADES. THE AIRFOILS ON ALL OF THE REMAINING BLADES HAVE BEEN KNOCKED OFF ABOVE THE PLATFORM.                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FTRA6WE    E00061EN             
             20081222     NE  2008       12         22         CA081210009      220081201G7200                ENGINE                                  AEROSPATR42 ATR42*      8680900EU  PWA   120   PW120            NE                                              ODOR            W      E   ENGINE SHUTDOWN                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE PILOTS NOTICED OIL ODOR AND MIST IN THE CABIN.  THEY TURNED THE AIR BLEED FROM THE ENGINE OFF AND THE MIST AND ODOR DISAPPEARED.  SOON AFTER, OIL PRESSURE FLUCTUATIONS AND THEN A DROP IN PRESSURE OCCURRED.  THE PILOTS SHUT DOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING.  GROUND INSPECTION FOUND LOW OIL LEVEL, BOROSCOPE INSPECTION OF THE AIR INLET WAS MADE AND REVEALED OIL LEAK FROM C OR D FLANGE AND THE REAR INLET CASE IS FLOODED WITH OIL.  THE ENGINE WILL BE REMOVED.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                         2H72 4T4  TRTA53EU   E20NE                
             20081229     NE  2008       12         29         CA081210010      220081127G7200                ENGINE                                  FOKKERF27   F27MK50            EU  PWA   PWA120PW125B           NE                                              POWER LOSS      W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB AFTER T/O, ENGINE POWER LOSS OCCURRED (AT APPROX 300 FT ALTITUDE). THE ENGINE WAS SECURED AND A TURNBACK INITIATED. THE ACFT MADE A SINGLE ENGINE LANDING. POST EVENT INSP FOUND FRACTURED HP BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA817    E20NE                
             20090203     EA  2009       2          3          CA081210011      220081210G7200                ENGINE                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              NR 1            SHUTDOWN        W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) NR 1 ENGINE SHUTDOWN CARRIED OUT AFTER TAKEOFF.  HERE IS THE DEFECT ENTERED BY THE FLIGHT CREW "LT PROP RPM ONLY GOES TO 1500 RPM ON TAKEOFF AS POWER REDUCED RPM DROPS".  THE INCIDENT IS UNDER INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA24CE   E4EA                 
             20090203     EU  2009       2          3          CA081210012      120081208G5530313108          BRACKET                                 ISRAEL1124  1124        4500102EU  GARRTTTFE731TFE73131G   29003NE                              VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9341                                                           (CAN)  FOUND CRACK IN BRACKET LOCATED ON THE FORWARD SIDE OF THE VERTICAL STAB ATTACH FITTING AT FS 521.75.  THREE CRACKS EXTEND FROM THE RIGHT OUTBOARD ATTACHMENT BOLT HOLE.  THE ATTACHING BOLTS RUNS HORIZONTALLY FWD AND AFT THROUGH THE RUDDER STOP BRACKET, VERTICAL STAB ATTACH FITTING, AND THROUGH THE BRACKET (P/N: 313108) WHICH IS CRACKED.  REFERENCE IPC: 53-40-00 FIG 1 (SHEET 2) PAGE 1, PART SHOWN DIRECTLY BELOW ITEM 32.                                                                                                                                                                                                                                                                                                    2M72 4F4  F  A2SW    E6WE                 
             20081222     NE  2008       12         22         CA081210013      220081128G7414BL600646201     MAGNETO                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAGNETO FOUND U/S.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
             20081229     EA  2008       12         29         CA081211002      320080116G6111W69EK763        PROPELLER                               DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  TIP OF BLADE    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       354                                                            (CAN) PRIOR TO A TRAINING FLIGHT WITH A STUDENT A WALK AROUND WAS PERFORMED ON THE ACFT WHERE IT WAS NOTED THAT ONE OF THE PROPELLER BLADE LEADING EDGE TIPS HAD AN INDICATION OF POSSIBLE ROCK CHIP DAMAGE OF APPROXIMATELY .2500 INCH IN LENGTH AND LESS THAN A .0625 INCH IN DEPTH.  IT SHOULD ALSO BE NOTED THAT THE PREVIOUS CREW HAD REPORTED A SLIGHT ENGINE VIBRATION AT 1700 RPM. UPON INSP BY AN AME IT WAS DETERMINED THAT IN FACT THERE WAS A SLIGHT NICK POSSIBLY CAUSED BY A SMALL ROCK. UPON FURTHER INVESTIGATION A CRACK WAS FOUND THAT WAS LOCATED AT THE MIDPOINT OF THE BLADE AT THE VERY TIP AND EXTENDED INWARD APPROX 2 INCHES. BY APPLYING PRESSURE TO EITHER OPPOSING SIDES OF THE BLADE TIP THE CRACK BECAME VERY APPA1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20081229     EA  2008       12         29         CA081211003      320081110G6111W69EK763T       PROPELLER                               DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  TIP OF BLADE    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       331                                                            (CAN) IN BETWEEN AND PRIOR TO A TRAINING FLIGHT THE PILOT AND STUDENT CONDUCTED A WALK AROUND WHERE IT WAS NOTICED THAT ON THE NR1 BLADE TIP THERE APPEARED TO BE A CRACK EMANATING FROM THE CENTER OF THE BLADE TIP WHICH EXTENDED INWARD TOWARDS THE ROOT. AN AME CONDUCTED A VISUAL INSPECTION UNDER 10X MAGNIFICATION AND VERIFIED THAT A CRACK EXISTED FROM THE CENTER OF THE NR1 BLADE TIP AND EXTENDED APPROX 2 INCHES INWARD TRAVELLING TOWARDS THE BLADE ROOT. THE AIRCRAFT WAS IMMEDIATELY REMOVED FROM SERVICE WHERE A NEW PROPELLER ASSEMBLY WAS INSTALLED.                                                                                                                                                                         1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
             20090203     NM  2009       2          3          CA081211004      120081203G531085312397101     BRACKET                                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  WINDOW          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING THE ACCOMPLISHMENT OF TASK 5310/06C, WINDSHIELD AND SIDE WINDOW LOWER SILL JOINT TO SIDE POST, THE BRACKET CONNECTED TO UNDERSIDE OF THE LOWER SILL TO THE SIDE POST (RIGHT SIDE) WAS FOUND TO HAVE A 2 1/2 INCH CRACK IN IT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090206     EA  2009       2          6          CA081211005      120081204G533021530023        SKIN                                    CNDAIRCL215 CL2156B11215       EA                                                               FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A MX INSPECTION, AN EMPLOYEE FOUND A CRACK ON THE TOP SKIN FS 388 RSTR 9. DWG 215-30023-175 AOM 53-30-00-103 REV A.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T    RTA14EA                        
             20081222     CE  2008       12         22         CA081212002      120081205G2421                BEARING                                 CESSNA421   421B        2076014CE  CONT  O520  GTSIO520H   17032SO                              ALTERNATOR      FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        BH SMOKE/FUMES/ODORS/SPARKS  ELECT. POWER LOSS-50 PC                             CRCRUISE         1                      CA            16                                                        (CAN) IN CRUISE PILOT NOTICED SPARKS COMING FROM RT ENGINE.  UPON EXAMINATION ON GROUND BY MX, ALTERNATOR OUTER BRG. FAILED.  SHAFT DEFORMED FROM HEAT.  FAILURE OF CRANKSHAFT ALTERNATOR DRIVE GEAR CAUSED MAJOR INTERNAL ENGINE DAMAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7CE    E7CE                 
             20090203     NE  2009       2          3          CA081212003      220081212G7320J2009P03        PLUG                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              MFC             LOOSE           W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE CHECK, A FUEL LEAK WAS DISCOVERED COMING FROM THE NR 2 ENGINE MFC.  UPON FURTHER INVESTIGATION A PLUG WAS FOUND LOOSE.  THE PLUG WAS REMOVED, THE O-RING REPLACED AND THE PLUG RE-INSTALLED.  A LEAK CHECK WAS CARRIED OUT WITH NO LEAKS NOTED IPC REF IS 73-11-00, FIG. 5-380.  A RECORDS CHECK WAS CARRIED OUT AND NO PREVIOUS WORK WAS NOTED IN THIS AREA.  THIS PLUG IS NORMALLY NOT TOUCHED IN SERVICE, IT WOULD NORMALLY ONLY BE LOOKED AT DURING OVERHAUL OR BENCH CHECK.                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20090203     CE  2009       2          3          CA081212004      120081209G3244301401311       TIRE                                    CESSNA441   441         2076020CE  GARRTTTPE331TPE33110N   29062NE                              MLG             DEFECTIVE       W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       184                                                            (CAN) DEFECT IN SIDEWALL CAUSED SIGNIFCANT LOSS OF PRESSURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  TRTA28CE   E4WE                 
             20090203     NE  2009       2          3          CA081212005      320081212G61116607122666      BLADE                                   SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F25 NE  NR 2            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       389844641                                                      (CAN) THE PROP IN QUESTION WAS REMOVED FOR DISASSEMBLY TO BE SENT FOR DELAMINATION BEYOND LIMITS TO THE MANUFACTURER.  WHEN THE PROP ASSEMBLY WAS DISASSEMBLED, A RADIAL CRACK WAS DISCOVERED IN NR 2 BLADE MEASURING IN EXCESS OF 6 INCHES IN THE HUB OF THE BLADE S/N: SF340-132/234.  IT WAS DISCOVERED VISUALLY AND HAS SUBSEQUENTLY BEEN SENT FOR REPAIR TO THE MANUFACTURER.                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
             20090203     NE  2009       2          3          CA081212006      220081209G7210310838801       WASHER          PWC                     DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE                              NR 9 BEARING    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NR 2 ENGINE RGB METAL CHIP FOUND ON CHIP DETECTOR.  DETERMINED TO BE NON-ALLOWABLE CATEGORY 1 DEBRIS, IDENTIFIABLE FRAGMENT.  ALSO WASHER WAS CRACKED ENGINE S/N 123037 RGB S/N 123124  DEBRIS IDENTIFIED AS NR 9 BEARING KEY TAB WASHER TAB. IN CONSULTATION WITH MANUFACTURER THE COMPONENT WAS GIVEN A 10 HOUR REINSPECT, .10 HOUR, REINSPECT COMPLETED WITH NO FURTHER ANOMALIES.                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE                
             20090203         2009       2          3          CA081212007      220081027G74144372            STOP PIN                                                                                                                                MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       764                                                            (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
             20090206         2009       2          6          CA081212008      220081212G74144372            STOP PIN                                                                                                                                MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       328                                                            (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
             20090203     CE  2009       2          3          CA081212010      120081209G3260                WARNING LIGHT                           BEECH 200   200BEECH    1152920CE                                                               MLG             UNKNOWN         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) ON DEC 9TH, RETURNING FROM KGEG TO CYYC - ON TAKEOFF, WHEN THE GEAR WAS RETRACTED, THE FLIGHT CREW NOTICED THE "RED" GEAR LIGHTS WERE INDICATING THAT THE GEAR WAS NOT FULLY RETRACTED.  FLIGHT CREW CYCLED THE GEAR ONCE MORE AND ON THAT ATTEMPT WERE ABLE TO CONFIRM THAT THE GEAR WAS LOCKING DOWN, BUT ONCE BROUGHT UP THE RED LIGHTS DID NOT GO OUT.  THE FLIGHT CREW DID A VISUAL INSPECTION OF EACH MAIN GEAR WHEEL AND CONFIRMED THAT THE MAIN WHEELS WERE INDEED UP.  AT ALTITUDE, THE FLIGHT CREW CYCLED THE GEAR ONCE MORE AND THE LIGHTS WENT OUT INTERMITTENTLY, BUT SHORTLY AFTER STARTED TO COME ON AGAIN.  THE FLIGHT CREW MAINTAINED THE GEAR EXTENSION SPEED OF 181KTS FOR THE REMAINDER OF THE FLIGHT.  OTHER THAN HAV1L72 4T      A24CE                        
             20090203     CE  2009       2          3          CA081212011      120081204G8000C2925010105     SWITCH                                  CESSNA150   150M        2071830CE  CONT  O200  O200A       17020SO  MCAULY1A102 1A102OCM    GL  STARTER         UNSERVICEABLE   W      O   OTHER                                                                                           MBHOVER TEMP                 SMOKE/FUMES/ODORS/SPARKS  ELECT. POWER LOSS-50 PC   NRNOT REPORTED   1                      CA                                                                      (CAN) HAD STARTER FAILURES WHERE THEY SEIZED AND OVERHEATED.  INVESTIGATION REVEALED THAT IF PILOT AGGRESSIVELY ROTATED KEY IN CLOCKWISE DIRECTION THAT KEY WOULD JAM AND LEAVE SWITCH IN THE START POSITION.  THIS WOULD CAUSE THE STARTER TO REMAIN ENGAGED UNTIL IT SMOKED.  REPLACED SWITCH WITH NEW, ALL CORRECT.                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A19    E252    5  NP918     
             20090203     EU  2009       2          3          CA081212013      220081006G7210                SPLINE          ROTAX                                                      ROTAX 912   ROTAX912F3       EU                              PROP SHAFT      CHIPPED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1465 44                                                        (CAN) METAL CHIP FOUND ON MAGNETIC PLUG DURING SERVICING.  TRACED TO GEARBOX.  GEARBOX REMOVED AND CHIP WAS FOUND TO BE FROM TOP SPLINE OF THE PROPSHAFT JUST ABOVE THE RING HALF.  POSSIBLE CAUSE, COULD BE FROM A "STEP" WORN IN FROM RING HALF.  IF RING HALF WAS INSTALLED WITH THIS STEP RESTING ON THE RING SURFACE IT COULD CAUSE A STRESS POINT.  THERE IS A SLIGHT CORRESPONDING WEAR MARK 180 DEGREES FORM THE CHIP THAT INDICATES THE CHIP IS RELATED TO THE PREV RING HALF LOCATION.  PROPSHAFT HAD PASSED NDT 44.5 HRS PRIOR (OVERHAUL).  AREA COULD HAVE BEEN UNDER HIGH LOAD DUE TO STEP WORN INTO SPLINE.  PROPSHAFT REPLACED.  INCLUDE INSPECTION FOR THIS TYPE OF WEAR IN FUTURE WORK.                                               3  O          E00051EN             
             20090206         2009       2          6          CA081212015      420081117G256297A256000000    ELT                                                                                                                                     CABIN           MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) A NR OF INSTANCES OF UNCOMMANDED TRANSMISSIONS HAVE OCCURRED ON 406MHZ ELTS INSTALLED ON OUR ACFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
             20090203     NM  2009       2          3          CA081214001      120081213G28208SC0764         CHECK VALVE                             BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              FUEL SYSTEM     FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING THE UNSCHEDULED REMOVAL OF THE NR 2 ENGINE FUEL FLOW TRANSMITTER, RESIDUAL AIRFRAME FUEL WOULD NOT STOP FLOWING.  FURTHER INVESTIGATION REVEALED THE RIGHT WING FUEL TANK "MOTIVE FLOW CHECK VALVE" STUCK OPEN.  MOTIVE FLOW CHECK VALVE REMOVED AND REPLACED AS PER AMM 28-11-11.                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E00062EN             
             20090203         2009       2          3          CA081215003      420081209G611305503214        SPINNER                                 CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       148                                                            (CAN) CRACKS PERPENDICULAR TO TOP OF PROP BOLT HOLES BARELY VISIBLE TO THE NAKED EYE, CONFIRMED WITH LPI.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274    5  NP910     
             20090203     EA  2009       2          3          CA081215009      120081210G2750855D10011       BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       11166                                                          (CAN) DURING FINAL SEGMENT OF CLIMB, THE FLT CREW RECEIVED A FLAP FAIL MSG ON EICAS.  THE FLAPS WERE AT ZERO AND WERE INDICATING ZERO AT THE TIME.  THE QRH WAS FOLLOWED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE CHECKED FECU FOR FAULT CODES AND FOUND CODES FOR RT BPSU, FECU AND WIRING FOR RT BPSU.  THE SYSTEM WAS RESET, THE FLAPS WERE OPS CHECKED AND NO FURTHER DEFECTS NOTED.  AIRCRAFT RETURNED TO SERVICE.  IN CRUISE FLIGHT, THE FLT CREW RECEIVED A FLAP FAIL MSG.  THE FLIGHT CONTROL SYNOPTIC PAGE INDICATED THE FLAPS WERE OUTLINED IN YELLOW SHOWING ZERO DEGREES OF EXTENSION.  THE AIRCRAFT LANDED BACK WITHOUT INCIDENT.  MAINTENANCE PULLED FECU CODES (SEE ATTACHED) WHICH INDICATED R BPSU OR WIRING.  TH2L72 4F4  FRTA21EA   E15NE                
             20090203     SW  2009       2          3          CA081216001      120081110G5311206033107117    FRAME                                   BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON REMOVAL OF AFT CABIN HAT RACK ASSY RT FRAME ASSY WAS FOUND CRACKED.  FRAME ASSY WAS REMOVED AND REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E1GL                 
