Service Bulletin (SB) supersedes SB 1245. Aircraft that have previously complied with SB 1245 are already in 

compliance with SB 1245A.

SUBJECT: STABILATOR control system INSPECTION

Reason for revision: SB1245A clarifies cleaning and inspection instructions. 

MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

PA-28 Series All

PA-28S Series All

PA-28R Series All

PA-28RT Series All

PA-32 Series All

PA-32S Series All

PA-32R Series All

PA-32RT Series All

PA-34 Series All

PA-44 Series All

COMPLIANCE TIME: Upon reaching fifteen (15) calendar years time-in-service, initial inspection to 

coincide with the next regularly scheduled maintenance event. 

Thereafter, compliance to be accomplished on a recurring basis, at an interval 

not to exceed two thousand (2,000) operating hours or seven (7) calendar years 

time-in-service, whichever occurs first.

Note: A logbook entry documenting the replacement of any flight control 

cable or turnbuckle body will relieve the inspection requirement for that 

component only, until such time as that component has been in service 

for 15 calendar years.

APPROVAL: The technical content of this Service Document has been shown to comply with 

the applicable Federal Aviation Regulations and is FAA approved.

 SERVICE NO. 1245A

 BULLETIN

PIPER CONSIDERS

COMPLIANCE MANDATORY

Piper Aircraft, Inc.

2926 Piper Drive

Vero Beach, Florida, U.S.A. 32960

Date: November 28, 2012 (S) (M)

ATA: 2730

(OVER)
SERVICE BULLETIN NO. 1245A PAGE 2 of 3

PURPOSE: Existing Instructions for Continued Airworthiness (i.e., the appropriate Piper 

Maintenance Manual and associated Service Publications) include an inspection 

of all flight control pulleys, cables, fittings and turnbuckles on a recurring basis. 

However, service history suggests that over time, the turnbuckles used in the 

stabilator flight control cable system may develop cracks or corrosion which may 

not be detected during these inspections.

This Service Bulletin provides specific instructions for the recurring inspection of 

the stabilator flight control system.

NOTE: Refer to the applicable Piper Maintenance Manual, as well as Piper 

Service Letters SL 1069 and SL 1135 for additional flight control cable 

maintenance requirements.

INSTRUCTIONS:

note: Refer to the applicable Piper Maintenance Manual for model specific details.

1. Secure a jack stand to the tail skid (tie down). Visually inspect the entire length of the Stabilator flight control 

cable system, with special emphasis on the turnbuckle area, as described in the steps that follow.

2. Locate the rear cabin bulkhead, which is behind the aft seats. The rear cabin bulkhead is accessible from inside 

the aircraft.

Note: Temporary removal of seats and/or other interior components may be required to accomplish this 

inspection.

3. Remove and retain the access cover from the rear cabin bulkhead, in order to gain access to the tailcone area.

4. Identify the two (2) stabilator flight control cable turnbuckles, which are located inside the tailcone, directly aft 

of the rear cabin bulkhead. See Figure 1. Using procedures described in the appropriate Service/Maintenance 

Manual, disassemble the turnbuckle bodies to facilitate a complete inspection of the turnbuckle bodies and 

associated cable terminals.

5. Clean the turnbuckle bodies and associated cable terminals thoroughly with Methyl Ethyl Ketone (MEK) or 

acetone prior to inspection. The non-threaded surfaces of the turnbuckle body and cable terminals may be 

cleaned using Scotch-BriteTM General Purpose Green Scouring Pad 96 or 105b.

NOTE: Most of the affected aircraft use control cables featuring strands made of galvanized steel. By design, 

the galvanized coating corrodes sacrificially, protecting the steel strands underneath. This normal 

corrosion process creates zinc oxide powder, which can migrate along the length of the control 

cable, covering the surfaces of the turnbuckle components with an inert white speckled coating. This 

coating, along with any other contaminants such as dirt, oil or grease, must be removed in order to 

properly examine the turnbuckle and cable terminals.

6. Using a 10X magnifier, a mirror and a suitable light source, carefully examine the entire surface of each 

turnbuckle, cable terminal, and adjacent portion of the flight control cable, inspecting for cracks, corrosion, or 

broken cable strands. Any evidence of cracks or cable fraying, however minute, is cause for replacement. Any 

evidence of corrosion that remains after accomplishing the cleaning instructions above is cause for replacement.

7. Using procedures described in the appropriate Service/Maintenance Manual, reassemble the turnbuckle 

bodies and associated cable terminals. Rig and adjust stabilator travel and stabilator control cable tension. 

8. Reinstall the rear cabin bulkhead access cover, which was removed in Step 3. Reinstall any interior components 

that were removed in Step 2.

9. Remove the jack stand from the aircraft.

10. Make a logbook entry indicating compliance with this Service Bulletin.
SERVICE BULLETIN NO. 1245A PAGE 3 of 3

MATERIAL REQUIRED:

Procure locally

Methyl Ethyl Ketone (MEK) or acetone

Scotch-BriteTM General Purpose Green Scouring Pad 96 or 105b

AVAILABILITY OF PARTS: N/A

Effectivity date: This Service Bulletin is effective upon receipt.

Summary: Please contact your Factory Authorized Piper Service Facility to make 

arrangements for compliance with this Service Bulletin in accordance with the 

compliance time indicated.

Note: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, 

serial number, current owner’s name and address.

Corrections and/or changes should be directed to:

PIPER AIRCRAFT, INC.

Attn: Customer Service

2926 Piper Drive

Vero Beach, FL 32960

Figure 1

Stabilator Control Cables (Typical)

To Stabilator

Turnbuckles

OUTBD FWD

UP