P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421 

### TO: HOLDERS OF SA226 SERIES SERVICE INFORMATION MANUALS

Attached is SA226 Series Service Letter 226-SL-050, INSPECTION OF RUDDER FLIGHT CONTROL CABLES , Issued: April 15, 2015.

An operator performed an inspection of the rudder control cables under the cockpit fl oor during normal Letter check, and found the left rudder fl ight control cable with extensive damage, such that 5 of the 7 wires were broken.The RH cable was inspected initially using the method described in the SA226 Maintenance Manual (MM), Chapter 27-00-00 and was not identi fi ed as damaged. It was only after further investigation, it was revealed that several strands of some of the wires within the 7x19 cable were broken at the same location as the LH cable. Inspection of these cables is also the subject of AD2011-17-07 and M7 bulletin SA226- 27-072. These cables are life limited to 3,500 hours. This latest failure occurred after only 1500 hours since last replacement. Please insert the attached revised Service Letter Index pages.P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421

## SA226 SERIES SERVICE LETTER INDEX

SL INDEX Page 1 of 3 Issued: February 14, 1992 Revised: March 27, 2003 SA226 SERIES

SA226 SERVICE LETTER

NO. DESCRIPTION DATE

001 DE-ICER BOOT MOISTURE REMOVAL .......................................................................02 14 92 002 GEARCASE OIL DRAIN FITTING .................................................................................05 29 92 003 ADD DRAIN HOLES TO VERTICAL STABILIZER ........................................................10 28 92 004 NOT ISSUED ................................................................................................................ .00 00 00 005 DL5040M5 PITCH TRIM ACTUATOR FREEPLAY MEASUREMENT .....................(R) 08 03 99 006 CARGO DOOR GAS SPRING ATTACH POINT (FUSELAGE FRAME) ........................05 12 93 007 POLYURETHANE HOSES, 5/8 INCH INSIDE DIAMETER (ID) ....................................09 27 93 008 ALTERNATE MEANS OF COMPLIANCE WITH AD 93-15-02 ......................................08 12 93 009 REPLACEMENT OF P/N 69380, MS24593-8 OR J416-8SS-5 BLEED AIR CHECK VALVE ..............................................................................................................10 2 6 93 010 RETURN PORT, NOSE WHEEL STEERING ACTUATOR ............................................11 22 93 011 NOSE LANDING GEAR UPLOCK ROLLER/STRIKER EXTENSION REMOVAL ...................................................................................................................... 06 24 96 012 EXTERIOR EXIT MARKINGS .......................................................................................01 29 97 013 EXTERIOR ESCAPE ROUTE .......................................................................................02 21 97 014 BARBER COLMAN PITCH TRIM ACTUATOR - PERFORM ADJUSTMENT - MECHANICAL/ELECTRICAL STOPS FUNCTIONAL CHECK AND NO-BACK FUNCTIONAL CHECK .............................(R) 02 01 99 015 GENERATOR CONTROL UNIT INTERCHANGEABILITY ......................................(R) 02 09 99 016 PILOT SEAT BACK POCKET INTERFERES WITH JUNCTION BOX ..........................04 02 98 017 BARBER COLMAN PITCH TRIM ACTUATOR - AIRSPEED LIMITATION ..............(R) 09 02 98 018 INSPECTION OF PITCH TRIM ACTUATOR FOR CORRECT INSTALLATION AND FREEDOM OF OPERATION ................................................................................09 09 98 019 INSPECTION/REPLACEMENT OF (31PSI) PNEUMATIC PRESSURE REGULATOR FOR INCORRECT INLET/OUTLET PORT ORIENTATION .......................................... 11 24 98 020 LIFE PRESERVER WITH LOCATOR LIGHT FOR FAR, PART 121.2 AND 121.340 REQUIREMENT ............................................................................................. 12 04 98 021 OVERHAUL TIME LIMIT FOR P/N 27-81009 HYDRAULIC POWER PACK .......................................................................................................................(R) 11 03 99 022 BFGOODRICH P/N 74-451-AC EROSION REPAIR KIT, FOR WING AND TAIL DE-ICE BOOTS ............................................................................................................ 08 2 5 99 023 INSPECTION/REPLACEMENT/PROTECTION OF FUEL BOOST PUMP WIRE HARNESS FOR CHAFFING CONDITION ...................................................(R) 09 25 00 024 NOT ISSUED ................................................................................................................ .00 00 00 025 INSPECTION OF PRIMARY FLIGHT CONTROL CABLE TERMINALS FOR CRACKS/PITTING CORROSION ..................................................................................05 29 01 026 INSPECT P/N 27-81069-011 BLANKET ASSEMBLY FOR PRESENCE OF FLAMABLE FLUID AT EACH PRE-FLIGHT ............................................................07 03 02 027 INSPECT CABIN AND CARGO DOOR, FORE AND AFT "CLICK-CLACK" RECEPTACLES .............................................................................................................03 2403 028 INSPECTION OF MAIN LANDING GEAR (MLG) TRUNNION BUSHING, P/N 27-51009, ATTACHING HARDWARE FOR LOOSENESS .....................................03 27 03