             20090203     SW  2009       2          3          CA081216002      120081110G5311206033302031    FRAME                                   BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON REMOVAL OF BELL INSTALLED HEATER ASSY.  A VISUAL INSPECTION WAS COMPLETED OF THE AREA`S SURROUNDING STRUCTURE.  THE LT AFT FRAME ASSY WAS FOUND CRACKED BEYOND LIMITS.  THE CRACK WAS NOTED TO PROTRUDE FROM A RIVET HOLE ACROSS THE FACE OF THE FRAME.  FRAME ASSY WAS REMOVED AND REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H2SW    E1GL                 
             20090203     EA  2009       2          3          CA081216003      220081211G7200                ENGINE                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                                              MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            3823                                                      (CAN) PILOTS HEARD A GRINDING SOUND FROM THE EXHAUST STACK WHEN PUTTING ON THE PROP TIE`S AFTER A FLIGHT.  MAINTENANCE CONFIRMED THE SOUND AND UPON REMOVING A EXHAUST STACK TO INVESTIGATE THEY VISUALLY CONFIRMED THAT THERE APPEARED TO BE A PIECE OF METAL CONTACTING THE NR 2 POWER TURBINE.  POWER SECTION WAS REMOVED AND REPLACED AND IS IN AT STANDARD AERO WINNIPEG FOR FURTHER INVESTIGATION AND REPAIR. TSO 3823.0, CSO 2033 (TTSN AND TCSN UNAVAILABLE AS LOG BOOKS ARE AT OVERHAUL FACILITY).                                                                                                                                                                                                                                     1L72 4T4  T  A24CE   E4EA                 
             20090203     SW  2009       2          3          CA081216004      120081214G56102719442004      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              COCKPIT         CRACKED         W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            3686                                                      (CAN) DURING TAXI AS THE CREW TURNED INTO A 35 KNOT HEADWIND THE FIRST OFFICER WINDSHIELD SHATTERED.  THE WINDSHEILD HEAT WAS SELECTED TO LOW AND THE OUTSIDE AIR TEMPERATURE WAS -36 DEGREES CELCIUS.  MAINTENANCE REPLACED THE WINDSHIELD IN ACCORDANCE WITH THE AMM AND WAS RELEASED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA8SW    E4WE                 
             20090203     EA  2009       2          3          CA081216005      120081212G2750                FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) FLAPS FAILED AT 3 DEGREES ON APPROACH.  NORMAL LANDING FOLLOWED.  CREW ABLE TO RESET SYSTEM ON THE GROUND AND FLIGHT CONTINUED UNDER MEL.  SECOND FLAP FAILURE ON AIRCRAFT 107 IN AS MANY FLIGHTS.  FLAPS FAILED AT 23 DEGREES INBOUND.  NORMAL LANDING OCCURRED.  MX RECTIFICATION TO FOLLOW ALL ACTUATORS REPLACED, RT BPSU REPLACED, LT NR 3 FLAP FLEX DRIVE REPLACED, RT NR 1AND NR 4 FLAP FLEX DRIVES REPLACED.  A/C THEN HAD TEST FLIGHT AND HAD ANOTHER FAILURE AT 38 DEGREES EXTENSION.  FLAP ELECTRONIC CONTROL UNIT AND FLAP PDU REPLACED AND A/C TEST FLIGHT WAS SUCCESSFUL.  A/C RETURNED TO SERVICE DEC 18,2008.                                                                                                             2L72 4F4  FRTA21EA   E15NE                
             20090203     NE  2009       2          3          CA081217001      220081213G7230                COMPRESSOR                              BOEING737   737201      1384454NM  PWA   JT8   JT8D17      52049NE                              NR 2 ENGINE     FOD             W      C   ABORTED TAKEOFF                                                                                 CA F.O.D.                    FLAME/FIRE                                          TOTAKEOFF        1                      CA  CFJLB43057                                                          (CAN) AIRCRAFT WAS ON TAKEOFF ROLL WHEN THE PILOTS HEARD A LOUD BANG FROM ENGINE NR 2 & EXPERIENCED A YAW TO THE RIGHT AS THEY APPROACHED 110 KNOTS.  THE PILOTS THROTTLED BACK, ABORTED THE TAKEOFF, TAXIED BACK TO THE RAMP AND SHUTDOWN THE ENGINES.   PASSENGERS OBSERVED FLAMES EXPEL FROM NR 2 ENGINE INLET AND EXHAUST WHEN THE BANG OCCURRED.  CONDUCTED AN INITIAL VISUAL INSPECTION AND FOUND PART OF A RUBBER SEAL MISSING AND DETACHED FROM THE C2 INLET GUIDE VANE.  THERE IS NO DAMAGE TO THE C1, C2 OR T4.  REQUESTED AN EXTERNAL A BORESCOPE INSPECTION TO DETERMINE IF THERE IS DAMAGE TO THE INTERNAL PART OF ENGINE.   NO EVIDENCE OF FOD INGESTION.                                                                         2L72 4F4  F  A16WE   E2EA                 
             20090203     EA  2009       2          3          CA081217002      120081216G3230                LANDING GEAR                            CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C5     30050NE                              LEFT            INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) LANDED WITHOUT LT MLG NOT FULLY EXTENDED.  THE FLT CREW ATTEMPTED TO EXTEND GEAR, BUT NEVER GOT A LT MLG GREEN DOWN AND LOCKED INDICATION.  THEY CYCLED THE GEAR 3 TIMES, BUT STILL WERE UNABLE TO GET GOOD INDICATION.  THEY PERFORMED A MANUAL EXTENSION AND AGAIN DID NOT GET THE GEAR TO EXTEND.  AC LANDED ON RT MLG ON TOUCH DOWN AND COMPLETED ITS LANDING W/THE LT WING HITTING THE RUNWAY.                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E00063EN             
             20090203     EA  2009       2          3          CA081217003      120081216G2120601R95655       DUCT                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              CABIN AIR       FAILED          W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE PILOT NOTICED THE AIRCRAFT CABIN ALTITUDE WAS CLIMBING SO HE INITIATED AN EMERGENCY DESCENT.  HE THEN HEARD A LOUD POP/BANG THAT SOUNDED LIKE IT CAME FROM THE AFT OF THE AIRCRAFT.  NOT TO LONG AFTER THAT ALL THE OXYGEN MASKS DEPLOYED IN THE CABIN.  THE AIRCRAFT ALSO HAD A MEL FOR THE RIGHT PACK PRIOR TO THE FLIGHT  THE CAPITAN DID NOT DECLARE AN EMERGENCY AND THE PLANE LANDED WITHOUT INCIDENT.  MX FOUND A SUPPLY DUCT COMING FROM THE LEFT PACK GOING BEHIND THE APU INTO THE AFT PRESSURE BULKHEAD BLOWN.  THEY ARE ORDERING PARTS AND WILL REPAIR ACCORDINGLY 17- O2 GENERATORS WERE ACTIVATED.                                                                                                        2L72 4F4  FRTA21EA   E15NE                
             20090203     EA  2009       2          3          CA081217004      120081213G3260                PROXIMITY SENSOR                        CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              MLG             OUT OF ADJUST   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       19856                                                          (CAN) ON TAKEOFF WHEN THE LANDING GEAR WAS SELECTED UP, THE EICAS DISPLAYED "GEAR DISAGREE" MSG FOLLOWED BY "NOSE GEAR DOOR" MSG.  THE QRH WAS FOLLOWED AND THE GEAR WAS LOWERED AND THE MESSAGE CLEARED.  THE AIRCRAFT RETURNED AND PERFORMED A LOW PASS SO THE TOWER COULD VERIFY ALL GEAR DOWN.  THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.   THE AIRCRAFT WAS THEN FERRIED WITH GEAR DOWN AND PINNED.  MAINTENANCE READJUSTED THE PROX SENSOR TARGET FOR PROX SENSOR PS14GA (NOSE GEAR EXTEND/CENTER PROX SENSOR) AND THE SYSTEM CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20090203     NE  2009       2          3          CA081217005      220081210G7261                SCREEN                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              RT ENG OIL      CONTAMINATED    W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) FLT CREW REPORTED R ENGINE OIL PRESS (W) MSG AT CRUISE.  WARNING PERSISTED AT POWER SETTINGS ABOVE IDLE.  COMPLIED WITH QRH AND DIVERTED TO PHL.  ENGINE REMAINED AT IDLE DURING THE 40 MIN FLIGHT TO PHL.  LOWEST OIL PRESSURE SHOWN WAS 24 PSI.  AIRCRAFT LANDED IN PHL WITHOUT FURTHER INCIDENT.  MAINTENANCE REMOVED RT LUBE/SCAVENGE PUMP AND FOUND SCREENS COKED UP CAUSING RESTRICTION.  CLEANED SCREENS IN ACCORDANCE WITH EO 8/016/479 AND REINSTALLED PUMP IN ACCORDANCE WITH AMM 79-21-01.  OPS CHECKS CARRIED OUT AND NO FURTHER DEFECTS NOTED.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
             20090203     CE  2009       2          3          CA081217006      120081215G324061702935        CONTROL CABLE                           CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              PARKING BREAK   FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       516  516                                                       (CAN) THE CRIMP THAT RETAINS THE CABLE SHEATH TO THE CABLE ATTACH POINT FAILED ALLOWING THE SHEATH TO MOVE CAUSING THE PARK BRAKE TO NOT RELEASE.  THIS CABLE IS POST SB 550-32-50.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
             20090203     CE  2009       2          3          CA081217007      120081206G2750MS250261        LIMIT SWITCH                            BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                              TE FLAPS        FAILED          W      GA  O2 MASK DEPLOYED        UNSCHED LANDING                                                         BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, JUST BEFORE 10000 FT, CREW NOTICED ODOR OF ELECTRICAL SMOKE IN COCKPIT.  AS ACFT LEVELED OFF AT 10000 FT, CABIN CREW INFORMED FLT CREW OF AN ODOR OF SMOKE CABIN.  DONNED O2 MASKS, NOTIFIED ATC & INFORMED THEM OF SMOKE IN COCKPIT & RECEIVED A CLEARANCE TO PROCEED TO THE NEAREST AIRPORT.  WHILE DOING THE BEFORE LANDING CHECKLIST THE FLAPS WOULDN`T EXTEND,  A FLAPLESS LANDING COMPLETED WITHOUT FURTHER INCIDENT.  POST FLT INSP FOUND FLAP CIRCUIT BREAKER POPPED & FLAPS RETRACTED HARD AGAINST THEIR STOPS.  IT IS SUSPECTED THE UP LIMIT SWITCH FAILED ALLOWING SYSTEM TO THINK THAT THE FLAPS WERE NOT ALL THE WAY UP.   MOTOR OVERHEATED BEFORE TRIPPING THE CIRCUIT BREAKER, CAUSING THE ELECTRICAL SMOKE O1L72 3T4  T  A14CE   E4EA                 
             20090203     SW  2009       2          3          CA081217008      120081201G5302206020113215A   TAIL BOOM                               BELL  407   407         1182206SW                                                                               DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORE ASSEMBLY 206-020-113-215A BONDED IN VERTICAL FINS ASSEMBLIES 206-020-113-233 FOUND WITH VOIDS IN THE ADHESIVE AT THE LOWER PORTION OF THE FIN NEAR THE TAILROTOR SKID ATTACHMENT POINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U    O H2SW                         
             20090203     NM  2009       2          3          CA081217011      120081215G5610NP15790113      WINDSHIELD                              DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       16661                                                          (CAN) DURING CLIMB LT WINDSHIELD CRACKED.  AIRCRAFT RETURNED TO DESTINATION AIRPORT.  UNEVENTFUL LANDING.  MAINTENANCE REPLACED THE DAMAGED WINDSHIELD AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090203     EU  2009       2          3          CA081217012      120081217G32134321012188      BEARING                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  MLG STRUT       WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6340                                                           (CAN) RIGHT MAIN LANDING GEAR SHOCK ABSORBER STRUT LOWER BEARING WORN AND LOOSE INTERNALLY.  REPLACED WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
             20090203     EU  2009       2          3          CA081217013      120081208G7930                OIL SYSTEM                              AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              ENGINE          LOW PRESSURE    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) SHORTLY AFTER TAKEOFF, THE PILOT NOTICED A LOW OIL PRESSURE INDICATION.  THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED TO ORIGIN FOR AN UNEVENTFUL SINGLE ENGINE LANDING.  GROUND INSPECTION REVEALED A POSSIBLE FRACTURED TOWERSHAFT.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRT        E20NE                
             20090203     NE  2009       2          3          CA081217014      220081208G7200                ENGINE                                  FOKKERF27   F27MK500    4990629EU  PWA   PWA120PW125B           NE                                              MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING T/O CLIMB, THE ENGINE OUT LIGHT CAME ON AND THE CREW ELECTED TO SHUT THE ENGINE DOWN AND RETURN TO THE POINT OF DEPARTURE FOR AN UNEVENTFUL SINGLE LANDING.  GROUND INSPECTION SHOWED OIL FILTER BYPASS INDICATORS ACTIVATED AND METAL WAS FOUND ON THE CHIP DETECTORS.  A RECOMMENDATION TO REMOVE THE ENGINE HAS BEEN MADE.                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  T  A817    E20NE                
             20090203     SW  2009       2          3          CA081217015      120081210G6320                HOUSING                                 BELL  412   412EP       1182205SW  PWA   PT6T  PT6T3       52045EA                              M/R GEARBOX     CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, OIL PRESSURE WAS LOST ON THE COMBINING GEARBOX AND THE PILOT PERFORMED AN UNSCHEDULED LANDING OFF BASE.  THE HELO HAD TO BE TRANSPORTED BACK ON A TRUCK.  INSPECTION OF THE ENGINE REVEALED A CRACK IN THE GEARBOX HOUSING FROM WHICH THE OIL ESCAPED.  THE GEARBOX WILL BE REMOVED AND FORWARDED TO P&WC FOR INVESTIGATION.  UPDATES WILL BE PROVIDED IN DUE COURSE.                                                                                                                                                                                                                                                                                                                                                      1G72 4U4  U  H4SW    E22EA                
             20090203     SW  2009       2          3          CA081217016      120081212G2435M2040AC2        BEARING         BFGOODRICH              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              STARTER GEN     FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA            822                                                       (CAN) STARTER GENERATOR FAILED IN FLIGHT CAUSING THE RT GEN FAIL LIGHT TO ILLUMINATE.  UPON LANDING AND INSPECTION BY MAINTENANCE THE GENERATOR WAS FOUND TO HAVE DAMAGE RELATED TO COMPONENT FAILURE.  THE GENERATOR WAS REPLACED AND SENT TO PERIMETER`S OVERHAUL FACILITY.  THE TEARDOWN REPORT INDICATES FAILURE OF BOTH GENERATOR BEARINGS (PN M2040AC-2).  GENERATOR WAS LAST INSPECTED AT 487.6 HOURS IN ACCORDANCE WITH THE MANUFACTURERS CMM SINCE LAST OVERHAUL AND PASSED THE INSPECTION AND WAS RETURNED TO SERVICE.  AT 822.4 THE BEARINGS FAILED CAUSING THE GENERATOR SYSTEM FAILURE.  BOTH THE STATOR AND ARMATURE ASSY WERE DAMAGED BEYOND REPAIR.  NO DEFINITIVE CAUSE CAN BE DETERMINED.                                     2L72 4T4  TRTA8SW    E4WE                 
             20090203     GL  2009       2          3          CA081218001      120081208G5512                SKIN                                    DIAMONDA20  DA20A1      2990000GL  ROTAX 912   ROTAX912F3       EU                              HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5400                                                           (CAN) DURING ROUTINE MAINTENANCE, A 1 1/2 INCH LONG CRACK WAS NOTICED IN THE LEADING EDGE OF THE HORIZONTAL STABILIZER.  TAP TESTING INDICATED POSSIBLE DELAMINATION, SO THE STABILIZER WAS REMOVED FROM AIRCRAFT AND SENT TO COMPOSITE REPAIR SHOP (XU AVIATION) FOR FURTHER EVALUATION AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTTA4CH   E00051EN             
             20090203         2009       2          3          CA081218003      420081216G31608221917202      DISPLAY                                 CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              COCKPIT         MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE FL 380, 3.5 HOURS IN FLIGHT, THE MFD NR 2 LOWER WINDOW STARTED TO CYCLE BETWEEN THE DIFFERENT FORMATS (PPOS, PLAN, TCAS ECT) AT FEW SECONDS INTERVAL WITH UNDEFINED SYMBOLS/TEXT LINE (HIEROGLYPH).  AT THAT TIME THE PFDS 1 AND 2, MFD 1 SHOWED NORMAL INFORMATION.  THEN, THE COMS AND NAVS ACTUAL AND PRE SELECTED FREQUENCIES, WOULD HAVE DIGITS CHANGING ON THEIR OWN, SOMETIMES THE FREQUENCIES WOULD BE GREEN OR AMBER ON BOTH CDUS TUNING PAGE AND MFDS RADIO MENUS.  THE NAVS TUNING MODE WOULD BE CHANGING BY THEMSELVES BETWEEN AUTO/MAN.  SUBSEQUENTLY, THE COMMUNICATION WITH BOTH VHF COMS WAS NO LONGER POSSIBLE WITH AIR TRAFFIC CONTROL.  ONBOARD SATELLITE AIRPHONE WAS USE.  THE FLIGHT WAS REDIRECTED TO A C2L72 4F4  FRTA21EA   E15NE                
             20090203     SO  2009       2          3          CA081218004      120081201G3245                TUBE                                    PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              TIRE            FAILED          W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      CA       391                                                            (CAN) WHEN THE AIRCRAFT LANDED IT WAS DISCOVERED THAT THE NOSEWHEEL WAS FLAT.  INSPECTION DID NOT REVEAL A DIRECT CAUSE FOR THE TUBE TO FAIL.  THERE WERE SEVERAL SEVERE WEATHER CHECK CRACKS IN THE TUBE WHEN THE TIRE WAS DISASSEMBLED.  THE COMPANY IS INSTALLING A PROCEDURE FOR INSPECTING NEW TUBES BEFORE INSTALL AS WELL AS PROPER WHEEL BUILD UP PROCEDURES.  THE COMPANY IS ALSO IMPLEMENTING A 12 MONTH INSPECTION AND REPLACEMENT SCHEDULE FOR THE NOSEWHEELS ON THE NAVAJO AIRCRAFT.                                                                                                                                                                                                                                               1L72 3O3  O  A20SO   E14EA                
