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 identifi 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 26 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 25 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 24 03

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 03

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) 01 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) 08 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, 2015
P.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 identifi 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 specifi 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