### Issued: June 27, 2011 226-27-072 Page 1 of 8 

# SERVICE BULLETIN SA226 SERIES



## FLIGHT CONTROLS Flight Control Cable Replacement 1. PLANNING INFORMATION A. 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 B. Reason: Safety improvement to prevent premature cable failure. Additional stress is exerted on primary flight control cables that have been re-routed from standard configuration to accommodate belly-mounted camera installations. C. Description:Replace all elevator, rudder, aileron, and aileron-to-rudder interconnect primary control cables as identified in step 2.C., or 2.D., or 2.E. every 3500 hours TIS. The existing 10000 hour time in service (TIS) life limit for all other cables per AD 87-02-02 remains in effect. D. Compliance: Highly Recommended A reduced life limit per Step 2.B. is placed against particular control cables. M7 Aerospace recommends a one time check of flight control cable tension between 50 flight hours and 200 flight hours after installing new cable(s) due to cable stretch and/ or thermal variances within aircraft operating area. E. Approval: FAA Approved for Engineering Design. F. Manpower: Individual aircraft may vary. It is recommended that operators obtain an estimate from their nearest M7 Aerospace authorized Service Facility/Maintenance Department.

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# SERVICE BULLETIN SA226 SERIES

G. Material – Cost and Availability:Contact your nearest M7 Aerospace authorized Service Facility/Maintenance Department. It is recommended that operators notify M7 Aerospace/Distributor 45 days prior to new cable(s) being required to accommodate manufacturing schedules. H. Tooling – Price and Availability: Kit, Swage, Control Cable P/N AT520JK Kit, Pull Test, Control Cable P/N AT520CTK Contact M7 Aerospace for price and availability. I. Weight and Balance: Weight and Balance unaffected. J. References: Swearingen Aviation Corporation drawing 27-13090, Rev B and EO's C-1, C-2A, C-3, C-4, C-5, C-6, and C-7 (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13150, Rev A (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13219, Rev IR and EO's A-1 and A-2 (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13216, Rev IR and EO's A-1 and A-2A (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13300, Rev IR and EO's A-1, A-2, A-3, A-4, and A-5 (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13242, Rev IR and EO's A-1 A-2, A-3, A-4, A-5, A-6, A-7, and A-8 (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13233, Rev IR and EO A-1 (or latest FAA approved revision). Swearingen Aviation Corporation drawing 27-13181, Rev IR and EO A-1 (or latest FAA approved revision). NOTE: References are for manufacturer’s use only. K. Other Publications Affected: SA226 Maintenance Manual. SA226 Illustrated Parts Catalog.

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# SERVICE BULLETIN SA226 SERIES

2. ACCOMPLISHMENT INSTRUCTIONS A. Disconnect electrical power from the aircraft. Turn off main batteries. Disconnect GPU. Tag out circuit breakers and battery switches to prevent injury to personnel or damage to the aircraft. B. Time limits have been revised for control cables installed in aircraft listed in the effectivity section of this service bulletin. For the specific cables identified in step 2.C., 2.D., and 2.E., the following Table 1 intervals must be followed.



## TABLE 1 d e r i u q e R n o i t c A e m i T e c n a i l p m o C l a i t i n I l a v r e t n I e v i t i t e p e R

o t l a u q e r o n a h t s s e l s e l b a c r o F

. s e l b a c e c a l p e r , S I T s r u o h 0 0 5 3 s r u o h 0 5 1 r o S I T s r u o h 0 0 5 3 y B s i h t f o e t a d e v i t c e f f e e h t m o r f S I T s r u c c o r e v e h c i h w , n i t e l l u b e c i v r e s

. r e t a l S I T s r u o h 0 0 5 3 y r e v E

. r e t f a e r e h t

o t l a u q e r o n a h t s s e l s e l b a c r o F n a h t r e t a e r g t u b , S I T s r u o h 0 0 0 5

. s e l b a c e c a l p e r , S I T s r u o h 0 0 5 3 e h t m o r f S I T s r u o h 0 5 1 n i h t i W e c i v r e s s i h t f o e t a d e v i t c e f f e

. n i t e l l u b S I T s r u o h 0 0 5 3 y r e v E

. r e t f a e r e h t

0 0 0 5 n a h t r e t a e r g s e l b a c r o F

. s e l b a c e c a l p e r , S I T s r u o h e h t m o r f S I T s r u o h 0 5 n i h t i W e c i v r e s s i h t f o e t a d e v i t c e f f e