             20090203     EA  2009       2          3          CA081218005      120081217G2752                ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) FLAP FAIL ON APPROACH.  WHEN FLAPS SELECTED THE FLAPS DID NOT MOVE FROM ZERO DEGREES.  FLAPLESS APPROACH AND LANDING CARRIED OUT WITHOUT FURTHER INCIDENT.  ACFT FERRIED FOR FLAP REPAIR.  ALL FLAP ACTUATORS REPLACED, RT NR 1 FLAP DRIVE ASSY REPLACED DUE TO DAMAGED CORE, RT NR 2 AND NR 3 DRIVE CABLES FOUND WITH MOISTURE CONTAMINATION-CORE AND CASINGS CLEANED AND RELUBED.  LT NR 1 FLAP DRIVE FOUND WITH MOISTURE CONTAMINATION-CLEANED AND RELUBED.  LT NR 5 FLAP DRIVE DEFORMED BEYOND LIMITS.  REPLACED FLAP POWER DRIVE UNIT.  ACFT TEST FLOWN SUCCESSFULLY AND RETURNED TO SERVICE.                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
             20090203     SW  2009       2          3          CA081218006      120081217G79318974072         BYPASS VALVE                            SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              OIL FILTER      LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) THE CREW REPORTED THAT ONE TIRE HAD BLOWN DUE TO FROZEN BRAKES.  AN AME WAS SENT TO CHANGE THE WHEEL AND FLY BACK TO THE BASE WITH THE AIRCRAFT.  UPON RETURN TO BASE, A LARGE OIL LEAK WAS NOTED COMING FROM THE NR 2 ENGINE.  IT WAS EVENTUALLY DETERMINED BY MAINTENANCE STAFF TO BE THE OIL FILTER BYPASS PIN.  THE PIN POPS OUT IF THE OIL SYSTEM BECOMES CONTAMINATED.  THE PIN WAS NOT EXTENDED, HOWEVER, IT WAS LEAKING OIL.  THE OIL LEAK WAS INITIALLY THOUGHT TO BE AN STARTER GENERATOR OIL SEAL, DUE TO THE VOLUME OF OIL LEAKED THROUGHOUT THE ENGINE COMPARTMENT.  A SECOND GROUND RUN DISCOVERED THE LEAK FROM THE BYPASS PIN AREA.  PRELIMINARY REPORT, THE DEFECT IS BEING REPAIRED NOW.  UNKNOWN TSO ON THE PART, HOWEV2L72 4T4  TRTA8SW    E4WE                 
             20090203         2009       2          3          CA081222007      420081219G2350164ZS01Y        AUDIO PANEL                             AMD   FALC10FALCON10    2730101EU  GARRTTTFE731TFE7312     01518WP                              COCKPIT         MALFUNCTIONED   W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       6069 6069                                                      (CAN) DURING THE BASIC INSPECTION WITH AIRCRAFT POWER ON, FUMES AND LIGHT SMOKE WHERE NOTICED IN THE COCKPIT.  AFTER INSPECTION THE AUDIO WARNING PANEL BOX WAS FOUND TO BE THE CAUSE.  THE AUDIO WARNING PANEL BOX WAS REPLACED WITH A REPAIRED SERVICEABLE UNIT FROM DASSAULT AND TESTED SERVICEABLE P/N 164ZS01Y S/N 202.  REMOVED AND S/N 175, INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A33EU   E6WE                 
             20090203     SW  2009       2          3          CA081222008      120081208G6730222382001101    SERVO                                   BELL  222   222U        1182140SW  LYC   LTS101LTS101750C1 41560NE                                              UNKNOWN         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) SOLID RESISTANCE FELT WITH AFT CYCLIC MOVEMENT DURING OPERATIONS WITH FORCE TRIM ON & UTILIZING CYCLIC TRIM RELEASE SWITCH.  ON FIRST OCCURRENCE RESISTANCE RELEASED WITH A FIRM BUMP & FAULTY LT CYCLIC TRIM RELEASE SWITCH SUSPECTED HOWEVER WITH SECOND OCCURRENCE SWITCHING FORCE TRIM OFF HAD NO EFFECT & RESISTANCE ONCE AGAIN RELEASED WITH A FIRM BUMP AFTER SEVERAL SECONDS.  ALL THE MAIN ROTOR CONTROLS WERE INSPECTED FOR FREEDOM OF MOVEMENT & TRAVEL, NO DEFECTS NOTED.  A GPU FOR HYD SYSTEM ATTACHED & SYSTEM 1 & 2 CHECKED.  NO DEFECTS.  WHEN CYCLIC MOVED FOR & AFT WHEN POWERED BY ONLY 1 HYD SYSTEM NOTICED THAT CYCLIC STICK SEEMED TO BE MOTORED (DRIVEN) FOR & AFT BY SERVO ACTUATOR.  SERVO HAD 23.8 HOURS SINCE 1G72 3U3  U  H9SW    E5NE                 
             20090203     NM  2009       2          3          CA081222009      120081218G242131708001A       GENERATOR                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 1 AC         MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 HJ ELECT. POWER LOSS-50 PC   WARNING INDICATION                                  CLCLIMB          1                      CA       260711768                                                      (CAN) SHORTLY AFTER TAKE OFF, THE FLIGHT CREW RECEIVED "NR 1 AC GEN" AND "NR 2 AC GEN" CAUTION LIGHTS.  SYSTEMS WERE RESET AND NR 2 AC GENERATOR RETURNED ON LINE.  DECISION WAS MADE TO RETURN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  THE NR 1 AC GENERATOR WAS REPLACED AND THE PHASE A AND C WIRES LOCATED UNDER THE RT FLAP BETWEEN THE NACELLE AND THE FUSELAGE WERE REPAIRED.  BOTH WIRES WERE SHORTED DUE TO CHAFING.                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090203     CE  2009       2          3          CA081222010      120081221G561010138402523     WINDSHIELD                              BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       4500                                                           (CAN) WINDSHIELD CRACKED AFTER TAKEOFF, CRACKS EMANATED VERTICALLY FROM THE BOTTOM INBOARD EDGE.  UNIT TTSN 4500 HOURS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  T  A24CE   E4EA                 
             20090203     NE  2009       2          3          CA081223001      220081219G7230311194301       BEARING                                                                    PWA   118   PW118            NE                              NR 3            FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) NR 3 BEARING FAILURE FOUND AT DISASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       4  T          E20NE                
             20090203     NE  2009       2          3          CA081223002      220081217G7200MS945226        BEARING                                                                    PWA   PW120 PW123            NE                              ENGINE          SEIZED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE BEARING SEIZED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           4  T          E20NE                
             20090203         2009       2          3          CA081223004      420081221G34604082499902      COMPUTER                                BOEING737   737800*            NM                                                               FLIGHT CONTROL  MALFUNCTIONED   W      L   ABORTED APPROACH                                                                                F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) CREW REPORT STABILIZER LIGHT CAME ON.  ATC INFORMED AND CREW BROKE OFF APPROACH AND DETERMINED THAT THERE WAS NO STABILIZER TRIM.  AIRCRAFT RETURNED TO AIRPORT AND CONDUCTED A SAFE LANDING.  MAINTENANCE TROUBLESHOT REPORTED SNAG AND FOUND FAULT APPEARED TO LIE WITH THE FLIGHT CONTROL COMPUTER.  UNIT REPLACED AND SYSTEM CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
             20090203     EA  2009       2          3          CA081223005      120081208G5531215221182       RIB                                     CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              VERTICAL STAB   CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CRACK 35 MM LONG ON RIB OF VERTICAL STAB AT WL 396.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA14EA   E20NE                
             20090203     GL  2009       2          3          CA081223007      120081123G7921AE7010101H0114  HOSE                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              OIL COOLER      LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       577                                                            (CAN) AIRCRAFT WAS ON A REGULAR TRAINING FLIGHT WHEN THE CREW NOTICED THAT THE OIL PRESSURE INDICATION HAD FALLEN OUT OF THE GREEN ARC AND REMAINED LOW UNTIL THE AIRCRAFT WAS ABLE TO RETURN TO BASE.  ONCE THE AIRCRAFT HAD RETURNED AND WAS INSPECTED MY MAINTENANCE, IT WAS DETERMINED THAT THERE WAS A SIGNIFICANT OIL LEAK.  FURTHER INVESTIGATION REVEALED THAT THE OIL COOLER HOSE HAD A PUNCTURE AND THAT WAS THE LIKELY CAUSE OF THE FAILURE.  THE ENGINE WAS REMOVED AND SENT OUT FOR BULK INSPECTION.  A REPLACEMENT ENGINE WAS INSTALLED ALONG WITH NEW OIL COOLER HOSES.  THE FAULTY HOSE WAS INSPECTED, TESTED AND RETURNED TO THE MANUFACTURER FOR ANALYSIS.                                                                    1L71 3O3  ONTTA4CH   E7SO                 
             20090203     NE  2009       2          3          CA081223008      220081223G741422021081806     BEARING                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         LACK OF LUBE    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       474                                                            (CAN) MAG RECEIVED FOR 500 HR INSPECTION, ROTATING MAGNET SHAFT SPUN BEFORE DISASSEMBLY TO INSPECT BEARING CONDITION & PRELOAD.  NO END PLAY OR ROUGHNESS FELT, WHEN MAG WAS DISASSEMBLED, DISCOVERED THAT AT O/H IN SEPT 2007.  NO GREASE HAD BEEN PACKED INTO BEARINGS.  BEARINGS WERE LUBRICATED BY OIL THAT EACH BEARING IS PACKAGED WITH WHEN NEW.  ONLY OTHER SOURCE OF LUBRICATION WAS A SMALL AMOUNT OF OIL THAT HAD LEAKED INTO MAG PAST OIL SEAL.  LACK OF LUBRICATION COULD CAUSE MAGNETO & ENGINE FAILURE, EVEN THOUGH BEARINGS DID NOT APPEAR DAMAGED THEY WERE REPLACED,  MAG WAS RETURNED TO SERVICE.                                                                                                                            1G71 3O3  O  H11NM   1E4                  
             20090203     EA  2009       2          3          CA081229001      120081225G561004093H1031      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       1057510575                                                     (CAN) DURING CLIMB, THE RT WINDSHIELD CRACKED LIMITING THE FIRST OFFICER VIEW.  AN EMERGENCY WAS DECLARED, THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT.  AT THIS TIME, NO IMPACT WERE REPORTED BY THE FLIGHT CREW.  VISUAL INSPECTION OF THE WINDSHIELD INDICATES THAT THE EXTERNAL AND INTERNAL LAYERS ARE CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20090203     GL  2009       2          3          CA081229003      220081224G732323070101        GOVERNOR                                BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              ENGINE          FAILED          W      BA  EMER. DESCENT           UNSCHED LANDING                                                         XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA            1419                                                      (CAN) PILOT ENCOUNTERED HIGH SIDE GOVERNOR FAILURE.  TORQUE INCREASED FROM 85 TO 100 PERCENT DURING CLIMB WITH NO COLLECTIVE INPUT.  NR/N2 INCREASED TO 110 PERCENT AND THROTTLE WAS ROLLED TO IDLE WITH NO INITIAL EFFECT.  NR/N2 THEN DROPPED TO 90 PERCENT.  A DESCENT AND SHORT RUN-ON LANDING WAS MADE USING MANUAL THROTTLE MOVEMENTS.  NO DAMAGE OCCURRED.  REPLACEMENT OF GOVERNOR CURED PROBLEM AFTER TROUBLESHOOTING IN ACCORDANCE WITH ROLLS ROYCE 250 C30P MM.  REMOVED GOVERNOR WILL BE SENT TO REPAIR STATION FOR INSPECTION.                                                                                                                                                                                                     1G71 3U3  U  H2SW    E1GL                 
             20090203     EA  2009       2          3          CA081229004      120081226G5210601R317047      HANDLE                                  CNDAIRCL600 CL600*      1900302EA  GE    CF34  CF348C5     30050NE                              PAX DOOR        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1081110811                                                     (CAN) WHEN GROUND CREW ATTEMPTED TO OPEN AIRCRAFT FOR MORNING DEPARTURE, OUTER DOOR HANDLE SNAPPED OFF IN HIS HAND.  MAINTENANCE INSPECTED AND REPLACED MAIN CABIN DOOR HANDLE ASSEMBLY AND FUNCTION CHECKED AS PER MANUFACTURERS MAINTENANCE MANUAL.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E00063EN             
             20090203     NE  2009       2          3          CA081231001      220081229G7200                ENGINE                                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 1            OVERTORQUED     W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE CREW OBSERVED AN OVERTORQUE ON THE NR 1 ENGINE, THE POWER LEVER WAS REDUCED AND THE ENGINE STABILIZED AROUND 93 PERCENT OF TORQUE BEFORE RAISING AGAIN.  DECISION WAS MADE TO PERFORM AN INFLIGHT SHUTDOWN.   THE CREW DECLARED AN EMERGENCY, RETURNED TO THE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.  IT IS UNKNOWN AT THIS TIME WHAT HAS CAUSED THE ENGINE OVERTORQUE.  THE ENGINE IS BEING REPLACED AND WILL BE SHIPPED TO AN OVERHAUL FACILITY.                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090203     NE  2009       2          3          CA081231002      220081231G7414GE5298          DRIVE GEAR      BOSCH                                                      PWA   R985  R985AN14B   52008NE                              MAGNETO         WORN            W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA            778                                                       (CAN) ON INSPECTION MAGNETO WAS FOUND TO HAVE ERATIC TIMING ON DRIVE GEAR PART NUMBER GE5298, LOOSE ON SHAFT AND EXCESSIVE WEAR ON KY11-14 - KEY WOODRUFF FOR DRIVE GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              3  R          5E1                  
             20090203     CE  2009       2          3          CA081231003      120081221G561010138402524     WINDSHIELD                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) WINDSHIELD CRACKED AS AIRCRAFT CLIMBED OUT OF YYC.  AIRCRAFT RETURNED TO YYC.  MAINTENANCE REPLACED WINDSHIELD AND RETURNED AIRCRAFT TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA                 
             20090203     CE  2009       2          3          CA081231004      120081221G561010138402523     WINDSHIELD                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              COCKPIT         CRACKED         W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AFTER START PILOT NOTED THAT THE WINDSHEILD WAS CRACKED.  ENGINES WERE SHUT DOWN AND MAINTENANCE REPLACED THE WINDSHEILD AND RETURNED THE AIRCRAFT TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A24CE   E4EA                 
             20090203     EA  2009       2          3          CA090102002      120081224G2750                FLAP SYSTEM                             CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B      30069NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE FLAP FAILED TO EXTEND AND THE AIRCRAFT DIVERTED WHERE THEY LANDED WITH THE FLAPS UP.  UPON INSPECTION FOUND THE FLAPS WOULD NOT MOVE AND WERE IN ASYMMETRIC CONDITION.  BOTH THE LT AND RT BDU WERE REPLACED AND THE FLAP SYSTEM TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
             20090203     CE  2009       2          3          CA090102004      120081231G531097430000149     DOOR FRAME                              BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              BS 201          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6727                                                           (CAN) WHILE CARRYING OUT SPECIAL INSPECTION, INSPECT ESCAPE HATCHES AND ASSOCIATED CLOSURE AREA.  FOUND THE RT AFT EMERGENCY EXIT CROSS TIE CRACKED THROUGH AT FS 201.775, AFT RT ESCAPE HATCH FRAME.  THERE WERE TWO RIVETS SHEARED OFF IN THE SAME AREA AND THE .125 INCH THICK PIECE HAD BUCKLED.  NO ADDITIONAL DAMAGE WAS NOTED IN THE FUSELAGE.  THIS WAS THE FIRST 1000 LANDING REPETITIVE INSPECTION AFTER THE INITIAL 5000 LANDING INSPECTION.  PART WILL BE REPLACED WITH FACTORY NEW PART.                                                                                                                                                                                                                                           2L72 4T4  T  A24CE   E4EA                 
             20090203     CE  2009       2          3          CA090105001      120081208G3210                STRUCTURE                               CESSNA172   172M        2072418CE  LYC   O360  O360A4M     41514EA                              MLG             WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       15                                                             (CAN) WORN ATTACH HOLE, CAUSING FORE AND AFT MOVEMENT OF THE WHEEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E286                 
             20090203     CE  2009       2          3          CA090105002      120081224G561050420066103     WINDOW                                  BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A34      52043EA  HARTZLHCB4T HCB4TN3     GL  COCKPIT         FAILED          W      BG  EMER. DESCENT           O2 MASK DEPLOYED                                                        O  OTHER                                                                         CRCRUISE         1                      CA       15865                                                          (CAN) AT 16000 FT LEVEL CRUISE, WINDOW FAILURE OCCURRED, COMPLETE WINDOW FAILED LEAVING ONLY APPROX 2 INCHES OF WINDOW ATTACHED TO AIRFRAME  WINDOW SEAL STAYED ATTACHED TO AIRFRAME.  CRAZING, PITS AND SCRATCHES REMOVED FROM WINDOW FEB 10, 2000, WINDOW MEASURED AFTER  REPAIR.  .304-.321, COMPLETED BY AVGLASS USA.                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3T4  T  A14CE   E4EA    6  CP40EA    
