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 Bulletin 226-27-080, Inspection of the Elevator Control System Rod End Bearings, Issued: November 5, 2015; Revised: February 23, 2016. This revision removes the NAS43HT4-4 spacers from the elevator control links to quadrant hardware stack-up shown in Figures 1 and 4, and adds to the *Note in Figure 4 to allow use of one NAS43HT4-4 spacer in place of two AN960-416L washers if necessary. Please replace existing Service Bulletin 226-27-080 IR with the attached Service Bulletin and replace revised Chapter 27 Index pages.P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421CHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 1 of 10 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

27-001 02-08-71 Replace Rollers SA226-T, S/N T201-207, (R) 09-18-75 Located Between SA226-AT, S/N AT001-002, Spars with Pulleys SA226-TC, S/N TC201-202. 27-002 04-17-71 Adjustment of Rudder/ SA226-T, S/N T201-209, (R) 09-18-75 Aileron Interconnect SA226-AT, S/N AT001-002, Springs SA226-TC, S/N TC201-202.
27-003 03-15-71 Deice Modi fi cation SA226-T, S/N T201-218, (R) 10-09-75 SA226-AT, S/N AT001-006, SA226-TC, S/N TC201-202.
27-004 03-22-72 Pitch Trim Actuator- SA226-T, S/N T201-999, (R) 05-31-78 Increase in Time SA226-AT, S/N AT001-999, Between Overhauls SA226-TC, S/N TC201-999.
27-005 10-10-72 Rudder Trim Control SA226-T, S/N T201-219, (R) 10-21-75 Rod SA226-AT, S/N AT001-006, SA226-TC, S/N TC201-202. 27-006 06-20-73 Inspection and Repair SA226-T, S/N T201-237, (R) 10-21-75 of Rudder Trailing SA226-AT, S/N AT001-009, Edge Skin SA226-TC, S/N TC201-202.
27-007 03-08-73 Stabilizer Actuator- SA226-T, S/N T201-225, (R) 10-21-75 Replacement to Ensure SA226-AT, S/N AT001-008, Irreversibility SA226-TC, S/N TC201-202. 27-008 07-16-73 Inspection of Rudder SA226-T, S/N T201-234, (R) 10-21-75 Bellcrank for SA226-AT, S/N AT001-009, Hardness SA226-TC, S/N TC201-207.
27-009 09-20-73 Installation of SA226-T, S/N T228-238, (R)10-21-75 Aileron Control SA226-AT, S/N AT009-012, Cable Guard SA226-TC, S/N TC205-207. 27-010 09-18-73 Inspection and SA226-T, S/N T201-238, (R)10-21-75 Adjustment of SA226-AT, S/N AT001-009, Aileron T ab Gap SA226-TC, S/N TC201-207. 27-011 05-31-74 Improved Rudder SA226-T, S/N T201-245, (R)10-21-75 Tab Link Assembly SA226-AT, S/N AT001-015, SA226-TC, S/N TC201-208E.

Issued: February 8, 1971 Revised: May 31, 1978CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

CHAPTER 27 INDEX Page 2 of 10 27-012 07-31-84 RESCINDED
27-013 07-31-84 RESCINDED 27-014 11-12-73 Aileron Balance SA226-T, S/N T201-241, (R) 10-21-75 Weight Attachment SA226-AT, S/N AT001-014, SA226-TC, S/N TC201-207. A27-015 08-23-74 Horizontal Stabilizers - SA226-AT, S/N AT001-024, (R) 10-22-75 Spar Cracks-Inspection SA226-TC,S/N TC201-211EE

. & Repair.
A27-016 08-23-74 Horizontal Stabilizers - SA226-T, S/N T201-248. (R) 10-22-75 Spar Cracks-Inspection & Repair. 27-017 06-25-75 Improved Stabilizer SA226-T, S/N T201-251, (R)10-22-75 Trim Actuator Availability SA226-AT, S/N AT001-033, SA226-TC, S/N TC201-212.
27-018 11-11-74 Modi fi cation of SA226-T, S/N T201-250, (R) 10-22-75 Aileron Trim Tab SA226-AT, S/N AT001-026, Leading Edge SA226-TC, S/N TC201- 211EEE. 27-019 03-13-75 Replace Trim Limit SA226-T, S/N T249-250. (R) 10-22-75 Switch Mounting Bracket & Rod.

