82-27-13 R2 PIPER AIRCRAFT CORPORATION: Amendment 39-4534 as amended by Amendment 39-4707. Applies to Models PA-31 (S/Ns 31-2 thru 31-7812129), PA-31-300 (S/Ns 31-2 thru 31-511), PA-31-325 (S/Ns 31-7300932 thru 31-7812129), PA-31-350 (S/Ns 31-5001 thru 31-7852171), PA-31T (S/Ns 7400002 thru 31T-7820092, except 31T-7820067), PA-31T1 (S/Ns 31T-7804001 thru 31T-7804011) and PA-31P (S/Ns 31P-1 thru 31P-7730012) airplanes certificated in any category.
COMPLIANCE: Required as indicated unless already accomplished.
To prevent loss of control due to flap asymmetric conditions caused by failure of the flap extension system, accomplish the following:
a) On Models PA-31 (S/Ns 31-2 thru 31-7812129), PA-31-300 (S/Ns 31-2 thru 31- 511), PA-31-325 (S/Ns 31-7300932 thru 31-7812129), PA-31-350 (S/Ns 31-5001 thru 31- 7852171) and PA-31P (S/Ns 31P-1 thru 31P-7730012) airplanes:
1. Within 25 hours time-in-service after April 22, 1982, restrict maximum flap extension to 25 degrees by installation of temporary instrument markings and placards and incorporation of pen and ink changes in the applicable "Airplane Flight Manuals" or "Pilot's Operating Handbook and FAA Approved Flight Manual" in accordance with Part I of Piper Service Bulletin No. 739, dated March I, 1982. The installation of permanent kits prescribed in paragraph a)4 below meets these requirements.
2. Within 100 hours time-in-service after April 22, 1982, and thereafter at intervals not exceeding 500 hours time-in-service, visually inspect the flap flexible drive shaft assemblies for alignment, wear and security of attachment of end fittings to the flexible shaft. Prior to further flight, replace unsatisfactory parts in accordance with Part II of Piper Service Bulletin No. 739, dated March 1, 1982.
3. Within the next 100 hours time-in-service after April 22, 1982, or when last accomplished under AD 76-10-06 or AD 81-11-03 and thereafter at intervals not exceeding 100 hours time-in-service, visually inspect the wing flap transmission for excessive wear. Prior to further flight, rework or replace this assembly, as necessary, in accordance with "Instructions No. 1" of Piper Service Bulletin 494B dated July 17, 1979.
4. Permanent Piper Flap Travel Restrictions and Placard Kit, P/N 764 396, applicable to Model PA-31, PA-31-300, PA-31-325 and PA-31-350 airplanes, and P/N 764 397, applicable to Model PA-31P airplanes, may be incorporated when available. On or before March 31, 1983, install Flap Travel Restriction Supplementary Kit, P/N 764 920L, in accordance with Piper Service Letter 958 dated October 25, 1982, which includes additional stops and modification instructions to preclude the possibility of flap damage.
NOTE: Service Letter 958 applies only to those aircraft listed in paragraph a) of this AD which have installed Piper Kit 764 396 or 764 397 with an issue date of March 5, 1982 (820305), in compliance with Piper Service Bulletin 739, Part III, dated March I, 1982.
All Piper Kits 764 396 and 764 397 shipped from the factory on or after September 9, 1982, will be identified with a revision date of September 21, 1982 (R82092I), and will incorporate the supplementary material and instructions referenced in this Service Letter.
The installation of these later kits can be determined by examination of the center flap tracks for presence of a P/N 71887-02 upper flap stop as shown on page 3 of Piper Service Letter 958 dated October 25, 1982.
b) On Model PA-31T (S/Ns 31T-7400002 thru 31T-7520013) airplanes:
1. Within 25 hours time-in-service after April 22, 1982, restrict maximum flap extension to 15 degrees by installation of temporary instrument markings and placards and incorporation of pen and ink changes in the "Pilot's Operating Handbook and FAA Approved Airplane Flight Manual" in accordance with Part I of Piper Service Bulletin No. 741, dated March I, 1982. The installation of permanent placards and manual revisions prescribed by paragraph b)4 below meets this requirement.
2. Within the next 100 hours time-in-service after April 22, 1982, and thereafter at intervals not exceeding 500 hours time-in-service, visually inspect the flap flexible drive shaft assemblies for alignment, wear and security of attachment of end fittings to the flexible shaft. Prior to further flight, replace unsatisfactory parts in accordance with Part I B, Piper Service Bulletin No. 741, dated March 1, 1982.
3. Within the next 100 hours time-in-service after April 22, 1982, or since last accomplished under AD 76-10-06 or AD 81-11-03 and thereafter at intervals not to exceed 100 hours time-in-service, visually inspect the wing flap transmission for excessive wear. Prior to further flight, rework or replace this assembly as necessary in accordance with "Instructions No. 1" of Piper Service Bulletin No. 494B, dated July 17, 1982.