             20090203     EA  2009       2          3          CA090105006      120081231G2750865D1007        DRIVE UNIT                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       1496314963                                                     (CAN) THIS AIRCRAFT WAS UNDER A FERRY PERMIT TO YYC FOR A BROKEN OUTER DOOR HANDLE.  THE FLAPS WHERE AT 8 DEGREES BEFORE DEPARTURE.  AFTER TAKEOFF THE FLAP FAIL MESSAGE WAS POSTED WITH FLAPS STILL AT 8 DEGREES.  THE PILOT RETURNED TO YZF DUE TO INSUFFICIENT FUEL TO REACH YYC WITH FLAPS AT 8 DEGREES.  THE AIRCRAFT IS GOING TO FERRY TO YYC WITH FLAPS SET AT 8 DEGREES.  FLAP POWER DRIVE UNIT REPLACED AND FLAP SYSTEM CHECKED SERVICEABLE.  A/C RETURNED TO SERVICE (RESOLVED ON W/O: 174456 TASKCARD: NR-00002) DEFECT NR 819812.                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
             20090203     NM  2009       2          3          CA090105007      120081220G6120699018002       PCU                                     BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NO 1 ENGINE     MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) POWERPLANT INDICATION ON ED NR 1 TRU AND AC GEN ZERO INDICATION WHILE TAXIING.  ACTION TAKEN AT MNL, RETRIEVE FAULT CODE 388 AND 1504 AND CLEARED POWERPLANT MESSAGE.  PEC REPLACED.  PERFORMED FAULT CODE ISOLATION AND OPERATIONAL CHECK OF RADIO ALTIMETER AND FAULT ISOLATION ON POWERPLANT ELECTRONIC UNIT (PEC).  PERFORMED ENGINE RUN-UP FOUND SATISFACTORY IN ACCORDANCE WITH Q400 TASK 77-31-00-810-805, 61-20-07-810-815, 32-61-00-710-801.                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN             
             20090203     CE  2009       2          3          CA090105008      120081224G5540                ATTACH BRACKET                          CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160CTM    GL  RUDDER WEIGHT   BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10742                                                          (CAN) RUDDER BALANCE WEIGHT EXCEEDED MAY ALLOWABLE WEIGHT OF 4.38 LBS PLUS .25 LBS BY 1.5 LBS WEIGHT WAS ADDED TO BALANCE WEIGHT FOLLOWING PAINTING OF RUDDER.  EXCESSIVE WEIGHT CAUSED ATTACH POINTS TO FAIL ALLOWING THE BALANCE WEIGHT TO BE ABLE TO SHIFT IN SUCH A MANNER THAT COULD CAUSE FLIGHT CONTROL BLOCKAGE.                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
             20090203     EA  2009       2          3          CA090105009      120081229G2752852D10019       ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              TE FLAPS        MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA                                                                      (CAN) FIRST FLIGHT OF THE DAY.  PILOTS WERE TAXIING AND SELECTED FLAPS TO 20 DEGREES AND THE FLAPS STAYED AT 0.  OAT -33 DEGREES C.  ACFT FERRIED FOR REPAIR.  ALL FLAP ACTUATORS REPLACED WITH POST SB ACTUATORS, FLAP DRIVE LUBE TASK COMPLETED, RIGGING AND FUNCTION CHECKS COMPLETED, AND A/C SUCCESSFULLY TEST FLOWN AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
             20090203     EA  2009       2          3          CA090105012      220081210G7200                ENGINE                                  BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                                              COKED           W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE CREW OBSERVED A RAPID RISE IN ENGINE TEMPERATURE AND TORQUE WITH FLAMES COMING OUT THE RIGHT ENGINE EXHAUST STACKS.  THE ENGINE THEN FLAMED OUT, THE FLIGHT WAS DIVERTED WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED.  DISASSEMBLY OF THE ENGINE BY THE OPERATOR REVEALED A LARGE PIECE OF CARBON COMPLETELY BLOCKING ONE OF THE CT GUIDE VANE, CT BLADES HEAVILY ERODED AND HEAVY CARBON DEPOSITS ON THE COMBUSTION LINER.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                       1L72 3T4  T  A14CE   E4EA                 
             20090204         2009       2          4          CA090105014      120081217G6123                AUTOFEATHER SYS                                                            PWA   PW120 PW124B           NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE ENGINE TORQUE DROPPED TO 22 PERCENT AND THEN ZERO.  THE ENGINE WAS SECURED AND THE A/C RETURNED TO THE POINT OF DEPARTURE, WHERE A SINGLE ENGINE LANDING WAS PERFORMED.  POST FLIGHT TROUBLESHOOTING LED TO THE REPLACEMENT OF THE AUTO FEATHER UNIT BEFORE THE ACFT WAS RETURNED TO SERVICE.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                 4  T          E2ONE                
             20090204     WP  2009       2          4          CA090106002      120081223G3260                DOWNLOCK SWITCH                         CVAC  340   340CVAC     242270AWP  ALLSN 501D  501D13D     03004GL                              MLG             OUT OF ADJUST   W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, CREW EXPERIENCED A LT GEAR UNSAFE LIGHT.  AFTER DETERMINING THE GEAR TO BE DOWN, ACFT LANDED UNEVENTFULLY.  MAINTENANCE ADJUSTED THE DOWN LOCK SWITCH AND ACFT WAS RETURNED TO SERVICE                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4R4  T  6A6     E282                 
             20090206     SO  2009       2          6          CA090107004      120081223G57124042306         RIB                                     PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA                              LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING MX, RIB P/N 40423-06, WHICH RUNS THROUGH THE LT WW, WAS FOUND CRACKED THROUGH AT THE NARROWEST PART OF THE RIB AT THE TOP CENTER OF THE WW. THE WING SKIN IMMEDIATELY ABOVE AND ATTACHED TO THE RIB ALSO HAD A SMALL CRACK WHICH COINCIDED WITH THE RIB CRACK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA                
             20090206     EA  2009       2          6          CA090107006      120081229G5610                WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       13762                                                          (CAN) CAPTAINS SIDE WINDOW SHATTERED IN FLIGHT.  FOLLOWED QRH, DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.   R&R CAPTAINS SIDE WINDSHIELD IAW AMM 56-11-01 AND CARRIED OUT LEAK CHECKS.  ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
             20090206         2009       2          6          CA090107008      420081226G34178220372445      ADC                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              NR 1            MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       4396                                                           (CAN) JUST AFTER TAKEOFF, THE CREW RECEIVED RED FLAGS FOR THE CAPTAINS AIRSPEED, ALTIMETER AND VSI MOMENTARILY.  INDICATIONS RETURNED TO NORMAL SHORTLY AFTER. THE FLIGHT RETURNED TO THE DEPARTURE AIRFIELD AND LANDED WITHOUT FURTHER INCIDENT.  MX R&R THE NR 1 ADC AND OPS CHECKED SERVICEABLE.  ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
             20090206     EA  2009       2          6          CA090107009      120081222G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) FLT CREW REPORTED FLAP FAIL MSG WHILE ON APPROACH WHEN FLAPS SELECTED OUT OF 0 DEG.  QRH FOLLOWED AND LANDED WITH FLAPS AT 0 DEG WITH NORMAL BRAKING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
             20090206     EA  2009       2          6          CA090107011      120081219G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN)  EXPERIENCED FLAP FAILURE.   REPLACED BPSU.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
             20090203     EA  2009       2          3          CA090107014      120081216G30205399001         ANTI-ICE VALVE                          CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA            12356                                                     (CAN) FLT CREW REPORTED RIGHT COWL ANTI-ICE MESSAGE IN FLIGHT WITH ANTI-ICE SELECTED ON.  COMPLETED QRH AND MESSAGE PERSISTED.  DIVERTED AND LANDED WITHOUT FURTHER INCIDENT.  REMOVED AND REPLACED RIGHT COWL ANTI-ICE VALVE AND OPS CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.  ANTI-ICE VALVE 5399-00-1 0186A FAILED RIGHT COWL 13148/12356 (VALVE TIMES).                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
             20090203     EA  2009       2          3          CA090107015      120081215G4930600970249       LINE                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                              APU FUEL SYSTEM CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       19855                                                          (CAN) WHILE SERVICING APU MAINTENANCE NOTICED A FUEL SMELL.  OPENED PANEL AND RAN APU.  FOUND APU INLET BELLOWS RETAINING CLIP RIGHT SIDE SLID AFT AND CHAFED HOLE IN METERED FUEL LINE TO NOZZLES.  FUEL WAS DRIPPING ON IGNITER BOX.  REMOVED AND REPLACED FUEL LINE AND REPOSITIONED RETAINING CLIP AND PLACED SPIRAL WRAP ON FUEL LINE BEHIND CLIP.  AIRCRAFT RETURNED TO SERVICE.  FUEL LINE 600-97024-9 N/A CHAFED APU COMPARTMENT 20830/19855.                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
             20090203     EA  2009       2          3          CA090107016      120081022G492038004883        APU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1     30070NE                                              SMOKE           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      LDLANDING        1                      CA            20144                                                     (CAN) FLT CREW REPORTED SMOKE IN FLIGHT DECK AFTER LANDING.  SMOKE DISSIPATED AFTER PACKS SELECTED OFF, APU 3800488-3 P-601 19506/20144 (APU TIMES).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
             20090203     EU  2009       2          3          CA090108002      120081229G3260A254210012      UPLOCK                                  AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2*         GL                              NLG             FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 DEDESCENT        1                      CA       59564                                                          (CAN) IN DESCENT TO LGW, FLIGHT CREW REPORTED, L/G NOSE WHEEL UNSAFE INDICATION.  PERFORMED L/G GRAVITY EXTENT ION.  NLG UPLOCK ASSY WAS REPLACED AND OPERATIONAL CHECK WAS CARRIED OUT SERVICEABLE.  AS SAFETY PRECAUTION, BOTH NOSE LANDING GEAR DOOR SEQUENCE VALVE WERE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA35EU   E23EA                
             20090203     SW  2009       2          3          CA090108003      120081226G5310                DOOR FRAME                              BBAVIA7     7AC         2110102SW                                                               FUSELAGE        CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       2508                                                           (CAN) DOOR TUBE RUSTED THROUGH LOWER END, REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O      A759                         
             20090203     NM  2009       2          3          CA090109002      120081214G79308D1437          PRESSURE SWITCH                         DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE                  MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) NR 1 ENG OIL PRESS WARNING LIGHT ILLUMINATION IN FLIGHT, ENGINE SHUTDOWN IN ACCORDANCE WITH QRH/AFM, AIRCRAFT RETURNED TO DEPARTURE AIRPORT AND LANDED SAFELY.  MAINTENANCE DETERMINED NR 1 OIL PRESSURE SWITCH FAILED.  SWITCH REMOVED AND REPLACED.  ENGINE RUNS CARRIED OUT, OPERATION SATISFACTORY.  AIRCRAFT RETURNED TO SERVICE.  SWITCH MANUFACTURER (CUSTOM CONTROL SENSORS) NOT IN THE DROP DOWN LIST.                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090204     CE  2009       2          4          CA090112004      120081214G2823C2915030101     SELECTOR                                CESSNA206   U206D       2073342CE  CONT  O520  IO520F      17032SO  MCAULY2A34C D2A34C58    GL  FUEL SYSTEM     LEAKING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1085110851                                                     (CAN) FUEL SELECTOR CLOSED DUE TO FLEX HOSES IN ENGINE COMPARTMENT BEING REPLACED.  AFTER HOSES INSTALLATION FUEL SELECTOR OPEN TO CHECK FOR LEAKS, FUEL LEAK FOUND ON BELLY.  FUEL SELECTOR WAS LEAKING ON THE TOP, SOURCE OF LEAK SHAFT ON THE TOP.  SELECTOR WAS ORIGINAL INSTALLATION (1969).  UNIT REPLACED WITH NEW UNIT FROM CESSNA.  NO FURTHER LEAKS. (TC NR 20090112004)                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E5CE    5  CP3EA     
             20090205     SO  2009       2          5          CA090112008      220081031G7414                GASKET          BENDIX                  PIPER PA28  PA28R201T   7102813SO  CONT  O360  TSIO360FB   17025SO                              MAGNETO         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            23                                                        (CAN) ENGINE INSPECTED FOR OIL LEAK AT REAR ACCESSORY SECTION, FOUND OIL COMING FROM RIGHT MAGNETO ATTACH GASKET.  MAGNETO REMOVED, GASKET AND ENGINE MATING SURFACE INSPECTED OK.  MOUNTING FLANGE ON MAGNETO INSPECTED AND FOUND CRACKED IN AREA WHERE BOTH HOLD DOWN CLAMPS MAKE CONTACT, FLANGE WAS ON THE VERGE OF BREAKING OFF COMPLETELY WHICH WOULD RESULT IN MAGNETO FAILURE AND POSSIBLE COMPLETE ENGINE OIL LOSS.  LEFT MAGNETO REMOVED FOR INSPECTION, FOUND SATISFACTORY.  AIRCRAFT OWNER REPORTED THAT LEFT MAGNETO WAS REPLACED FOR SAME REASON ABOUT 50 HOURS EARLIER.  SUSPECT CAUSE OF CRACKING FLANGES IS FROM OVERTORQUING HOLD DOWN CLAMP NUTS.  (TC NR 20090112008)                                                       1L71 3O3  O  2A13    E9CE                 
             20090206     CE  2009       2          6          CA090116004      120081229G7500                MOTOR                                   CESSNA500   560CESSNA   2076750CE  PWC   545   PW545B           NE                              HBV TORQUE      FAILED          W      E   ENGINE SHUTDOWN                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA                                          654577883                   (CAN) THE CREW REPORTED VIBRATION ON RT ENGINE AND THE EEC REVERTED TO MANUAL MODE. THEY OBSERVED A SUDDEN RISE IN ENGINE TEMPERATURE AND ELECTED TO SHUT IT DOWN BEFORE MAKING A SINGLE ENGINE LANDING. REPLACED THE BLEED-OFF VALVE AND TORQUE MOTOR BEFORE THE ACFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA22CE   E00059EN             
             20090206     NE  2009       2          6          CA090116006      220081224G7250                TURBINE BLADES                          DHAV  DHC8  DHC8301     1386003NM  PWA   120   PW123D      52152NE                              ENGINE          FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, AT FL68, THE ENGINE LOST POWER.  IT WAS SHUT DOWN AND SECURED AND THE ACFT RETURNED TO THE POINT OF DEPARTURE WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED.  GROUND INSPECTION FOUND THAT THE PROPELLER WOULD NOT ROTATE AND POWER TURBINE BLADES WERE FRACTURED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE                
             20090206     NE  2009       2          6          CA090116007      220081222G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              POWER LOSS      W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE ENGINE TORQUE AND TEMPERATURE INCREASED UNCOMMANDED.  CREW REDUCED POWER BUT THE ENGINE DID NOT RESPOND AND WAS SHUT DOWN AND SECURED.  A SINGLE ENGINE LANDING WAS ACCOMPLISHED AT THE POINT OF ORIGIN.  THE ENGINE WILL BE REMOVED AND INVESTIGATED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRT        E20NE                
             20090206     NE  2009       2          6          CA090116008      220081229G7200                ENGINE                                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE                  MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE CREW NOTED A RAPID INCREASE IN FUEL FLOW, FOLLOWED BY A RAPID RISE IN TEMPERATURE AND TORQUE ON THE LT ENGINE. THE ENGINE DID NOT RESPOND TO POWER LEVER MOVEMENTS AND AN UNCOMMANDED IFSD OCCURRED.  A SINGLE ENGINE LANDING WAS MADE AT THE POINT OF DEPARTURE. GROUND INSPECTION FOUND METAL PARTICLES IN THE OIL TANK.  THE ENGINE WILL BE REMOVED.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20090206     GL  2009       2          6          CA090119011      120081228G2421A3579101        GENERATOR                               BOMBDRBD100 BD1001A10   1390044GL  HNYWL AS907 AS90711A    33908WP                                              FAULTED         W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       LDLANDING        1                      CA                                                                      (CAN) ACFT ARRIVED WITH RT GEN FAULT. RT COWL OPEN, FOUND GEN DAMAGED AND DISLODGED OUT FROM IT`S EXHAUST HOUSING. SHAFT DIDN`T SHEARED. THE BACK MATING PLATE AT THE GEARBOX ASSY SLIGHTLY CHAFED DUE TO IN CONTACT WITH GEN SHAFT. LMM AS907-1-1A CHAP 72-61-01, FIG 801,PG 802, ITEM 170)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00005NYE00010LA             
20080325000602008032500060NM  2008       3          25         CO1Y200800001    120080307G5340ARB71701        SUPPORT FITTING                         DOUG  MD11  MD11F       3023600NM                                                               MLG DOOR        CORRODED        B  CO1YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33725BC                       48503                                   AT LT MLG AND DOORS, FOUND BOLTS LOWER AND UPPER WITH PLI LOOSE ON LT FRAME SUPPORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L73 4F    RTA22WE                        