27-020 01-14-76 Installation of SA226-T, S/N T201-256, Oilite Bearings on SA226-AT, S/N AT001-043, Rudder Pedal SA226-TC, S/N TC201-216. 27-021 11-11-76 Flight Controls- SA226-T, S/N T201-271, Rudder and Tab SA226-AT, S/N AT001-051, SA226-TC, S/N TC201-222.
27-022 01-05-79 Installation of Cable SA226-T, S/N T201-290, (R) 01-21-82 Guard & Retainer SA226-AT, S/N AT001-066, SA226-TC, S/N TC201-255. 27-023 11-13-79 Elevator/Horizontal SA226-T, S/N T201-302, Stabilizer Support Mod. SA226-AT, S/N AT001-070, SA226-TC, S/N TC201-286.
Issued: February 8, 1971 Revised: July 31, 1984CHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 3 of 10 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

A27-024 11-13-79 Inspection of SAS Servo SA226-T, S/N T201-291 except T276, SA226-AT, S/N AT001-073, SA226-TC, S/N TC201-314. A27-025 03-21-80 Inspection of Aileron SA226-T(B), S/N T(B)292- Control Cable Routing 329, SA226-AT, S/N AT067-074, SA226-TC, S/N TC256-325. 27-026 05-09-80 Installation - Adjust- SA226-T(B), S/N T(B)276, table Angle of Attack T(B) 292-298, 300-311. (AOA) Transmitter Bracket 27-027 07-17-80 Rudder Cable SA226-T, S/N T201-275, Attaching Hardware- T277-291, Inspect and Replace SA226-T(B), S/N T(B)276, T(B)292-999, SA226-AT, S/N AT001-999, SA226-TC, S/N TC201-999. A27-028 12-11-80 Inspection of Yaw SA226-T, S/N T201-275, Damper and SAS T277-291, Servos SA226-T(B), S/N T(B)276, T(B)292-391.

27-029 04-23-81 Inspection of Elevator All SA226 Series Aircraft. Mass Balance Weights

27-030 06-03-81 Aileron Balance SA226-T(B), S/N T(B)394, Requirements T(B)397, 400, 403, 405, 407, and 414, SA226-TC, S/N TC401, TC413, 415, and 418. 27-031 07-08-81 Elevator Return SA226-AT, S/N AT001-419, Spring and Attaching SA226-TC, S/N TC201-419. Bolts Inspection 27-032 09-14-81 Relocation of SA226-AT, S/N AT001-999, (R) 01-19-83 Elevator Down Spring SA226-TC, S/N TC201-999.
A27-033 12-03-82 Removal of Second SA226-T(B), S/N T(B)276, (R) 01-06-83 Clutch from CONRAC T(B)292-999. SAS Servo Issued: February 8, 1971 Revised: January 19, 1983CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

CHAPTER 27 INDEX Page 4 of 10 27-034 03-20-84 Rudder Gust Lock SA226-T, S/N T201-291, Rework except T-276, SA226-T(B), S/N T(B)276 T(B)292-417, SA226-AT, S/N AT001-074 except AT070, SA226-TC, S/N TC201-419. 27-035 12-13-83 Rudder Torque Tube SA226-T, S/N T201-275, (R)09-19-84 T277-291, SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-036 03-20-84 Improved Flap Control SA226-T, S/N T201-275, Handle Bracket T277-282, SA226-T(B), S/N T(B)298- T(B)417, SA226-AT, S/N AT001-062, AT071-074, SA226-TC, S/N TC201-246, TC280-419. 27-037 02-15-85 CONRAC SAS System SA226-T(B), S/N T(B)276, (R) 09-16-85 Inspection and T(B)292-417 (R) 11-04-85 Recalibration SA226-T, S/N T201-275, (R) 04-15-88 CATEGORY III T277-291* (R) 02-10-93 SA226-AT, S/N AT001-074* (R) 05-06-96 SA226-TC, S/N TC201-419* (R) 07-24-08 * Aircraft modi fi ed by S.T.C (R) 06-12-13 SA4725SW. 27-038 02-15-85 Rosemount SAS System SA226-T, S/N T201-275, (R)09-16-85 Inspection and T277-291*, (R)11-04-85 Recalibration SA226-AT, S/N AT001-074*, (R)01-07-88 CATEGORY III SA226-TC, S/N TC201- (R)01-16-90 419*, (R)07-26-99 *Except aircraft modi fi ed by S.T.C SA4725SW.