4. Permanent Autopilot/Flap Operation Placard, Piper P/N 81009-02 and permanent "Pilot's Operating Handbook and FAA Approved Airplane Flight Manual" revisions incorporating the same information specified in paragraph b)I may be incorporated when available.
5. Upon installation of Piper Kit 764-398, Wing Flap Transmission Modification Kit, the restrictions and inspections required by paragraphs b)I and 2 are no longer required and temporary markings and manual revisions may be removed and the requirements of paragraph c) below become applicable.
c) On Model PA-31T (S/Ns 31T-7520014 thru 31T-7820066, 31T-7820068 thru 31T-7820092) and those airplanes having S/N 31T-7400002 thru 31T-7520013 if Piper Kit 764 398 is installed and Model PA-31T1 (S/Ns 31T-7804001 thru 31T-7804011) airplanes:
1. Within the next 25 hours time-in-service after April 22, 1982, install a Temporary Autopilot/Flap Operating Placard and make temporary changes in the "Airplane Flight Manual" or "Pilot's Operating Handbook and FAA Approved Airplane Flight Manual" in accordance with Part II of Piper Service Bulletin No. 741, dated March 1, 1982. The installation of a permanent placard and manual revisions prescribed by paragraph c)3 below meets these requirements.
2. Within the next 100 hours time-in-service after April 22, 1982, or when last accomplished under AD 76-10-06 or AD 81-11-03 and thereafter at intervals not exceeding 100 hours time-in-service, visually inspect the wing flap transmission for excessive wear. Prior to further flight, rework or replace this assembly as necessary in accordance with "Instructions No. 1" of Piper Service Bulletin 494B, dated July 17, 1979.
3. Permanent Autopilot/Flap Operation Placard, Piper P/N 81009-02 and permanent "Pilot's Operating Handbook and FAA Approved Airplane Flight Manual" revisions incorporating the same information specified in paragraph c)1 may be incorporated when available.
d) Upon submission of substantiating data by an owner or operator, through an FAA Maintenance Inspector, theManager, Atlanta Aircraft Certification Office, FAA, may adjust the inspection intervals and compliance times specified in this AD.
e) An equivalent method of compliance with this AD when used must be approved by the Manager, Atlanta Aircraft Certification Office, FAA, P.O. Box 20636, Atlanta, Georgia 30320. The following has been approved as an equivalent method of compliance with paragraph a)I, a)2, a)4.
1. Remove wing flap transmissions (20:1 gear ratio):
Piper P/N 489-425(L.H.), Dukes P/N 1209-00-1
Piper P/N 489-426(R.H.), Dukes P/N 1210-00-1
2. Install transmissions (40:1 gear ratio):
Piper P/N 489-427(L.H.), Dukes P/N 1215-00-1
Piper P/N 489-428(R.H.), Dukes P/N 1216-00-1
or alternatively:
3. Convert the transmissions to 40:1 gear ratio by use of Piper Kit No. 755 050 or No. 764 398 (Dukes Kit No. 1215-1000). The converted units are then identified as:
Piper P/N 489-427(L.H.), Dukes P/N 1215-00-1
Piper P/N 489-428(R.H.), Dukes P/N 1216-00-1
4. Remove flexible drive shaft, Piper P/N 486-590 or 486-597, as applicable, and install flexible drive shaft Piper P/N 486-631.
5. Change the Autopilot/Flap Operation Placard located on the pilot's side window molding to read:
"OPERATE FLAP CONTROL IN SMALL INCREMENTS TO ASSURE FLAP
SYMMETRY. NO FLAP SELECTION WITH AUTOPILOT ENGAGED."
6. Remove red full flap radial position mark on flap position indicator at 25 degrees as required by Part 1 of Piper Service Bulletin No. 739 dated March 1, 1982.
7. Install a Supplement to the POH which reflects appropriate revisions to the pages and paragraphs listed in Piper Service Bulletin No. 739, dated March 1, 1982. Delete the limitations imposed by the 25 degree flap setting and insert those applicable to the 40 degree flap setting. However, retain the instructions for incremental flap extension and retraction. This Supplement must be approved by the Manager, Atlanta Aircraft Certification Office located at the address specified in paragraph e) of this AD.
8. Compliance with Part II of Piper Service Letter No. 959, dated June 10, 1983, is approved as an equivalent means of compliance with paragraphs a)1, a)3 and a)4 of this AD.
9. Compliance with Part I of Piper Service Letter No. 959, dated June 10, 1983, is approved as an equivalent method of compliance with paragraphs a)1 through a)4 of this AD.
NOTE: In the event replacement flexible drive shafts are not available for the PA-31, PA-31-300, PA-31-325 and PA-31-350 airplanes, the airplane may be operated with flaps secured in the full-up position provided appropriate performance data is used.
This amendment supersedes AD 82-08-06 (Amendment 39-4368 as revised by Amendment 39-4456).
Amendment 39-4534 became effective January 11, 1983.
This Amendment 39-4707 becomes effective August 18, 1983.