20080414000152008041400015NM  2008       4          14         CO1Y200800002    120080327G5510                STRUCTURE                               DOUG  MD11  MD11F       3023600NM                                                               ZONE 400        CORRODED        B  CO1YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33725BC                       48503                                   AT HORIZONTAL STABILIZER CTR SECTION, FOUND CORROSION INSIDE BARREL NUT HOLE NR 36 LT HORIZ STAB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F    RTA22WE                        
20080428003182008042800318NM  2008       4          28         CO1Y200800003    120080114G5755ARC44231        HINGE BRACKET                           DOUG  MD11  MD11        3023602NM                                                               LT SPOILER      WORN            B  CO1YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33725BC                       48503                                   LT SPOILER NR1 FOUND WITH PLAY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F    RTA22WE                        
20080225000082008022500008NE  2008       2          25         CRSCW1R075K      120080221G64107610105017045   SPAR            SKRSKY                  SKRSKYS76   S76B        8143007NE  PWA   PT6   PT6*        52043EA                              T/R BLADE       CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA11780P 2905       A11602002X  760359                                  DURING A ROUTINE INSP, A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE. BLADE ASSY (P/N 76101-05501-042, S/N A245-00153) WAS REMOVED FOR PRECAUTIONARY MEASURES AND SENT FOR INSP/EVALUATION. UPON DISASSEMBLY AND INSP, SPAR WAS FOUND TO HAVE CRACKS COMING FROM ELIPITICAL PLUG AREA. SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURNED TO SERVICABLE CONDITION. SCRAPED SPAR TOTAL TIME WAS 2905.8 HOURS. THIS IS THE SECOND SPAR WE HAD CRACKED.                                                                                                                                                                                                                                                             1G72 4U3  T  H1NE    E2NE                 
20080204001042008020400104CE  2008       2          4          CWQR200801       120080129G5330651201026       SKIN                                    CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              FUSELAGE        CRACKED         B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05839QS                       5600690                                 DURING A PHASE 1-4 INSPECTION THE TECHNICIAN NOTICED A SMALL CRACK IN THE PAINT UNDER THE RT ENGINE PYLON. REMOVED THE PAINT AND FOUND A 1.5 INCH CRACK. STARTING AT THE FWD BOTTOM CUT OUT FOR THE FWD SUPPORT BEAM. APPEARS THAT THERE WAS NOT ENOUGH CLEARANCE IN THE TAILCONE SKIN FOR THE MOVEMENT OF THE ENGINE BEAM WHEN THE AIRCRAFT WAS MANUFACTURED.  SUBMITTED TO MFG ENGINEERING FOR REPAIR.                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA22CE   E00053EN             
             20080909     CE  2008       9          9          CWQR200808       120080821G5320661503517       SUPPORT BRACKET                         CESSNA560   560XL       2076702CE                                                               FUSELAGE        CRACKED         B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05679QS                       5605279                                 DURING A PHASE 1-4 INSP, FOUND THE SUPPORT BRACKET CRACKED, CRACK IS LOCATED IN THE SUPPORT BRACKET FOR THE ECU, THE CRACK INTERSECTS A HOLE FOR THE NUTPLATE THAT ATTACHES ONE OF THE ECU MOUNTING BOLTS. SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER SCR# 376154.                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA22CE                        
             20081001     CE  2008       10         1          CWQR200809       120080821G5320661503515       SUPPORT BRACKET                         CESSNA560   560XL       2076702CE                                                               FUSELAGE        CRACKED         B  CWQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05679QS                       5605279                                 DURING A PHASE 104 INSPECTION, FOUND THE SUPPORT BRACKET CRACKED.  CRACK IS ABOUT 1.5 INCHES LONG AND IS CENTERED AT THE ATTACH POINT FOR THE VALVE.  SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER SCR NR 376160. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA22CE                        
20080313000482008031300048SO  2008       3          13         DAL26220220      120080218G49101159AC30551103  DUCT                                    GULSTMG1159 GIV         3980115SO                                                               APU INLET       CRACKED         E  CLWAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05589HM6464                   1153                                    A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA12EA                        
20080317002522008031700252EU  2008       3          17         DJSR20080125     120080125G361032156321        PRESSURE VALVE                          AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE731*     01518WP                              BLEED AIR SYS   MALFUNCTIONED   B  DJSAA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL23531FL15                     113                                     NR 1 BLEED OVERHEAT LIGHT ILLUMINATED PASSING 15,000 WITH CORRESPONDING CABIN PRESSURE FLUCTUATIONS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA7EU    E6WE                 
20080310003432008031000343EU  2008       3          10         DJSR20080205     120080205G5610MY20268109      WINDSHIELD                              AMD   FALCONFALCON20    2730103EU  GARRTTTFE731TFE731*     01518WP                              COCKPIT         CRAZED          D  DJSRA   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      GL23541FL3                      48                                      F/O`S WINDSHIELD OUTER PANE CRAZED OBSTRUCTING F/O`S VISION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA7EU    E6WE                 
20080320000212008032000021EU  2008       3          20         DJSR20080226     120080226G3231                MECHANISM                               AMD   FALC20FALCON      2720302EU  GARRTTTFE731TFE731*     01518WP                              NLG DOOR        ICED            B  DJSAA   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      GL23521FL15493                  68                                      NOSE GEAR DOOR WOULD NOT CLOSE IN FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  F  A7EU    E6WE                 
20080428003442008042800344    2008       4          28         DJSR20080417     420080417G3417065008206       AIR DATA MODULE                         AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE731*     01518WP                              COCKPIT         MALFUNCTIONED   B  DJSAA   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      GL23511FL     68                122                                     ALTIMETER SYSTEMS SHOWING MISCOMPARE (EXCEEDING 50 FT AT 5000 FT).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA7EU    E6WE                 
20080122000892008012200089WP  2008       1          22         DSC4331DL6292    220080110G721031022811        RETAINER SEAL                                                              GARRTTTPE331TPE33110R   0517 WP                              ENGINE          CRACKED         B      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      SO15                                        P37369C                     NO GEARCASE NEGATIVE PRESSURE INDICATED DURING ENGINE TEST STAND FUNCTIONAL TESTING.  TROUBLESHOOTING FOUND CRACKS IN SEAL RETAINER.  SUBJECT RETAINER IS MADE WITH ALUMINUM. OLDER PN 693905-10 IS MADE WITH STEEL.  SB 72-0224 AUTHORIZED INSTALLATION OF ALUMINUM RETAINER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                         4  T          E4WE                 
             20080603     EU  2008       6          3          DT1R200800001    120080508G27001090020477      LEVER                                   AGUSTAA109  A109S       0260103EU                                                               YAW TRIM SYSTEM DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17167JC40                     22067                                   OPENED THE ACCESS PANEL UNDER THE CO-PILOT'S SEAT, FOUND THE YAW TRIM LEVER (PN 109-0020-47-7 NSN) DETACHED FROM THE YAW TRIM MOTOR SHAFT.  NO DAMAGE NOTED TO THE MOTOR SHAFT.  THE LEVER WAS INTACT BUT DAMAGED AT THE POINT WHERE IT CONTACTS THE SHAFT, BUT HAD THE CORRECT HARDWARE AND COTTER PIN INSTALLED.  THE APPLICABLE PUSH-ROD END (ATTACHED TO THE LEVER) WAS ALSO LOOSE.  INSPECTED AND RETORQUED THE ROD-END.  REPLACED AND TORQUED THE LEVER, REINSTALLED TO THE YAW TRIM MOTOR SHAFT, AND COMPLETED OPERATIONAL CHECK WITH NO DEFECTS NOTED.                                                                                                                                                                                  1G71 3U    RTH7EU                         
             20080828     NM  2008       8          28         DU4R2008238      120080822G5322                SHEAR TIE                               DOUG  MD80  MD83        3023681NM                                                               FS 148 L22L     DAMAGED         B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15874GA                       49643                                   ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RT                             
             20080828     NM  2008       8          28         DU4R2008238A     120080822G5330                SKIN                                    DOUG  MD80  MD83        3023681NM                                                               FS 148 L22L     DAMAGED         B  DU4RO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      SO15874GA                       49643                                   ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RT                             
             20081201     NM  2008       12         1          DU4R2008263      120081124G531536726           FLOORBEAM                               BOEING737   7378Q8      13844BXNM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15171LF                       30637                                   FOUND CORROSION IN AFT PIT ON TOP SURFACE OF FLOORBEAM AT BS 787 TO BS 847 RBL 16.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
             20090105     NM  2009       1          5          DU4R2008273      120081213G5314                KEELBEAM                                BOEING757   75723APF    1384966NM                                                               BS 956          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION AT TIMCO-LCQ, LAKE CITY, FL FOUND KEEL BEAM LOWER SURFACE CORSS BRACE HAS CORROSION AT BS 956S/O 318002   N/R #35360                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008274      120081213G5314                KEELBEAM                                BOEING757   75723APF    1384966NM                                                               BS 1040         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND KEELBEAM LOWER SURFACE CROSS BRACE HAS CORROSION AT BS 1040.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008275      120081216G5730                SKIN                                    BOEING757   75723APF    1384966NM                                                               LT WING         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND LT WING HAD CORROSION IN UPPER SKIN AT ALL VORTEX GENERATORS                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008276      120081216G5330                SKIN                                    BOEING757   75723APF    1384966NM                                                               BS 600-612      DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND 3 EA.  DENTS IN LOWER FWD FUSELAGE BELOW MLG DOOR SCUFF PLATE BS 600-612.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008277      120081216G5330                SKIN                                    BOEING757   75723APF    1384966NM                                                               BS 1125         DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND DENT IN EXT. FUSELAGE SKIN BS 1125, S-10L LAP SEAM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008278      120081216G5330                SKIN                                    BOEING757   75723APF    1384966NM                                                               BS 1364-1410    DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND NUMEROUS CREASES IN EXT. FUSELAGE SKIN BS 1364 - 1410, S-26L TO S-26R                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008279      120081217G5711                SPAR                                    BOEING757   75723APF    1384966NM                                                               LT WING         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT WING REAR SPAR BELOW LEFT AFT BOOST PUMP RSS 185.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008280      120081217G5314                KEELBEAM                                BOEING757   75723APF    1384966NM                                                               BS 996          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON KEELBEAM LOWER SURFACE CROSS BRACE AT BS 996.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008281      120081216G5330                SKIN                                    BOEING757   75723APF    1384966NM                                                               BS 1932-1936    CORRODED        B      R   AUTOROTATION                                                                                    O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON EXT SKIN AROUND APU OIL FUEL DRAIN MAST RT APD ACCESS DOOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008282      120081217G5320                SUPPORT                                 BOEING757   75723APF    1384966NM                                                               BS 1098         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON WING TO BODY FAIRING SUPPORT ABOVE RT WING AT BS 1098.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008283      120081210G5320148N31388000    STRAP                                   BOEING757   75723APF    1384966NM                                                               ZONE 300        CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION,  FOUND HEAVY CORROSION ON 2 EA. SUPPORT STRAPS REMOVED FROM BS 1825, B/O 0, RT SIDE TO HORIZ STAB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008284      120081217G5711112N100217      SPAR                                    BOEING757   75723APF    1384966NM                                                               ZONE 500        CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION ON WEB, LT WING REAR SPAR, ABOVE LT AFT BOOST PUMP WS 188                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA2NM                         
             20090105     NM  2009       1          5          DU4R2008285      120081228G5512                SKIN                                    BOEING757   75723APF    1384966NM                                                               ZONE 900        CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15868AN                       24868                                   DURING SCHEDULED INSPECTION, FOUND CORROSION IN SEVERAL AREAS OF UPPER SURFACE SKINS ON LT HORIZONTAL STABILIZER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA2NM                         
             20080828     NM  2008       8          28         DUR42008238B     120080822G5313                LONGERON                                DOUG  MD80  MD83        3023681NM                                                               FS 148 L22L     DAMAGED         B  DU4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15874GA                       49643                                   ACFT ARRIVED WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RT                             
20080508000972008050800097NM  2008       5          8          DXTA200803018    120080424G2613RP16100         SENSOR                                  AMD   FALC50FALCON2000  2730170NM  PWC   PW308 PW308C      52182NE                              BLEED AIR SYS   INOPERATIVE     E  DXTAA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL07223QS430                    86                                      BLEED OVERHEAT LIGHT CAME ON 2 MIN AFTER TAKEOFF.  CHECKLIST ACCOMPLISHED AND CREW WAS UNABLE TO ISOLATE THE MALFUNCTION.  FAULT CODE 404 AND 428.  BLEED OVERHEAT COMES ON WITH APU BLEED ON AND ENGINE OFF. REMOVED & REINSTALLED TEMP SENSOR L70HU. OPS & LEAK CHECKS GOOD IAW MM 36-70-00                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA50NM   E00065EN             
