| AD Number | 83-19-03 | Status | Active |
| Effective Date | September 30, 1983 | Issue Date | September 15, 1983 |
| Docket Number | Unknown | Amendment | 39-4730 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | --- - _EMPTY_ |
| Citation | This information is not available. | ||
| Manufacturer(s) | Piper Aircraft Inc. |
| Model(s) | PA-24 PA-24-250 PA-24-260 PA-24-400 PA-30 PA-39 |
83-19-03 PIPER: Amendment 39-4730. Applies to Models PA-24-180/250/260 (S/N 24-1 and up); PA-24-400, (S/N 26-2 and up); PA-30 (S/N 30-2 thru 30-2000); and PA-39 (S/N 39-1 thru 39-155) airplanes certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To prevent wing lower main spar cap damage and possible cracks in this component where it enters the fuselage at the lower wing root fairing, accomplish the following:
a) Within the next 100 hours time-in-service after the effective date of this AD, inspect the lower spar cap for chafing damage and cracks in accordance with the Instructions Section of Piper Service Bulletin 751 dated May 24, 1983.
b) Prior to further flight, polish out any chafing damage or replace parts which are cracked or that have chafing damage which cannot be polished out within the depth limits specified in the Instructions Section of Piper Service Bulletin 751 dated May 24, 1983, with a serviceable part.c) Prior to reinstallation, trim the lower portion of the seal plates in accordance with the Instructions Section of Piper Service Bulletin 751 dated May 24, 1983.
d) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished.
e) An equivalent method of compliance with this AD may be used, if approved, by the Manager, New York Aircraft Certification Office, FAA, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581.
This amendment becomes effective on September 30, 1983.