### Issued: February 14, 1992 Revised: September 19, 2014 SL INDEX Page 2 of 3 

## SA226 SERIES SERVICE LETTER INDEX SA226 SERIES

029 INSPECT FOR POSSIBLE CRACKS IN LH/RH FUSELAGE STATION (F.S.) 272 AND 276 FOR MAIN SPAR, F.S. 308 AND 311 FOR AFT SPAR ON AT/TC MODELAIRPLANES OR F.S. 169 AND 173 FOR MAIN SPAR, F.S. 205 AND 208 FOR AFT SPAR ON T/T(A)/T(B) MODEL AIRPLANES, LOWER BELT FRAMES AND NESTED CHANNELS AT LH/RH STRINGER 10A FEEDTHROUGH .....................................................................06 10 03 030 INSPECT FOR CRACKS AND/OR BULGES OF LEFT HAND/RIGHT HAND, INBOARD/OUTBOARD, KEELSON WEB SKIN AT NACELLE STATION (N.S.) 141.69 .................................................................................................06 10 0 3 031 ONE TIME INSPECTION OF UPPER PITCH TRIM ACTUATOR ATTACH FITTING/HARDWARE, FOR CORRECT INSTALLATION .............................................02 25 04 032 RELIEF FOR RECENT CHANGE OF SA226 MM, CHAPTER 5, HYDROSTATIC TEST INTERVAL (HTI), FOR P/N 30301100 AND 30300020 FIRE EXTINGUISHER BOTTLES ................................................................04 16 04 033 SPECIAL INSPECTION OF FUSELAGE DRAINS AND INSTALLATION OF ADDITIONAL FUSELAGE DRAINS IN ACCORDANCE WITH M7 ENGINEERING DRAWING, 27K22011 ...................................................................12 07 04 034 LORD MECHANICAL PRODUCTS, SERVICE INFORMATION LETTER, LM827-71-001, CLARIFICATION ON THE ENGINE ISOLATOR INSPECTION CRITERIA ................................................................................................................(R) 0 1 20 06 035 INSPECTION OF AFT SPAR, AT LOWER AFT STEEL ANGLE FOR CORROSION .................................................................................................................04 05 05 036 USE OF THE NAME FAIRCHILD OR M7 AEROSPACE LP ..........................................02 20 07 037 INSPECTION AND REPLACEMENT OF FLIGHT CONTROL CABLE, PULLEY GUARD PIN .............................................................................................................(R) 01 30 14 038 INSPECTION OF UPPER AND LOWER ENGINE ATTACH FITTING BOLTS FOR CORRECT TORQUE .....................................................................................................11 14 08 039 NOT ISSUED ................................................................................................................ .00 00 00 040 COCKPIT HEATED WINDSHIELD (P/N 26-21126 AND 27-19442) DAMAGE REPORT ..................................................................................................................(R) 0 8 31 12 041 INSPECTION OF ENGINE TRUSSES FOR CHAFING BY ANTI-ICE VALVE P/N 319980-13-1 ...................................................................................................................08 26 11 042 APPH SOLENOID VALVES AND HYDRAULIC POWER PACKS ALERT .....................08 03 12 043 DEFECTIVE STANDARD HARDWARE - MS21042 SELF-LOCKING NUTS ................08 03 12 044 NOT ISSUED ................................................................................................................ .00 00 00 045 INSPECT AILERON SPAR WEB AT HINGES FOR CRACKING .............................(R) 09 19 14 046 INSPECT AND REPLACE 27-51000-031 LANDING GEAR ACTUATOR BOLTS .........08 13 13 047 INSPECT HONEYWELL P/N 894568-2 FUEL LINE FOR DAMAGE ......................(R) 12 12 13 048 RECOMMEND REPLACE/REWORK PROPELLER PITCH CONTROL (PPC) ASSEMBLIES PER HONEYWELL SERVICE BULLETIN TPE331-72-2190 .................02 11 14 049 INSPECT HONEYWELL P/N 894382-1/-2/-5/-6 ANTI-ICE TUBE FOR CRACKING OR DAMAGE ....................................................................................................................... 09 19 14 

### SA226 SERVICE LETTER

NO. DESCRIPTION DATE

## SA226 SERIES SERVICE LETTER INDEX

SL INDEX Page 3 of 3 Issued: February 14, 1992 Revised: March 27, 2003 SA226 SERIES

SA226 SERVICE LETTER

NO. DESCRIPTION DATE 050 INSPECTION OF RUDDER FLIGHT CONTROL CABLES ...........................................04 15 15



### April 15, 2015P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421

### Issued: April 15, 2015 226-SL-050 Page 1 of 1 

# SERVICE LETTER SA226 SERIES



## ENGINE CONTROLS

SUBJECT: INSPECTION OF RUDDER FLIGHT CONTROL CABLES

1. EFFECTIVITY : SA226-T, S/N T265, T267 SA226-T(B), S/N T(B)348 SA226-TC, S/N TC277 SA226-AT, S/N AT071, AT072, AT073

2. REASON:
An operator performed an inspection of the rudder control cables under the cockpit fl oor during normal Letter check, and found the left rudder fl ight control cable with extensive damage, such that 5 of the 7 wires were broken.The RH cable was inspected initially using the method described in the SA226 Maintenance Manual (MM), Chapter 27-00-00 and was not identi fi ed as damaged. It was only after further investigation, it was revealed that several strands of some of the wires within the 7x19 cable were broken at the same location as the LH cable. Inspection of these cables is also the subject of AD2011-17-07 and M7 bulletin SA226- 27-072. These cables are life limited to 3,500 hours. This latest failure occurred after only 1500 hours since last replacement.

3. DESCRIPTION:
Immediately perform a detail visual inspection of the LH and RH Rudder fl ight control cables under the fl oor between FS 116.56 and FS 138.56, with speci fi c focus on the cable and the pulley at FS126.06.

4. ACTION:
Perform a one-time inspection within the next 10 fl ight hours or 60 days whichever is less, from the date of this Service Letter.
See SA226 MM, Chapter 27-00-00 for inspection method. Replace any damaged cables. Replacement details can be found in Service Bulletin 226-27-072. Contact M7 Aerospace with all fi ndings at MetroTech@M7Aerospace.com.P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421