Issued: February 8, 1971 Revised: June 12, 2013CHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 5 of 10 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

27-039 03-20-85 Rework or Replacement SA226-T, S/N T201-275, (R)10-16-85 of 27-71016 Bellcrank T277-291, (R)12-09-86 Assembly SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-040 07-31-85 Rudder Pedal Bellcrank SA226-T, S/N T201-275, Hardware Inspection T277-291. SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-041 10-21-85 Alternate Elevator SA226-T, S/N T201-275, (R) 02-18-86 Gust Lock T277-291. SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-042 06-17-86 Pitch Trim Actuator SA226-T, S/N T201-275, (R) 10-31-86 Replacement T277-291, (R) 03-24-87 Category III SA226-T(B), S/N T(B)276, T(B)292-417. SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-043 03-05-87 Improved SAS Servo SA226-T(B), S/N T(B)276, Idle Control Assembly T(B)292-417. Category III 27-044 06-08-87 Aileron Trim Cable SA226-T, S/N T201-275, Drum Guard Pin T277-291, Category III SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-045 06-18-87 Rudder Bellcrank SA226-T, S/N T201-275, Improvements T277-291, Category III SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. Issued: February 8, 1971 Revised: June 18, 1987CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

CHAPTER 27 INDEX Page 6 of 10 27-046 02-19-88 Aileron Bellcrank SA226-T, S/N T201-275, Housing Modi fi cation T277-291, Category III SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-047 01-27-88 Rudder Hinge Bolts- SA226-T, S/N T249-275, Improved Access T277-291, Category III SA226,T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-048 07-26-89 Elevator Control SA226-AT, S/N AT001-074, Cable Hardware SA226-TC, S/N TC201-419. Category III
27-049 01-10-90 CANCELLED 27-050 01-22-90 Elevator Torque Tube SA226-T, S/N T258-275, Category III T277-291, SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-051 05-19-94 Rudder Bellcrank Hinge SA226-T, S/N T201-275, Assembly Rework T277-291, Category III SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT025-074, SA226-TC, S/N TC201-413, TC418, 419. 27-052 07-23-93 Replacement of Turn SA226-T, S/N T201-275, and Slip Indicator T277-291, SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT001-074, SA226-TC, S/N TC201-419. 27-053 12-15-94 Increased Service Life All SA226 Series Airplanes (R) 01-05-96 of 27-42030 Rudder Bellcrank Issued: February 8, 1971 Revised: January 5, 1996CHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 7 of 10 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

27-054 05-22-95 Rudder Torque Tube SA226-T, S/N T258-275, Drain Hole T277-291, SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT043-074, SA226-TC, S/N TC222-419. 27-055 08-09-95 Rudder Control Lock Weldment SA226-T, S/N T258-275, and Bellcrank Inspection- T277-291, Optional Improved Strength SA226-T(B), S/N T(B)276, Rudder Torque Tube, Control T(B)292-417, Lock Weldment and Aluminum SA226-AT, S/N AT043-074, Bellcrank Installation SA226-TC, S/N TC222-419.
27-056 00-00-00 NOT ISSUED 27-057 09-08-95 Rudder Trim Tab Actuator All SA226 Series Airplanes Decal 27-058 05-15-96 Rework of UP/DOWN Elevator All SA226 Series Airplanes Quadrant Stops and LH/RH Rudder Bellcrank Stops
27-059 00-00-00 NOT ISSUED 27-060 12-11-96 Control Column Roller Bearing All SA226 Series Airplanes (R) 02-24-97 and Elevator Rod End Bearing (R) 12-05-14 Inspection/Replacement
27-061 06-16-97 Control Column Pivot All SA226 Series Airplanes Improvement 27-062 11-18-98 Installation of Simmonds All SA226 Series Airplanes Precision P/N DL5040M5 with Barber Colman, P/N and/or DL5040M6 Pitch Trim 27-19008-001/-002 Pitch Actuator (PTA) Trim Actuator Installed. 27-063 05-11-99 Installation of P/N All SA226 Series Airplanes (R) 12-27-99 DL5040M8, Simmonds with P/N 27-19008-001/-002/ (R) 11-18-02 Precision Pitch Trim -004/-005/-006/-007 Bar Actuator (PTA) ber-Colman PTA Installed.