             20080715     CE  2008       7          15         E812008F00000    120080213G532050430043619     CHANNEL                                 BEECH B300  B300        1159232CE                                                               FUSELAGE        CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0337TD 6102                   FL25                                    INVESTIGATED PILOT COMPLAINT OF LOOSE FUSELAGE SKIN RIVETS AT CABIN DOOR HINGE AREA. FOUND FUSELAGE DOOR FRAME CHANNEL CRACKED. CABIN DOOR DAMPER ACTION ALSO REPORTED AND FOUND TO BE WEAK. SUSPECT CAUSED BY CABIN DOOR "BOTTOMING OUT" EXCESSIVELY HARD OR EXCESSIVE WEIGHT ON DOOR OVER REPEATED CYCLES. TECH/ INSPECTORS SHOULD  CHECK DOOR DAMPNER OPERATION AT SCHEDULED PHASE INSPECTIONS AND CORRECT IF WEAK OPERATION NOTED.  EVIDENCE OF LOOSE HINGE AREA RIVETS SHOULD ALSO BE INVESTIGATED FOR POSSIBLE CRACKED STRUCTURE UNDER THRESHOLD. (K)                                                                                                                                                                                     2L72 4T    RTA24CE                        
20080508000912008050800091NE  2008       5          8          EY2R080424001    320080424G61117826761         BEARING                                 EMB   120   EMB120      3260201SO                                   HAMSTD14RF  14RF9       NE  BLADE           CRACKED         B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    (0087319) CRACKED RACE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T    RTA31SO           6  CP11NE    
20080114000412008011400041EA  2008       1          14         FAA010808001     220080108G7200MILH60001       BREATHER TUBE                           AYRES S2    S2RT15NORMAL0970105SO  PWA   PT6   PT6*        52043EA                              ENGINE          COLLAPSED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO072281A7940                   T15034                                  ENGINE BREATHER HOSE SWELLED ON INSIDE FROM THE ORIGINAL 1INCH DIAMETER TO .3750 INCH DIAMETER FROM HOT OIL FUMES. THRUSH ADDRESSED THE SAME PROBLEM ON THE MFG POWERED LINE. THIS IS NOT AN ISOLATED INCIDENT. THE CONDITION NOTED CAN ONLY BE FOUND AFTER HOSE REMOVAL. EXTERIOR OF HOSE LOOKS OK. SUGGEST A SCHEDULE OF REPLACEMENT EVERY 2000 HOURS.                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T3  T  A3SW    E2NE                 
20080131000072008013100007EU  2008       1          31         FAA011808001     220080104G7321CASC514         FUEL CONTROL                            GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              ENGINE          INOPERATIVE     C      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      EA25396U 4905                   1350        16820                       ON APPROACH TO TTN THE AUTO THROTTLES DISENGAGED. THE RT LEVER KNOB WAS ONE KNOB AFT OF THE LT.  WHEN RT LEVER WAS ADVANCED FORWARD THE RT ENGINE DID NOT RESPOND TO THROTTLE MOVEMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA12EA   E25NE                
20080131000082008013100008SO  2008       1          31         FAA011808002     120080110G7930                OIL SYSTEM                              GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              ENGINE          LOW PRESSURE    D      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      EA17396U 4905                   1350        16820                       30 MINUTE INTO THE FLIGHT OIL PRESSURE DROPPED TO 7 PSI. NO ASSOCIATED CAS MESSAGE. OIL TEMP WAS SLIGHTLY HIGHER THAN LT ENGINE. FUEL TEMP WAS 19 DEGREES HIGHER THAN LT.  DURING DESCENT OIL PRESSURE CAME BACK TO 47 PSI.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA12EA   E25NE                
20080131002982008013100298CE  2008       1          31         FAA012408001     120080124G2710556536118       CABLE                                   CESSNA500   550         2076604CE                                                               AILERON         WORN            B  N81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09338B                        5501132                                 DURING A PHASE 5 IT WAS FOUND THAT THE AILERON CABLES WERE LOCATED IN THE WRONG GROVES OF THE FUSELAGE SECTOR, CAUSING GROOVES TO BE WORN INTO THE SECTOR BY THE CABLES. THERE IS A SPECIAL "NOTE" IN THE MAINTENANCE MANUAL 27-11-08 SECTION 7 FOR THE AILERON LEFT WING CONTROL CABLE REMOVAL/INSTALLATION, STATING CABLES 8 AND 9 ROUTE AROUND THE SECTOR ASSEMBLY IN THE LOWER GROOVE.  THIS IS THE FIRST INSPECTION OF THIS SINCE THE AIRCRAFT WAS NEW AND THE IMPROPER ROUTING WAS DONE AT THE FACTORY.  CORRECTIVE ACTION WAS TO REPLACE THE PART.                                                                                                                                                                                       1L72 4F      A22CE                        
20080312000032008031200003CE  2008       3          12         FAA021208001     120080212G2810                FUEL CAP                                CESSNA172   172         2072402CE                                                                               DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15     4413                                                           LEFT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CAP RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END "S" HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SENDING UNIT LOCKING IT AT A 10 GAL. INDICATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O    NT3A12                         
20080414000012008041400001    2008       4          14         FAA030408001     120080304G4990                PUMP                                                                                                                                    APU ENGINE      FAILED          B      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SW99     135991468                                                      2 APUS WERE REPORTED LOP AUTO SHUTDOWN. DISASSEMBLY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE'S BEARING DID NOT HAVE LUBRICATION AT ALL.  THE OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLATE MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQUENCE OF INSUFFICIENT OIL PRESSURE.                                                                                                                                                                                                                                                        
20080414000032008041400003CE  2008       4          14         FAA031008001     120080310G2497                WIRE                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              COCKPIT         ARCED           B      BA  EMER. DESCENT           UNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      SW1743SA 10256                  5500086                                 PILOT REPORTED CB LABELED LT CB PANEL OPENED IN FLIGHT, PILOT BLEW THE GEAR DOWN AND INITIATED A FLYBY OF THE TOWER TO ASSURE THE GEAR WAS DOWN. AC LANDED WITHOUT FURTHER INCIDENT.  MAINT INVESTIGATION REVEALED THAT THE CROSSOVER POWER WIRE FROM THE CO-PILOTS CB PANEL HAD RUBBED AND ARCED TO THE NUT AND COTTER KEY ATTACHING THE AILERON CABLE LINK FROM THE PILOTS CONTROL COLUMN TO THE OB LT FWD AILERON CABLE. THE WIRE WAS NOT PROPERLY ROUTED OR SECURED. THE WIRE LAYS UNDERNEATH THE AIR CONDITIONER DUCTING AND IS NOT VISIBLE WITH ONLY THE COCKPIT FLOORBOARDS REMOVED. THE WIRE SUPPLIES POWER FROM THE CO-PILOTS CB PANEL TO THE PILOTS CIRCUIT BREAKER PANEL BUSS THAT SUPPLIES POWER TO THE FOLLOWING BREAKERS ACM-2, W/1L72 4F4  F  A22CE   E1NE                 
20080403000422008040300042CE  2008       4          3          FAA08222001      120080222G25203037091BS       SEAT                                    RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE731*     01518WP                                              MISINSTALLED    B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE01800RC                       258660                                  DURING PRE-FLIGHT INSPECTION IT WAS NOTED THAT NR2 RT SEATBACK WOULD NOT BREAK OVER AND FOLD FWD IAW PLACARD TO REMOVE ESCAPE HATCH.  THIS CONDITION PREVENTS ESCAPE HATCH FROM BEING EASILY REMOVED.  FURTHER INVESTIGATION REVEALED THAT THE NR2 RT SEAT HAD BEEN SWAPPED WITH THE NR1 LT SEAT.  SEATS ARE A DIFFERENT PN.  THIS APPARENTLY HAPPENED AT LAST MAJOR MAINT, QUITE SOME TIME AGO.  SEATS ARE A DIFFERENT PN, BUT WE COULD NOT FIND IN WRITING THAT SPECIFIED THIS INFORMATION NOR IS THERE A REQUIRED INSP TO CHECK FOR THIS CONDITION.  TALKS WITH MFG TECH INDICATE THAT THIS CONDITION IS FOUND FROM TIME TO TIME.   ACCOMPLISH AN IMMEDIATE INSP TO VERIFY THAT THE CORRECT PN SEAT IS IN THE NR2 RT POSITION AND CORRECT ANY2L72 4F4  FRTA3EU    E6WE                 
20080129000112008012900011CE  2008       1          29         FAA20080118      120080118G2752505212234       ACTUATOR                                BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              ZONE 600        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0985TB                        LJ833                                   RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE.  CRACK RUNS PARALLEL TO TUBE .                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3T4  T  3A20    E4EA                 
20080402000272008040200027CE  2008       4          2          FAA2008123001    120080123G61205221220F        PILOT VALVE     WOODWARD                BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              PROP GOVERNOR   BROKEN          B      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      EA63401BC     697   00066       TH1668                                  PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISCOVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXITED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RETRIEVED.                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  3A16    E3SO                 
             20081217     CE  2008       12         17         H51R08001        120081203G26202MD31AX287G     SWITCH                                  LEAR  35    31A         5170531CE                                                               EXTINGUISHERS   STICKING        B  H51RK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      NM03420LJ3052                   111                                     FAILURE OF SWITCH IN THE ENGINE FIRE PULL SWITCH ASSY.  AFTER ACCESSING THE FIRE PULL SWITCH ASSEMBLY TO VERIFY AIRWORTHINESS DIRECTIVE 95-21-03, AMENDMENT 39-9388, APPLICABILITY, THE S4 MICROSWITCH FAILED IN THE CLOSED POSITION.  THE AIRWORTHINESS DIRECTIVE WAS ISSUED FOR THIS PROBLEM, BUT WAS NOT APPLICABLE TO THIS SWITCH BY S/N, SUSPECT ADDITIONAL LOTS MAY BE EFFECTED.  AFTER REASSEMBLY OF GLARESHIELD, FUNCTIONAL TESTS REVEALED THE MICROSWITCH HAD STUCK CLOSED, PREVENTING LT ENGINE BLEED AIR FROM WORKING.  VISUAL INSPECTION OF SWITCH SHOWS THE S4 MICROSWITCH ACTUATOR STUCK IN THE RECESSED POSITION.  SWITCH P/N 6608214-3, S/N 2280, F.T. DATE FEB '93, MANUFACTURE EATON P/N 865001-3  AD WAS FOR SWITCHES S/N 2322L72 4F    RTA10CE                        
20080402000372008040200037    2008       4          2          HN8R200800001    420080122G61226602263         CONTROL CABLE                           MOONEYM20   M20J        5870219SW  LYC   O360  IO360A1A    41514EA                              PROP GOVERNOR   BROKEN          B  HN8RK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CE0558102298                    243008                                  PROPELLER GOVERNOR CONTROL CABLE BROKE WHILE AIRCRAFT WAS ON GROUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A3     1E10                 
20080404000032008040400003NM  2008       4          4          IU6R232726       120080306G2710654484515       MANIFOLD                                BOEING737   737         UTILSYSNM                                                                               BROKEN          B  IU6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01     71885                                                          FILTER BOWL BORE OF MANIFOLD BROKE OFF AT THE THREADS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
             20080522         2008       5          22         LJER050608       220080506G741410357424        BUSHING                     S4LSC200    ROBSINR22   R22BETA     7640110NM                                                               MAGNETO         LOOSE           B  LJERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM097155W531  531   E07DA122R   2759                                    ROTOR BUSHING DEBONDED AND LOOSE, CAUSED ROTOR AND GEAR PLAY.  MAGNETO FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O      H10WE                        
20080508000252008050800025CE  2008       5          8          LJER210408       120080421G323312810016        HOUSING                                 CESSNA172   172RG       2072438CE  LYC   O360  O360*       41514EA                              LT MLG ACTUATOR CRACKED         B  LJERA   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      NM099877B594                    172RG1066                               LANDING GEAR FAILED TO RETRACT.  LT MAIN ACTUATOR HOUSING CRACKED AT MOUNTING HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A17    E286                 
             20080715     CE  2008       7          15         MT9R00000040     120080530G7603SL60061         POWER LEVER                             CESSNA208   208B        2073701CE  PWA   PT6   PT6*        52043EA                              ENGINE CONTROL  BROKEN          B  MT9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW051324G                       208B0777                                ENGINE CONTROL QUADRANT POWER LEVER SPRING STOP BROKEN. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3T3  T  A37CE   E2NE                 
20080410002372008041000237GL  2008       4          10         MV1R200808061    220080402G72106898785         SHAFT           ALLSN                   SKRSKYS76   S76         8143010NE  ALLSN 250C  250C30S     03013GL                              NR1 PTO GEAR    CRACKED         B  MV1RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA1738   2822 1058  CAG90287    760087      CAE890282                   OIL LEAK FROM OUTPUT SHAFT NR 1 ENGINE. INSPECTED AREA NO DEFECTS FOUND AT THAT TIME. REPLACED SHAFT SEAL. GROUND OPS AND LEAK CHECK GOOD. AFTER FLIGHT OIL LEAK RETURNED. ON GROUND RUN NO LEAK UNTIL ROTOR WAS RELEASED. OIL LEAK WAS AT OUTPUT SHAFT. FOUND PTO OUTPUT SHAFT CRACKED. REMOVED ENGINE SENT TO ENGINE SHOP FOR INSPECTION AND REPAIR.                                                                                                                                                                                                                                                                                                                                                                                          1G72 3U3  U  H1NE    E1GL                 
             20080520     CE  2008       5          20         MV1R200808136    120080429G21211013841761      BLOWER                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ZONE 100        BURNED OUT      B  MV1RBGHAEMER. DESCENT           O2 MASK DEPLOYED        DEACTIVATE SYST/CIRCUITSUNSCHED LANDING         BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      EA1735   1486 178               BB88                                    DURING FLIGHT, SMOKE INITIATED FROM BEHIND INSTRUMENT PANEL CENTER BELOW. PROJECT POWER TERMINATED. ALL ELECTRICAL POWER NOT NECESSARY FOR FLIGHT, OFF. EMERGENCY LANDING, ON GROUND MAINT FOUND VENT BLOWER ASSY INOP AND BURNED.  BLOWER MEL'D AND FLOWN WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A24CE   E4EA                 
             20090106     NE  2009       1          6          MV1R200808429    120081217G62107615009100053   BLADE                                   SKRSKYS76   S76A        8143006NE                                                               MAIN ROTOR      DELAMINATED     B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA1738   213                    S760087                                 DURING 3 YEAR MAIN ROTOR BLADE INSP FOUND DELAMINATION IN BLACK MAIN ROTOR BLADE ROOT END. DATA SENT TO MFG FOR EVALUATION. TOTAL DELAMINATED AREA IS 1.472 SQUARE INCHES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G72 3U      H1NE                         
             20080717     CE  2008       7          17         N772AF           120080602G554010164001423     HINGE                                   BEECH 200   B200        1152922CE                                                               RUDDER          CORRODED        B  VIBRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      SO13772AF5763                   BB1001                                  CENTER RUDDER HINGE FOUND TO HAVE EXCESSIVE CORROSION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T      A24CE                        
20080508000422008050800042CE  2008       5          8          O7TR200800001    120080311G812046C22924E       TURBOCHARGER                            CESSNA182   T182T       2072738CE                                                               ENGINE          FAILED          B  O7TRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP17                                                                    MAJOR TURBO FAILURE DUE TO SEPARATION OF TURBINE WHEEL HEAD FROM SHAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O    NT3A13                         