. n i t e l l u b S I T s r u o h 0 0 5 3 y r e v E

. r e t f a e r e h t

0 0 0 6 n a h t r e t a e r g s e l b a c r o F

, S I T s r u o h f i e c a l p e r , s e l b a c t c e p s n i ) i (

. d n u o f e r a s e i c n e i c i f e d

. s e l b a c e c a l p e R ) i i ( e h t m o r f S I T s r u o h 0 1 n i h t i W ) i ( e c i v r e s s i h t f o e t a d e v i t c e f f e r e h t r u f o t r o i r p e c a l p e r ; n i t e l l u b

. d n u o f e r a s e i c n e i c i f e d f i t h g i l f e h t m o r f S I T s r u o h 0 5 n i h t i W ) i i ( e c i v r e s s i h t f o e t a d e v i t c e f f e

. n i t e l l u b e n o N ) i (

S I T s r u o h 0 0 5 3 y r e v E ) i i (

. r e t f a e r e h t

n o i s n e t e l b a c l o r t n o c t h g i l f k c e h C

, l a u n a M e c n a n e t n i a M 6 2 2 A S r e p

. 0 0

- 0 0

- 7 2 r e t p a h C r e t f a s r u o h 0 0 2 d n a 0 5 n e e w t e B

. e l b a c l o r t n o c w e n y n a g n i l l a t s n i . e n o N

### Issued: June27, 2011 226-27-072 Page 4 of 8 

# SERVICE BULLETIN SA226 SERIES

All other flight control cables not affected by this service bulletin are to be periodically inspected or replaced in accordance with AD87-02-02. Ten (10) hour inspection procedure for cables greater than 6,000 hours: (1) Release tension on each cable. (2) Pass a cloth along the entire length of each cable to clean the cable for visual inspection and to detect broken wires.Visual inspect the entire cable length for broken wires and general condition. Rotate the cable 180° where the cable contacts any pulley, fairlead or pressure seal. Birdcage cable (slightly untwist), and visually inspect for wear, broken wires and for general condition 24 inches either side of contact area when the control cables are in the neutral position. (3) Prior to further flight replace, with a new cable, any cable found to have any one of the following conditions: (a) More than three (3) broken wires within any one-foot section of the cable (any wire worn more than one half of its diameter is considered broken), or (b) More than one (1) one-foot section with broken wires, or (c) Cables whose total number of broken wires exceeds the total number of feet in length of that cable, or (d) More than six (6) wires worn not more than one-half of the wire diameter in any one-inch length of cable. (4) In cases where discrepant cables have been found, prior to further flight, inspect the condition of the associated fairleads / pressure seals or pulleys in accordance with SA226 Maintenance Manual, Chapter 27-00-00. Replace any unserviceable components as required. (5) Prior to returning the airplane to service, reset cable tensions, rerig primary flight control systems, reaasemble the airplane, and verify proper control systems operation in accordance with SA226 Maintenance Manual, Chapter 27-00-00. Make appropriate maintenance record entry per step 2.I. C. Replace flight control cables as follows for aircraft serial numbers. T265, T267, T(B)348 (Camera Mod, Fwd, ~ FS 116 to FS 261): NOTE: Refer to general instructions on removal/installation of flight control cables per SA226 Maintenance manual chapter 27-00-00.The following steps refer to figure numbers which are found in the respective maintenance manual chapters. NOTE: Refer to Kit Drawing 27K70004 for further installation details.

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# SERVICE BULLETIN SA226 SERIES

(1) Remove and replace Pilot and/or Copilot aileron cables 3 / 4 (Ref. Figures 202 and 203) between FS 98.56 (Control Wheel) and FS 225.78 (Aileron Interconnect Bellcrank) per SA226 Maintenance Manual Chapter 27-10-01. (2) Remove and replace Pilot and/or Copilot rudder/aileron interconnect cable 2 (Ref. Figure 1B) between FS 225.78 (from spring assembly aft attach point) and FS 243.19 (rudder trim tab cable connecting link) per SA226 Maintenance Manual Chapter 27-20-01. (3) Remove and replace Pilot and/or Copilot aileron trim tab cable (Ref. Figure 1) between FS 126.06 (Pedestal) and ~ FS 216 (Wing Rear Spar) per SA226 Maintenance Manual Chapter 27-10-04. (4) Remove and replace Pilot and/or Copilot rudder cables (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-01.(5) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05. (6) Remove and replace Pilot and/or Copilot elevator cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-30-01. NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for turnbuckle safety springs (if installed) or turnbuckle safety wiring. (7) Set rigging tension for SA226-T aircraft per SA226 Maintenance Manual chapter 27-00-00, Figure 207. D. Replace flight control cables as follows for aircraft serial numbers. AT071, AT072, and AT073 (Camera Mod, Fwd, ~ F.S. 174 to 455): NOTE: Refer to general instructions on removal/installation of flight control cables per SA226 Maintenance manual chapter 27-00-00.The following steps refer to figure numbers which are found in the respective maintenance manual chapters. NOTE: Refer to Kit Drawing 27K70004 for further installation details. (1) Remove and replace Pilot and/or Copilot aileron cables 3 / 4 between FS 174.06 (Control Wheel) and FS 332.27 (Aileron Interconnect bellcrank) per SA226 Maintenance Manual Chapter 27-10-01. (2) Remove and replace Pilot and/or Copilot rudder/aileron interconnect cable 2 (Ref. Figure 1B) between FS 324.77 (from spring assembly aft attach point) and FS 347.27 (rudder trim tab cable connecting link) per SA226 Maintenance Manual Chapter 27-20-01.