Issued: February 8, 1971 Revised: December 5, 2014CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

CHAPTER 27 INDEX Page 8 of 10 Issued: February 8, 1971 Revised: September 04, 2014 27-064 03-08-99 Installation of All SA226 Series Airplanes 27-19008-006/-007 with P/N 27-19008-001/-002/ Barber-Colman Pitch Trim -004/-005 Barber-Colman Actuator (PTA Installed. PTA
27-065 12-05-00 Installation of Fairleads All SA226 Series AT and TC at F.S. 174.06 Airplanes 27-066 09-29-03 Life Limit for Rudder Gust All SA226 Series Airplanes Lock Assembly, Part Number 27-70066-001, of 5000 Hours 27-067 04-02-04 Inspection of 26-72003 Rudder All SA226 Series Airplanes Pedals for cracks
27-068 00-00-00 NOT ISSUED
27-069 00-00-00 NOT ISSUED 27-070 09-19-08 Gravel Guard Installation All SA226 Series Airplanes 27-071 04-28-09 Pilot's and Copilot's Control All SA226 Series Airplanes Column Access Panels Modi fi cation 27-072 06-27-11 Flight Control Cable SA226-T, S/N T265, T267 Replacement SA226-T(B), S/N T(B)348 SA226-TC, S/N TC277 SA226-AT, S/N AT071, AT072, AT073 27-073 06-10-11 Inspection and Repair / All SA226 Series Airplanes (R) 09-06-11 Replacement of Pitch Trim (R) 10-14-11 Actuator Fuselage Fittings 27-074 06-06-13 Inspection and Lubrication of All SA226 Series Airplanes (R) 09-30-13 the Aileron Control Cable (R) 10-23-13 Chain in the Pilot's and Co- Pilot's Control Columns 27-075 09-04-14 Inspection/Replacement of the All SA226 Series Airplanes Aileron Control System Rod End BearingsCHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 9 of 10 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

Issued: February 8, 1971 Revised: February 23, 2016 27-076 09-04-14 Inspection of the Aileron Link All SA226 Series Airplanes Rod, Bellcrank, and Aileron Hinge Bracket for Damage 27-077 08-18-14 Inspection/Repair of Wiring All SA226 Series Airplanes Harnesses in the Vertical Stabilizer 27-078 10-08-15 Inspection of Cockpit Control All SA226 Series Airplanes Column Horizontal Tube for Cracks 27-079 04-23-15 Inspection of Rudder Bellcrank All SA226 Series Airplanes (R) 09-21-15 (R) 10-12-15 27-080 11-05-15 Inspection of the Elevator All SA226 Series Airplanes (R) 02-23-16 Control System Rod End BearingsCHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