             20081210     CE  2008       12         10         OMKR2008-0002    120081124G5100                UNKNOWN                                 CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA                                              UNKNOWN         B  OMKRO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM036197S                       T20608875   L1311661E                   NEW AIRCRAFT FROM FACTORY.  PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL.  FOUND CESSNA SUPPLIED AD LIST DID NOT MATCH LYCOMING SUPPLIED LIST, AND CESSNA HAD CHANGED 8 AD SIGN-OFFS FROM LYCOMING.  CESSNA CONTACTED, AND SAID THEY HAD TO CHANGE LYCOMING'S LIST BECAUSE IT WAS IN ERROR.  LYCOMING CONTACTED WITH NO REPLY YET.  STRAIGHT FLIGHT PMI BROUGHT INTO LOOP, AND WANTED SDR FILLED OUT.  PMI WILL ALSO ACTION.  VERY SERIOUS IN NATURE AS LYCOMING SAYS THEY CHANGED NUMEROUS PARTS FOR AD COMPLIANCE, INCLUDING THE CRANKSHAFT, WHEN THESE AD'S DO NOT APPLY IN THE FIRST PLACE.  SUSPECT YOU WILL FIND LARGE RUN OF LYCOMING ENGINES WITH THIS SAME PROBLEM.  THESE ENGINES ARE NOT AIRWORTHY WITH FALSE AD LISTS1H71 3O3  ORTA4CE    E14EA                
             20081210     CE  2008       12         10         OMKR2008-0003    120081124G5100                NONE                                    CESSNA208   208B        2073701CE                                                                               NONE            B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0322430                       208B2011                                NEW ACFT FROM FACTORY.  PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL.  FOUND NUMEROUS ADS SIGNED OFF AS COMPLIED WITH THAT WERE N/A TO ACFT.  MANY LISTED PARTS THAT WERE SUPPOSEDLY CHANGED.  CONTACTED CESSNA.  WAS ASKED WHY WITH SO MANY NEW ACFT BEING RELEASED, NO ONE ELSE WAS COMPLAINING.  AFTER SEVERAL PHONE CONVERSATIONS AND SEVERAL CORRECTED LISTS, FINALLY HAD AN ACCEPTABLE LIST.  2 ADS WERE NOT ACCOUNTED FOR AND HAD BEEN ISSUED PRIOR TO THE ACFT BORN-ON DATE.  STRAIGHT FLIGHT PMI BROUGHT INTO THE LOOP AND WANTED A SDR SUBMITTED.  HE IS ALSO WORKING.  EXPECT SERIES OF THESE CARAVANS TO HAVE SAME PROBLEM.  THESE ACFT ARE NOT AIRWORTHY WITH FALSE AD LISTS.                                       1H71 3T      A37CE                        
20080204001012008020400101EU  2008       2          4          PAI52008S4818    120080130G5540                STRUCTURE                               PIAGIOP180  P180        6960204EU                                                               RUDDER          CHAFED          B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05134SL2797                   1100                                    DURING D-CHECK INSPECTION, FOUND RUDDER TORQUE CHAFED BY AFT FAIRING P/N 80-561004-401.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3O    RTA59EU                        
20080225000092008022500009EU  2008       2          25         PAI52008S4858    120080212G5512                SKIN                                    PIAGIOP180  P180        6960204EU  PWA   PT6   PT6*        52043EA                              HORIZONTAL STAB CRACKED         B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05138SL           5072        1103                                    DURING D-CHECK INSPECTION, FOUND CRACK 2.5 INCHES LONG IN HORIZONTAL STABILIZER LT LOWER COMPOSITE SKIN.  CRACK IS AT IB END OF LT HORIZONTAL STABILIZER, 5 INCHES AFT OF LEADING EDGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3O3  TRTA59EU   E2NE                 
20080328001022008032800102CE  2008       3          28         PAI52008S4877    120080209G322007436062        SUPPORT FITTING                         CESSNA182   182T        2072703CE                                                               NLG             BROKEN          B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05470P 719                    18281290                                PILOT COMPLAINED OF NOSE WHEEL SHIMMY.  INSPECTION FOUND RIGHT-HAND SIDE OF NOSE GEAR LOWER SUPPORT FITTING BROKEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O    NT3A13                         
             20080602     NE  2008       6          2          PJ6G20080147     220080414G7200310718501       GAS GENERATOR                           AIRTRCAT802 AT802       0390305SW  PWC   PT6   PT6A67AG    52211NE  HARTZLHCB5M HCB5MA3     GL  ENGINE          ERODED          D  PJ6GO   OTHER                                                                                           P  NO WARNING INDICATION                                                         AGAGRICULTURE    1                      SW11627JP566  566               8020238     PCERD0147                   'C' FLANGE EROSION AT SCAVENGE TUBE OIL COUPLING WITH ASSOCIATED PARTIALLY SEVERED 'T' BOLT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
             20090114     NM  2009       1          14         R5KB20081220001  120081220G5320                WEB                                     BOEING727   727212      138407GNM                                                               BS 1213         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO33727NK                       21945                                   WEB CORRODED AT BS 1213 WL 177 RBL 5.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L73 4F      A3WE                         
20080131003052008013100305    2008       1          31         RC2R130L         420080123G61225221220F        PILOT VALVE                 B210800REVJ BEECH 58    58          1152740CE  CONT  O520  IO520CB     17032SO                              GOVERNOR        BROKEN          B      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      NE03401BC     697   00066       TH1668                                  PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISCOVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXITED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RETRIEVED.                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  3A16    E5CE                 
20080414000402008041400040NM  2008       4          14         RI3R200800001    120080331G2840403501          TSU                                     BOEING737   737*               NM                                                               INTERNAL        CONTAMINATED    B  RI3RK   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      SO15                                                                    WHILE PERFORMING TROUBLESHOOTING AND REPAIR OF 4035-01 SERIES TRANSIENT SUPPRESSION UNITS (TSU) IAW COMPONENT MM 28-44-64, REV 2, DATED 20/04/2007, IT WAS DISCOVERED THAT VARIOUS UNITS (7 TOTAL) SHOWED EVIDENCE OF CONTAMINATION ON INTERIOR SURFACES FROM WHAT APPEARS TO BE MOISTURE INTRUSION THROUGH THE CASE SEALS.  AFFECTED UNITS HAVE BEEN PLACED IN QUARANTINE.  IMMEDIATELY NOTIFIED THE ORIGINAL EQUIPMENT MFG AND PRODUCTION AUTHORITY HOLDER, OF THE FINDINGS.  COORDINATING WITH  ENGINEERING AND QUALITY REPRESENTATIVES ON FURTHER ACTION AND FINAL DISPOSITION.  AFFECTED UNITS TO REMAIN IN QUARANTINE UNTIL GUIDANCE IS RECEIVED. CONSULTED WITH FSDO, PMI.  RECOMMENDED ACTION:  SUBMIT SDR IAW 14 CFR PART 145.221 AND R2L72 4F    RTA16WE                        
20080414001032008041400103NM  2008       4          14         RI3R200800002    120080409G2840403501          TSU                                     BOEING737   737*               NM                                                                               CONTAMINATED    B  RI3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15                                                                    WHILE PERFORMING PRELIMINARY INSPECTION AND TROUBLESHOOTING OF THE TRANSIENT SUPPRESSION UNIT (TSU) 4035-01, S/N 1308, IT WAS DISCOVERED THAT THE UNIT SHOWED EVIDENCE OF INTERNAL CONTAMINATION.  THE CONTAMINATION APPEARS TO BE CAUSED BY MOISTURE INGRESS INTO THE UNIT.  THE UNIT HAS BEEN PLACED IN QUARANTINE, AND PAH/OEM HAS BEEN NOTIFIED OF THE FINDING.                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20080404000082008040400008GL  2008       4          4          SJ3R025859       320080314G6110D495            FORK                                    PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3D     GL  PROPELLER ASSY  CRACKED         B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05     2185 1361                                      HJ494           CRACK INDICATIONS FOUND DURING MAG PARTICLE INSPECTION.  CRACKS ARE LOCATED ON THE THIN SIDE OF ALL (4) FORK SLOTS RADI.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20080402000352008040200035NE  2008       4          2          SJ3R080124001    320080124G6110B6545           CAM FOLLOWER                            BEECH 1900  1900D       1154162CE  PWC   PT6   PT6A42A     52043NE  HARTZLHCE4A HCE4A3I     NE  PROP BLADE      BROKEN          B  SJ3RK   NONE                                                                                            E  VIBRATION/BUFFET                                                              ININSP/MAINT     1                      GL05                                                    HJ1430          REMOVED DUE TO SUSPECTED INTERNAL HUB COMPONENT FAILURE.  BLADE S/N 4152 WAS FOUND TO ROTATE FREELY +/- 12.5 DEGREE POST FIRST GROUND RUN AFTER INSTALLATION.  INSPECTION AFTER DISASSEMBLY REVEALED ONE BROKEN B-6545 PITCH CHANGE KNOB CAM FOLLOWER. THIS PART WAS INSTALLED NEW AT OVERHAUL AND FAILED ON FIRST GROUND RUN.                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA24CE   E4EA    5  CP10NE    
20080423001682008042300168NM  2008       4          23         SROM2008001      120080406G5350654869089       SUPPORT                                 BOEING737   737205      1384456NM                                                               LT MLG WW       GOUGED          C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA39285                  23466                                   LEFT HAND MAIN LANDING GEAR WHEEL WELL FAIRING SUPPORT GOUGED AT AFT OUTBOARD SIDE. REPAIRED LT MLG WHEEL WELL SUPPORT AT AFT OUTBOARD SIDE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-476 AND ASI SOLUTIONS DRAWING 5350476-1, REV IR, DATED MARCH 13, 2008.  REFERENCE NON-ROUTINE CARD 27, DATED 02/27/08.                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20080423001762008042300176NM  2008       4          23         SROM2008002      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4.  BLENDED AND FOUND CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 TO BE BEYOND LIMITS.  REPAIRED AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-4.  REFERENCE NON-ROUTINE CARD 488, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
             20080714     NE  2008       7          14         SROM20080023     220080523G7200JT8D17A         ENGINE                                  BOEING737   737205      1384456NM  PWA   JT8   JT8D17A     52049NE                              NR 1            BIRD INGESTION  C  SROMEL  ENGINE SHUTDOWN         ABORTED APPROACH                                                        CJRF.O.D.                    WARNING INDICATION        PARTIAL RPM/PWR LOSS      APAPPROACH       1                      AL03736BP366992561              23465       709500                      INGESTED LARGE BIRD ON APPROACH TO AKU, SHUT-DOWN ENGINE AND COMPLETED MISSED APPROACH.  DIVERTED TO SCC AND MADE UNEVENTFUL LANDING.  REMOVED AND REPLACED NR 1 ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E2EA                 
             20081126         2008       11         26         SROM20080024     420080926G2565D31355440       SLIDE                                   BOEING737   737205      1384456NM                                                               R2 DOOR         INOPERATIVE     I  SROMK   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      AL03733PA                       23466                                   DURING MINI EVACUATION DEMONSTRATION TRAINING SLIDE DEPLOYED BUT DID NOT INFLATE. WAITING ON TEAR DOWN REPORT FOR FINAL DISPOSITION.  11/20/08 FINAL DISPOSITION. TEARDOWN REPORT INDICATED NO FINDINGS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20080423001862008042300186NM  2008       4          23         SROM2008003      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50.  CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50 BLENDED BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-1.  REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9.  REFERENCE NON-ROUTINE CARD 494, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA16WE                        
20080423001712008042300171NM  2008       4          23         SROM2008004      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CORROSION FOUND ON FLOORBEAM STA BS 1016 BL 5 THRU BL 38 LEFT HAND.  CORROSION ON FLOORBEAM STA BS 1016 BL 5 THRU BL 28 LEFT REMOVED AND FOUND TO BE BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-01, FIGURE 1.  FLOORBEAM REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-04, FIGURE 1.  REFERENCE NON-ROUTINE CARD 19, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
20080423001332008042300133NM  2008       4          23         SROM2008005      120080406G5320                TORQUE BOX                              BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT. CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT REMOVED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06.  ORIGINAL MATERIAL 0.063, AMOUNT OF REMOVED MATERIAL 0.025, OUT OF LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01, PAGE 45, DETAIL V.  FORMED SECTION REPAIR CARRIED OUT IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-03.                                                                                                                                                                            2L72 4F    RTA16WE                        
20080423001782008042300178NM  2008       4          23         SROM2008006      120080406G5330                SKIN                                    BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CRACK IN FUSELAGE SKIN AT STA BS 760 STR 19L, (NDT CONFIRMED CRACK).  REPAIRED FUSELAGE SKIN AT STA BS 760 STR 19L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 48, FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-02.  REFERENCE NON-ROUTINE CARD 542, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20080423001772008042300177NM  2008       4          23         SROM2008007      120080406G252043100001        BAR                         87513       BOEING737   737205      1384456NM                                                               SEAT            CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   REPAIR CRACKED SPREADER BARS ON PASSENGER SEATS.  REPAIRED CRACKED SPREADER BARS ON PASSENGER SEATS IN ACCORDANCE WITH CPAI EO C007-2525-B737-01 AND FAA DER APPROVED 8110-3, 080-1226-08-471 AND ASI DRAWING 2520471-1, REV IR, DATED MARCH 19, 2008.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 160, DATED 02/28/08.                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20080423001882008042300188NM  2008       4          23         SROM2008008      120080406G5314                KEELBEAM                                BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LOWER CHORDS OF KEEL BEAM IN MAIN LANDING GEAR HAS CORROSION AT LOWER FLANGE IN SEVERAL AREAS UPPER & LOWER SURFACES FROM STA BS 663-727 RBL 6.5 & LBL 6.5.  REPAIRED LOWER CHORD OF KEEL BEAM IN MLG WHEEL WELL AT LOWER FLANGE IN ACCORDANCE WITH BOEING MESSAGE 1-789220434-4, DATED MARCH 28, 2008.  FASTENERS INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-2.  REFERENCE NON-ROUTINE CARD 570, DATED 03/04/08.                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20080423001722008042300172NM  2008       4          23         SROM2008009      120080406G5320                FITTING                                 BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CLIP CRACKED AT STA BS 1006 STR 21L.  REPLACED CLIP AT STA BS 1006 STR 21L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01 AND 51-30-02.  REFERENCE NON-ROUTINE CARD 578, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
20080423001732008042300173NM  2008       4          23         SROM2008010      120080406G5320                FITTING                                 BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   STRINGER TO FRAME CLIP REQUIRES BLENDING AT STA BS 907 STR 25L (REAR CARGO PIT).  INSTALLED NEW CLIP AT STA BS 907 STR 25L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-03.  REFERENCE NON-ROUTINE CARD 586, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20080423001692008042300169NM  2008       4          23         SROM2008011      120080406G5340                STRINGER CLIP                           BOEING737   737205      1384456NM                                                               FUSELAGE        DAMAGED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   STRINGER TIE CLIP DAMAGED AT STA BS 500A, STR 25R.  REPLACED STRINGER TIE CLIP AT STA BS 500A STR 25R IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-1, PAGE 9, SECTION 7 AND 51-30-03.  REFERENCE NON-ROUTINE CARD 590, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
20080423001812008042300181NM  2008       4          23         SROM2008012      120080406G5330                SKIN                                    BOEING737   737205      1384456NM                                                               FUSELAGE        DAMAGED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LIGHTNING STRIKE AT STA BS 933 STR 25.5R.  REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 23 (PERMANENT REPAIR), SECTION 1, PARAGRAPH 3., (NDT08-0509).  REFERENCE NON-ROUTINE CARD 602, DATED 03/04/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
