# AD 82-23-01 R1: Placard Near Flap Actuator - Type: Airworthiness directive - Status: Current - Products: Piper PA-24, PA-24-250, PA-24-260, PA-30 and PA-39 with STC SA2312WE or SA2495WE - Effective: April 7, 1983 - Published: March 31, 1983 - Issued: March 21, 1983 - Superseded by: Nothing supersedes this AD - Product type: Aircraft, Small airplane - Amendment: 39-4603 - Registered aircraft: 3,117 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/8B9D789516B1802E862569A6005C90BD.0001 - DRS record last changed: November 21, 2025 - Page: https://openairdocs.org/ad/82-23-01-R1 ## The airworthiness directive 82-23-01 R1 PIPER: Amendment 39-4483 as amended by Amendment 39-4603. Applies to Piper Models PA-24, PA-24-250, and PA-24-260 airplanes, modified per Robertson Supplemental Type Certificate (STC) SA2495WE, and PA-30 and PA-39 airplanes, modified per Robertson STC SA2312WE, certificated in any category. COMPLIANCE: Required within 25 hours time-in-service after the effective date of this AD unless already accomplished. To prevent possible loss of airplane control due to an asymmetrical flap extension or retraction, accomplish the following: (a) Install a temporary placard on the panel near the flap actuator which reads: "DO NOT EXTEND FLAPS BEYOND 15 DEGREES (TAKEOFF POSITION)" and operate the airplane in accordance with this limitation. (b) Insert a copy of Figure 1 of this AD dated March 3, 1983, or FAA approved equivalent, in the Airplane Flight Manual. (c) The installation of the placard and insertion of Figure 1 of this AD in the AFM may beaccomplished by the owner/operator of the airplane. This person shall make an appropriate entry in the airplane's maintenance record indicating compliance with this AD. (d) The temporary placard required by paragraph (a) and Figure 1 dated March 3, 1983, inserted in the Airplane Flight Manual as required by paragraph (b) may be removed when a positive flap retraction system is installed in accordance with Robertson Aircraft Corporation Service Bulletin 19 dated October 22, 1982. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, Seattle Area Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. Amendment 39-4483 became effective on November 8, 1982. This Amendment 39-4603 becomes effective April 7, 1983. Figure 1, AD 82-23-01 (March 3, 1983) FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT TO THE PIPER PA-24, PA-24-250, PA-24-260 AND PIPER PA-30, PA-39 AIRPLANE FLIGHT MANUALS This supplement applies to the above aircraft when modified with the Robertson STOL modification under STC SA2495WE or SA2312WE but have not been modified with the Robertson positive flap retraction system described in Robertson Service Bulletin 19 dated October 22, 1982. This document must be carried in the basic manual of the modified aircraft. The information in this document supersedes the basic manual only where covered in the items contained herein. For Limitations, Procedures and Performance not contained in this Supplement, consult the basic manual. I. LIMITATIONS Maximum flap extension is limited to 15 degrees under all flight conditions for electrically-operated flaps or second notch (approximately 18 degrees) for manually-operated flaps. II. PROCEDURES. EMERGENCY Flap operation: If the airplane begins a pronounced roll in either direction upon flap extension or retraction, immediately cease flap operation and reversethe action. That is, if flaps are being retracted and pronounced roll begins, cease retracting the flaps and initiate extension to previous setting or until the roll stops. If flaps are being extended and a pronounced roll begins, cease extending flaps and return flaps to the retracted position. Leave the flaps in the last position found to permit aileron neutral flight and return to a suitable landing field. If flaps are retracted, consider the need for additional landing field length. If flaps are extended, limit airspeed to maximum flaps extended speed (125 m.p.h. - 180K). NOTE The restriction against continuous flap retraction is necessary because of the possibility of asymmetric flaps occurring under certain conditions. With one flap extended to 15 degrees, or second notch (approximately 18 degrees) for manually-operated flaps, the airplane is controllable by coordinated use of ailerons and rudder. The EMERGENCY procedures listed above should be followedif pronounced roll is encountered when flaps are moved. This will restore balanced lift to each wing, permitting normal aileron authority for maneuvering the airplane. III. PERFORMANCE No change. ## Affected data sheets (2) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS 1A15](https://openairdocs.org/tcds/1A15): Piper Aircraft Inc.; names 3 of 4 models: PA-24, PA-24-260, PA-24-250 - [TCDS A1EA](https://openairdocs.org/tcds/A1EA): Piper Aircraft Inc.; names 2 of 3 models: PA-30, PA-39 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 3,117 (3,117 by airframe model, 0 by engine model) - Makers: Piper 3,117 Models with the most aircraft: - [Piper PA-24-250](https://openairdocs.org/model/piper-pa-24-250): 1,222 aircraft (airframe model) - [Piper PA-30](https://openairdocs.org/model/piper-pa-30): 878 aircraft (airframe model) - [Piper PA-24-260](https://openairdocs.org/model/piper-pa-24-260): 590 aircraft (airframe model) - [Piper PA-24](https://openairdocs.org/model/piper-pa-24): 345 aircraft (airframe model) - [Piper PA-39](https://openairdocs.org/model/piper-pa-39): 82 aircraft (airframe model) All 5 models: https://openairdocs.org/ad/82-23-01-R1/models.md Every aircraft: https://openairdocs.org/ad/82-23-01-R1/aircraft.md ## Related documents - [STC SA2312WE](https://openairdocs.org/stc/SA2312WE): Installation of leading edge cuffs, stall fences, stall strips drooped ailerons, flap actuated stabilator trim system, raked wing tips(optional) and dorsal fin.. Sierra Industries Inc, Named in the applicability - [STC SA2495WE](https://openairdocs.org/stc/SA2495WE): Installation of recontoured wing leading edge, staff fences, drooped ailerons in flaps down mode, flap actuated stabilator trim system, new wing tips, SC-100 stall warning system.. Sierra Industries Ltd., Named in the applicability --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.