CHAPTER 27 INDEX Page 10 of 10 Issued: February 8, 1971 Revised: February 23, 2016 INTENTIONALLY LEFT BLANK226-27-080 R1 Page 1 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 Flight Controls Inspection of the Elevator Control System Rod End Bearings 1. PLANNING INFORMATION A. Effectivity: All SA226 Series Airplanes. B. Reason: An operator reported a crew was performing fl ight control checks before take-off and noted something was wrong with the elevator control. Review of the elevator control system by maintenance personnel found the control link assembly located between the elevator torque tube and the elevator quadrant broken. This revision removes the NAS43HT4-4 spacers from the elevator control links to quadrant hardware stack-up shown in Figures 1 and 4, and adds to the *Note in Figure 4 to allow use of one NAS43HT4-4 spacer in place of two AN960-416L washers if necessary. C. Description: Inspect both control link assemblies between the elevator torque tubes and the elevator quadrant for frozen (stiff, hard to move) bearings, or broken/cracked links (rod ends). Replace rod ends if required and inspect mating quadrant for any signs of related damage. Otherwise, lubricate bearings, reinstall elevator control link assemblies, check system rigging/freeplay, and repeat inspection at next interval speci fi ed below. D. Compliance: Mandatory. 1) If fl ight crew reports abnormally high resistance when operating the elevators, perform Step 2.A. INSPECTION OF ELEVATOR CONTROL LINKS - INSTALLED prior to next fl ight. 2) For reasons other than 1.D.1), at the next zone related Phase or Letter Check inspection or next 600 fl ight hours (but no later than 6 calendar months), whichever occurs later, perform Step 2.B. INSPECTION OF ELEVATOR CONTROL LINKS - REMOVED. 3) Continue to repeat inspect elevator control link assemblies IAW Step 2.B. INSPECTION OF ELEVATOR CONTROL LINKS - REMOVED at both locations (1 per elevator). Repeat on an annual basis after compliance with applicable Step 1.D.1) or 1.D.2) threshold inspection. 4) Continue to repeat lubrication of rod end bearings (male and female) on both elevator control link assemblies IAW Step 2.E every 3 to 6 months, concurrent with Step 1.D.3) when possible. For aircraft located in climates conducive to corrosion, lubricate using the shorter interval. For aircraft with the previous lubricant application still present, it is permissible to use the longer interval. Adjust this 3 to 6 month interval as required to maintain lubricant on bearings at all times.226-27-080 R1 Page 2 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 5) The repeat inspection and lubrication tasks will be added to the Phase and Letter Check programs. E. Approval: FAA Approved for Engineering Design. F. Manpower: M7 Aerospace estimates 2 manhours to perform the inspect/torque check and a further 4 hours for rod end bearing replacement and rigging checks. This estimate is for direct labor only. G. Material - Cost and Availability: Contact M7 Aerospace Spares/Sales Department for Cost and Availability. See Table 1 for listing. H. Tooling-Price and Availability: Refer to the SA226 Maintenance Manual (MM) for required tooling for rigging of control system. I. Weight and Balance: None. The weight of the rod ends is comparable. NOTE : It is recommended the aircraft operating weight be re-established after incorporating 20 service bulletins classi fi ed as having negligible impact on aircraft weight and balance. This recommendation is derived from data provided in FAA Advisory Circular 120-27. J. Reference: M-5813 M7 Aerospace White Paper; M7 Aerospace SDR Review Item; SA226 Maintenance Manual, 27-00-00; SA226 Illustrated Parts Catalog (IPC) 27-30-04, Figure 1; M7 Aerospace Drawing 27-43000 (latest FAA approved revision). NOTE: References are for manufacturers’ use only. K. Other Publications Affected: SA226 Illustrated Parts Catalog (IPC) 27-30-04; SA226 Maintenance Manual (MM) 27-30-00; SA226 Phase and Letter Check Inspection Manuals.226-27-080 R1 Page 3 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 2. ACCOMPLISHMENT INSTRUCTIONS A. Inspection of Elevator Control Links - Installed: Refer to Figure 1 for location of the elevator control link rod end bearings to be checked. The subject rod end bearings are directly attached to the elevator quadrant and to the elevator torque tube at the inboard end of each elevator. Check each control link assembly as follows: 1) Remove panel 808 (see Figure 2) on the RH side of the vertical stabilizer to gain access to the elevator quadrant. 2) Ensure both rod ends on both elevator control link assemblies are intact. 3) Physically rotate the control link assemblies about their longitudinal axis in situ by hand. Do not remove any hardware at this stage. 4) If the control link assemblies rotate freely under hand force: a) Hand lube the elevator control link rod end bearings with MIL-PRF-81322 grease with link installed. Work in the grease by rotating link. b) Reinstall panel 808 and return aircraft to service. c) Perform procedures in step 2.B at the next zone related Phase or Letter Check inspection or next 600 fl ight hours (but no later than 6 calendar months), whichever occurs later. 5) If the control link does not rotate freely under hand force, or if link feels very stiff (slight movement only), proceed with Step 2.B. B. Inspection of Elevator Control Links - Removed: 1) Disconnect electrical power from the aircraft and disconnect main batteries. Tag out circuit breakers and switches to prevent injury to personnel or damage to the aircraft. 2) Placard the cockpit controls of the elevator and trim system "DO NOT OPERATE/ MOVE". 3) Unless access has already been attained (Step 2.A.1) above), remove panel 808 (see Figure 2) on the RH side of the vertical stabilizer to gain access to the elevator quadrant. 4) Locate the elevator control link assemblies on each side of the quadrant. Each control link assembly consists of a male rod end (HM-4M) attached to elevator quadrant and a female rod end (HF-4M) attached to elevator torque tube, secured with a nut (AN316-C4R). Both control link assemblies must be checked. 5) Remove both elevator control link assemblies from the vertical stabilizer. 6) Initially by applying fi nger pressure, determine if the spherical bearing in each226-27-080 R1 Page 4 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 control link rod end can be rotated in-plane within the outer race of the rod end bearing (see Figure 3 for in-plane rotation illustration). a) When performing the in-plane rotation check, inspect rod end bearings (male and female) for corrosion and general condition. b) Only during the initial compliance with Step 2.B. Inspection of Elevator Control Links - Removed, perform a magnetic particle inspection or liquid penetrant inspection to check for cracks on male rod end exposed threads, taking care to avoid any penetrant fl uid entering the bearing race area. Repetitive magnetic particle or liquid penetrant inspections of the male rod ends are not required during the repeat inspections called for in Step 1.D.3). If for any reason the male rod end threads at the nut appear to be damaged, the nut must be rotated to expose the threads and threads under the nut inspected. c) The bearing should move smoothly and freely without any binding or sticking. If not, perform Step 2.C. Torque Check Procedure to determine if the bearing must be replaced or may be reinstalled. d) Replace any rod end that fails the torque check or is found to have corrosion or other damage. Replace affected rod end(s) IAW Step 2.D. (see Step 3 Material Listing for parts). e) If the rod end bearings are not found to have corrosion or other damage, rotate freely and smoothly without any sloppiness, the control link assemblies may be reinstalled. Proceed to Step 2.E. C. Torque Check Procedure: 1) This method simply inserts a standard 1/4" diameter bolt through the rod end to be checked. The bolt must be of suf fi cient grip length to allow installation of the NAS1149* washer (of 0.032 min thickness) under the head, and nut, MS21042L4, with one or two threads showing past the end of the nut. 2) While holding the bolt head, lightly torque the nut to approximately 30-50 in-lbs. This provides adequate clamping support to measure the breakout friction of the rod end bearing. 3) Obtain a torque wrench with a reading tolerance of +/- 0.5 in-lbs or better. Ensure the wrench is in calibration and is capable of measuring 4 to 7 in-lbs torque.4) The torque wrench is then reset and applied to the bolt head only, rotating inplane to measure the breakout torque of the bearing. A torque greater than 5 in-lbs indicates the rod end bearing needs replacement. Values less than 5 in-lbs permit the rod end bearing to remain in service. a) Torque greater than 5 in-lbs - replace the affected rod end IAW Step 2.D. b) Torque less than or equal to 5 in-lbs - return to relevant Step 2.B. to complete inspection and in-plane rotation check of remaining rod end bearings.226-27-080 R1 Page 5 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 D. Link Rod End Replacement: 1) Whether the existing bearings are "frozen" or do not meet the torque requirement, or by choice of the operator, the rod end should be removed and replaced with a new rod end (see Step 3. Material Listing). 2) Prior to disassembly of a control link assembly, note orientation of rod ends and length of link assembly. Either using witness marks or some form of marking, note orientation with respect to the elevator quadrant and elevator torque tube as the new rod end must be installed in the same orientation and link assembly must have same length as removed. These features must be maintained to avoid any interference with other parts of the system. 3) Discard the old rod end and install the new rod end. Reassemble the system using the witness marks or other orientation marking as noted above. Torque the AN316-C4R jam nut which secures the male and female rod ends to each other (Ref AMM 20-10-00). E. Hand lube the elevator control link rod end bearings with MIL-PRF-81322 grease. Install elevator control links to elevator quadrant and elevator torque tubes (see Figures 4 and 5 for correct stack-up, and Step 3. Material Listing for part numbers). F. Visually check the installation for correct orientation, positioning, and location of parts. Correct any noted discrepancies (See Figures 4 and 5). G. Restore all systems disturbed by the steps above to perform this inspection/replacement. Check elevator rigging and free play IAW MM section 27-00-00. H. Remove warning placards from cockpit controls of the elevator and trim system. I. Perform several elevator operation cycles while looking for clearance between all parts and proper operation. Correct any noted discrepancies. J. Reinstall panel 808. K. Complete aircraft records in accordance with 14 CFR 43.9. L. Complete and return service bulletin Compliance Form to M7 Aerospace Technical Publications Department. Email: MetroTech@M7Aerospace.com.226-27-080 R1 Page 6 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 3. MATERIAL LISTING