20080423001342008042300134NM  2008       4          23         SROM2008013      120080406G5320                ATTACH FITTING                          BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CRACK IN INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L.  REPLACED INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2, FIGURE 7,3,11 AND 12.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 647, DATED 03/05/08.                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
20080423001702008042300170NM  2008       4          23         SROM2008014      120080406G5320                ATTACH FITTING                          BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CRACK IN INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L.  REPLACED INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2, FIGURE 7, 3, 11 AND 12.  REFERENCE NON-ROUTINE CARD 648, DATED 03/05/08.                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
20080423001352008042300135NM  2008       4          23         SROM2008015      120080406G5311                FRAME                                   BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CRACK ON BODY FRAME INNER CHORD STA BS 616 LEFT HAND AT STUB BEAM LOWER CHORD.  REPAIRED BODY FRAME INNER CHORD STA BS 616 LT AT STUB BEAM LOWER CHORD IN ACCORDANCE WITH BOEING SB 737-53A-1254.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 672, DATED 03/05/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20080423001672008042300167NM  2008       4          23         SROM2008016      120080406G5514                BUSHING                                 BOEING737   737205      1384456NM                                                               HORIZ STAB      LOOSE           C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LOOSE BUSHING ON STABILIZER SCREW JACK LOWER RIGHT HAND MOUNTING STRUCTURE (P/N 6-37464-1).  REPLACED BUSHING ON STABILIZER SCREW JACK LOWER RT MOUNTING STRUCTURE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 078-1236-08-473 AND ASI SOLUTIONS DRAWING 5340473-1, REV IR, DATED MARCH 14, 2008.  REFERENCE NON-ROUTINE CARD 740, DATED 03/06/08.                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA16WE                        
20080423001742008042300174NM  2008       4          23         SROM2008017      120080406G783065MK781031      BRACKET                                 BOEING737   737205      1384456NM  PWA   JT8   JT8D17A     52049NE                              NR 1 ENGINE     CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA39277                  23466       709507                      LEFT HAND ENGINE TAILPIPE CRACKED AT BRACKET MOUNT (3 O'CLOCK POSITION).  REPAIRED LEFT HAND ENGINE TAILPIPE BRACKET MOUNT (3 O'CLOCK POSITION) IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-477 AND ASI SOLUTIONS DRAWING 7830477-1, REV IR, DATED MARCH 18, 2008.  REFERENCE NON-ROUTINE CARD 826, DATED 03/11/08.                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA16WE   E2EA                 
20080423001752008042300175NM  2008       4          23         SROM2008018      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT LBL 24.5 STA BS 663.  REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT LBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410.  REFERENCE NON-ROUTINE CARD 843, DATED 03/18/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20080423001832008042300183NM  2008       4          23         SROM2008019      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT RBL 24.5 STA BS 663.  REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT RBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410.  REFERENCE NON-ROUTINE CARD 844, DATED 03/18/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20080423001892008042300189NM  2008       4          23         SROM2008020      120080406G5315                FLOORBEAM                               BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CORROSION ON FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39.  REPAIRED FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9, FIGURE 5.  REFERENCE NON-ROUTINE CARD 858, DATED 03/25/08.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA16WE                        
20080423001952008042300195NM  2008       4          23         SROM2008021      120080406G5320                TORQUE BOX                              BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   CRACKED APU TORQUE BOX WEB AT STA BS 1115 RBL 2.  HFEC CARRIED OUT IN ACCORDANCE WITH BOEING 737 NDT MANUAL 51-00-00, FIGURE 23, PART 6 ON A CUT-OUT ON THE APU TORQUE BOX, STA BS 1115.  NO DEFECTS EVIDENT (NDT08-0461).  APU TORQUE BOX WEB AT STA BS 1115 RBL 2 REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-01, FIGURE 1 AND INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-02, FIGURE 3 AND 11.  REFERENCE NON-ROUTINE CARD 859, DATED 03/25/08.                                                                                                                                                                                                                           2L72 4F    RTA16WE                        
20080423001842008042300184NM  2008       4          23         SROM2008022      120080405G5314                KEELBEAM                                BOEING737   737205      1384456NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   LOWER CHORD OF KEEL BEAM IN MLG HAS CORROSION ON VERTICAL AND HORIZONTAL FLANGES IN SEVERAL AREAS FROM STA BS 663-727 LBL 615.  REPAIRED LOWER CHORD OF KEEL BEAM ON LT SIDE BETWEEN STA BS 663 THRU 727 IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3,  095-1236-08-483 AND ASI SOLUTIONS DRAWING 5310483-1, REV IR, DATED APRIL 4, 2008.  CORROSION BLENDED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06 AND FAIRED AT A 10:1 RATIO IN ACCORDANCE WITH SRM 51-10-06.  ALL PARTS TREATED AND PROTECTED IN ACCORDANCE WITH SRM 51-10-2.  ALL FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-2.  REFERENCE NON-ROUTINE CARD 876, DATED 03/31/08.                                                                   2L72 4F    RTA16WE                        
20080410001632008041000163    2008       4          10         STS004           420080402G25641218FASA6311701 LIFE RAFT                               EMB   135   EMB135KL    3260302SO                                                                               MISINSTALLED    B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15WL7R      2                                                         THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HOUSING AND THE LINK VALVE ARE NOT LOCATED PROPERLY.  THE CAUSES THE LENGTH OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED.  THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY METHOD FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE.                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTT00011AT                     
200805141    200805141    NE  2008       5          14         SWDG08RD0113     220080508G72103030988         SEAL            PWC                     AIRTRCAT802 AT802A      0390308SW  PWC   PT6   PT6A67AG    52211NE  HARTZLHCB5M HCB5MA3     GL  RGB             DEFORMED        D  SWDGK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SW11804DG738        PCERD0113   802A0089    PCERD0113                   EXCESSIVE OIL LEAKAGE AROUND PROP SHAFT.  FOUND FELT SEAL MISALIGNED AND INTERFERING WITH THE SHAFT SEAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
200805141    200805141        2008       5          14         SWDG20085569     420080414G6122311849703       GOVERNOR                                AIRTRCAT802 AT802A      0390308SW  PWC   PT6   PT6A67AG    52211NE  HARTZLHCB5M HCB5MA3     GL  PROPELLER       LEAKING         D  SWDGA   UNSCHED LANDING                                                                                 KR FLUID LOSS                PARTIAL RPM/PWR LOSS                                AGAGRICULTURE    1                      SW11804DG721  721               802A0089    PCERD0113   HBA1298         GOVERNOR HAS EXCESSIVE BETA VALVE OIL LEAKAGE AND ERRATIC TORQUE FLUCTUATION.  PART REMOVED AND SENT TO REPAIR STATION FOR EVALVUATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20080225000072008022500007CE  2008       2          25         TIMR20080001     120080213G3233993880081       ACTUATOR                                BEECH 99    C99         1154006CE  PWA   PT6   PT6A36      52043NE                              MLG             LEAKING         B  TIMAO   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      NM07239AL     4731              U239                                    LT MLG DID NOT RETRACT AFTER TAKEOFF.  PILOT FLEW AC TO HOME BASE WITH GEAR DOWN.  INVESTIGATION REVEALED THAT FLUID WAS PASSING THE PISTON INTERNALLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3T4  T  A14CE   E4EA                 
20080111003072008011100307EA  2008       1          11         UE5R010208001    220080102G73133013635         NOZZLE                                  DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A28           EA                              ENGINE          SHEARED         B  UE5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA61                                                                    WHEN INSTALLING NOZZLE PN 3013635 ONTO NOZZLE ADAPTER ASSEMBLY USING SPECIFIED OHM TORQUE, NOZZLE SHEARED OFF COMPLETELY AT BASE OF THREADS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H72 3T4  TRTA9EA    E4EA                 
20080410002582008041000258CE  2008       4          10         VIB8368K         120080320G3220                BRACE                                   BEECH 100   B100        1152919CE                                                               NLG             CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1397WD 7178                   BE97                                    DISASSEMBLED NLG DURING SCHEDULED MAINT AND FOUND SIGNIFICANT CORROSION OVER MOST OF THE NOSE LANDING GEAR V BRACE, PN 50-820204. WE ALSO FOUND A CRACK OF 0.008 INCH IN THE NOSE BARREL, PN 99-820100-5, WHERE IT LOOKED LIKE IT HAD BEEN REPAIRED IN THE PAST. WE ALSO FOUND A CRACK OF 0.020 INCH IN THE V BRACE, PN 99-810028-989, OF THE LT LANDING GEAR.                                                                                                                                                                                                                                                                                                                                                                                  1L72 4T      A14CE                        
             20081126     EA  2008       11         26         VJ1R20081118001  120081107G3810500120701       WATER HEATER                            CNDAIRCL600 CL6002B16   1900305EA                                                               ZONE 900        OVERTEMP        B  VJ1RBAH EMER. DESCENT           UNSCHED LANDING         DEACTIVATE SYST/CIRCUITS                        MB OVER TEMP                 SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      SW05CGQWI                       5016                                    ACFT AT CRUISING ALTITUDE WHEN A PASSENGER ADVISED THE CREW THAT THEY COULD ODOR SOMETHING BURNING IN THE CABIN AREA. THE CREW DECLARED AN EMERGENCY AND DIVERTED. AFTER LANDING, THE PROBLEM WAS DETERMINED TO BE THE LAVATORY WATER HEATER HAD OVER HEATED CAUSING THE HEATER BLANKET TO EMIT SMOKE AND FUMES. THE WATER HEATER SYS WAS DISABLED BY PULLING THE SYS CIRCUIT BREAKER AND THE ACFT RETURNED TO DEPARTURE. THIS IS THE THIRD SUCH INCIDENT INVOLVING CANADIAN REGISTERED AIRCRAFT.  THE WATER HEATERS WERE UTILIZED FROM 1981 TO 1997 IAW STC SA4370SW IN APPROX 200 NEW ACFT EXECUTIVE INTERIOR INSTALLATIONS. THERE ARE POSSIBLY (2) PER INTERIOR ONE LOCATED BEHIND THE GALLEY AND ONE LOCATED BEHIND THE LAVATORY VANITY. A C2L72 4F    RTA21EA                        
20080414000412008041400041    2008       4          14         WL7R040208001    420080402G2564                HOUSING                                 EMB   135   EMB135KL    3260302SO                                                               LIFE RAFT       MISINSTALLED    B  WL7RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO15          2                                                         THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HSG AND THE LINK VALVE ARE NOT LOCATED PROPERLY.  THIS CAUSES THE LENGTH OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED.  THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY METHOD FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE.                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTT00011AT                     
20080404000072008040400007SO  2008       4          4          WS9R030608001    220080306G8530AEC631397       CYLINDER                                BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO                              ENGINE          CRACKED         B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07     205                                814500                      CRACK BETWEEN 3RD AND 4TH CYLINDER HEAD, COOLING FIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  3A15    E3SO                 
20080404000112008040400011SO  2008       4          4          WS9R031108001    220080311G8530                CYLINDER HEAD                           CESSNA180   180C        2072608CE  CONT  O470  O470L       17026SO                              ENGINE          CRACKED         B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07001                                     069693R                     VISUAL INSPECTION OF THE CYLINDER AS IT WAS RECEIVED FROM THE MFG, REVEALED CRACKED FINS NEAR THE FUEL INJECTOR NOZZLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  5A6     E273                 
20080404000122008040400012EA  2008       4          4          WS9R031908001    220080319G8530AEL14995        RETAINER                                PIPER PA28  PA28*              SO  LYC   O360  O360A4M     41514EA                              CYLINDER        BROKEN          B  WS9RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM07                                        L2841136A                   DISCOVERED THAT ALL (4) OF THE PUSH ROD TUBE RETAINERS WERE BROKE UPON REMOVING THE ROCKER BOX COVERS.  THIS ENGINE HAD JUST BEEN OVERHAULED AND HAS TEST CELL TIME ONLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A13    E286                 
20080401001202008040100120NM  2008       4          1          Y5CR200700003    120080122G6200369D25351       SPRAG CLUTCH                            DOUG  MD500 MD500E      3027372NM                                                               MAIN ROTOR      BROKEN          B  Y5CRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05     760                                                            DURING  A 300HR. INSPECTION ON THE O/R CLUTH THE CUSTOMER FOUND A BROKEN SPRAG CLIP ON THE SPRAG ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G72 3U    NC                             
             20080520     NM  2008       5          20         Y5CR200700004    120080501G6320369D2512311     BEVEL GEAR      DOUG                    DOUG  MD500 MD500E      3027372NM                                                               M/R TRANSMISSIONBROKEN          B  Y5CRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05     616        3668                                                M/R TRANSMISSION GEAR HAS BROKEN TOOTH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G72 3U    NC                             
20080403000442008040300044WP  2008       4          3          YZ4R200800001    120080222G26203260007         EXTINGUISHER                            DOUG  DC3   DC3CR183090C3021466WP  PWA   PT6   PT6*        52043EA                                              INOPERATIVE     B  YZ4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA39300BF                       26744                                   FIRE EXTINGUISHER DID NOT ACTIVATE. THE FIRE EXTINGUISHER IS FILLED WITH 4.5 POUNDS OF HALON 1301 AND PRESSURIZED TO 600 PSIG WITH DRY NITROGEN. THE CONTENTS ARE HELD IN THE CYLINDER BY A PLUG VALVE, PN 13038 WITH AN O-RING SEAL. THIS PLUG VALVE IS COMPRESSED BY THE HOUSING ASSY, PN 33370004. THE HOUSING ASSY IS THREADED INTO THE STEM, PN 31840000. THE DISCHARGE OUTLET IS BETWEEN THE HOUSING ASSY AND STEM. THE OUTLET ASSY SWIVELS ABOUT THE STEM AND HOUSING ASSY FOR ALIGNMENT AT TIME OF INSTALLATION IN AN AIRCRAFT.  WHEN THE FIRE EXTINGUISHER IS FILLED, THE PLUG VALVE AND HOUSING ASSY ARE IN COMPRESSION. THE HOUSING ASSY IS MFG WITH VARIOUS MACHINED GROOVES AND IS DESIGNED FOR THE COMPRESSIVE FORCES. WHEN THE CA2L72 4R3  T  A669    E2NE                 
20080122000612008012200061CE  2008       1          22         ZB0R20080001     120080111G2842S35942          SENSOR                                  CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              FUEL QTY        INTERMITTENT    B  ZB0RO   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      EA39272RP420  40                172S8405                                RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20080122000562008012200056CE  2008       1          22         ZB0R20080002     120080111G2842S35942          SENSOR                                  CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              FUEL QTY        INTERMITTENT    B  ZB0RO   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      EA39963AC226  45                172S8259                                RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10