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# SERVICE BULLETIN SA226 SERIES

(3) Remove and replace Pilot and/or Copilot aileron trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-10-04. (4) Remove and replace Pilot and/or Copilot rudder cables (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-01.(5) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05. (6) Remove and replace Pilot and/or Copilot elevator cables 1 and 2 (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-30-01. NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for turnbuckle safety springs (if installed) or turnbuckle safety wiring. (7) Set rigging tension for SA226-AT aircraft per SA226 Maintenance Manual chapter 27-00-00, Figure 209. E. Replace flight control cables as follows for aircraft serial number TC277 (Camera Mod, Aft, ~ F.S. 347 to 455): NOTE: Refer to general instructions on removal/installation of flight control cables per SA226 Maintenance manual chapter 27-00-00.The following steps refer to figure numbers which are found in the respective maintenance manual chapters. NOTE: Refer to Kit Drawing 27K70004 for further installation details. (1) Remove and replace Pilot and/or Copilot rudder cable 3 (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-01.(2) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05.(3) Remove and replace Pilot and/or Copilot elevator cable 1 per SA226 Maintenance Manual Chapter 27-30-01. NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for turnbuckle safety springs (if installed) or turnbuckle safety wiring. (4) Set rigging tension for SA226-TC aircraft per SA226 Maintenance Manual chapter 27-00-00, Figure 209. F. Remove tags from battery switches and circuit breakers pulled in step 2.A. and reset. Reconnect GPU to aircraft. G. Perform Adjustment/Test of primary flight controls per applicable sections of SA226 Maintenance Manual, chapter 27.

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# SERVICE BULLETIN SA226 SERIES

H. Return aircraft to serviceable condition. I. Complete aircraft records according to 14 CFR 43.9. J. Complete and mail Service Bulletin compliance form to M7 Aerospace Technical Publications. 3. MATERIAL LISTING For Aircraft Serial Numbers T265, T267, and T(B)348. NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION 27-13181-001SB 1 Aileron Control Cable, 27-13181-001 Scrap Cable 3 / 4, Pilot 27-13181-007SB 1 Aileron Control Cable, 27-13181-007 Scrap Cable 3 / 4, Copilot 27-13181-015SB 1 Aileron Trim Tab 27-13181-015 Scrap Control Cable 27-13181-003SB 2 Rudder Control Cable 27-13181-003 Scrap 27-13181-009SB 2 Rudder/Aileron 27-13181-009 Scrap Interconnect Cable 2 27-13181-019SB 1 Rudder Trim Tab 27-13181-019 Scrap Control Cable 27-13181-005SB 1 Elevator Control 27-13181-005 Scrap Cable 27-13181-011SB 1 Elevator Control 27-13181-011 Scrap Cable 27K70004 1 Kit Drawing None None For Aircraft Serial Numbers AT071, AT072, and AT073. NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION 27-13233-015SB 2 Aileron Control Cables 27-13233-015 Scrap 3 / 4 27-13233-007SB 1 Aileron Trim Tab 27-13233-007 Scrap Control Cable 27-13233-077SB 2 Rudder Control Cable 27-13233-077 Scrap 27-13233-009SB 1 Rudder Trim Tab 27-13233-009 Scrap Control Cable 27-13233-011SB 1 Elevator Control 27-13233-011 Scrap Cables 1 and 2, LH 27-13233-013SB 1 Elevator Control 27-13233-013 Scrap Cables 1 and 2, RH

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# SERVICE BULLETIN SA226 SERIES

For Aircraft Serial Numbers AT071, AT072, and AT073 (Continued). NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION 27K70004 1 Kit Drawing None None
For Aircraft Serial Numbers TC277. NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION 27-13216-009SB 2 Elevator Control Cable 27-13216-009 Scrap 27-13216-007SB 2 Rudder Control Cable 27-13216-007 Scrap 27-13216-005SB 1 Rudder Trim Tab 27-13216-005 Scrap Control Cable 27K70004 1 Kit Drawing None None