Location / Item Part Number Alternate P/N Quantity At Elevator Quadrant: Control Link Rod End, Male HM-4M MM-4M-18 § 2 Bolt NAS464P4-38 ǂ NAS6204-38D ǂ 1 Washer AN960-416L ǂ 2 * Spacer NAS43HT4-4 ǂ 2 Nut AN310-4 ǂ 1 Cotter Pin (Use with HM-4M) MS24665-153 ǂ 1 On Elevator Control Link: Jam Nut AN316-C4R ǂ 2 At Elevator Torque Tubes: Control Link Rod End, Female HF-4M MW-4M-17 § 2 Bolt NAS464P4-14 ǂ NAS6204-14D ǂ 2 Washer AN960-416 ǂ 4 Washer AN960-416L ǂ A/R ** Spacer, (INBD) NAS43HT4-5 ǂ 2 Spacer, (OUTBD) NAS43HT4-10 ǂ 2 Nut AN310-4 ǂ 2 Cotter Pin MS24665-153 ǂ 2 On Rod End Bearings: Grease MIL-PRF-81322 ǂ ¤ A/R § M7 Aerospace Sales Support item: M7-Sales@M7Aero.com ǂ Customer Furnished Material. * Extra washer may be added under nut to ensure proper torque on nut and cotter pin installation are met. ** Optional, 1 or 2 washers may be installed as required for proper bearing clamp-up or nut/cotter pin installation. ¤ MIL-PRF-23827 may be used as an alternate to MIL-PRF-81322. TABLE 1 MATERIAL LISTING FOR CONTROL LINKS / ATTACHMENT HARDWARE (SEE FIGURES 4 AND 5 FOR PROPER STACK-UP)226-27-080 R1 Page 7 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 ELEVATOR CONTROL LINK ASSEMBLIES (EACH ASSEMBLY CONSISTS OF 1 MALE ROD END, 1 FEMALE ROD END AND 1 JAM NUT)

ELEVATOR QUADRANT

ELEVATOR TORQUE TUBE 6B2708001R1

FIGURE 1 LOCATOR - ELEVATOR CONTROL LINKS226-27-080 R1 Page 8 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 2 ELEVATOR QUADRANT ACCESS PANEL 808 

### 808

6B2708002226-27-080 R1 Page 9 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 3 IN-PLANE ROTATION OF ROD END BEARING WITHIN RACE 6B2708003226-27-080 R1 Page 10 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 4 CONTROL LINK ATTACHMENT AT QUADRANT MS24665-153 COTTER PIN

AN310-4 NUT AN960-416L WASHER *

AN960-416L WASHER *

NAS464P4-38 BOLT ** ELEVATOR QUADRANT HM-4M BEARING **

HM-4M BEARING **

* AN EXTRA WASHER MAY BE ADDED UNDER NUT AND/OR HEAD OF BOLT TO ENSURE PROPER TORQUE ON NUT AND COTTER PIN INSTALLATION ARE MET. IT IS PERMISSIBLE TO USE ONE NAS43HT4-4 SPACER IN PLACE OF TWO AN960-416L WASHERS.

6B2708004R1 ** (SEE 3. MATERIAL LISTING FOR ALTERNATE P/N) EXISTING BUSHING (NAS77) EXISTING BUSHING (NAS77)226-27-080 R1 Page 11 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 5 CONTROL LINK ATTACHMENT TO ELEVATOR TORQUE TUBE 

### AN960-416L WASHER (OPTIONAL INSTALLATION OF 1 OR 2

WASHERS, (2PL) AS REQUIRED FOR PROPER BEARING CLAMP-UP AND NUT/COTTER PIN INSTALLATION)

AN960-416 WASHER

HF-4M ROD END * NAS43HT4-5 SPACER AN960-416 WASHER NAS464P4-14 BOLT *

AN310-4 NUT MS24665-153 COTTER PIN

NAS43HT4-10 SPACER

6B2708005


### * (SEE 3. MATERIAL LISTING FOR ALTERNATE P/N)226-27-080 R1 Page 12 of 12 

# SERVICE BULLETIN SA226 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 INTENTIONALLY LEFT BLANK

### SERVICE BULLETIN COMPLIANCE FORM

226-27-080 R1

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