| AD Number | 81-16-10 | Status | Active |
| Effective Date | September 17, 1981 | Issue Date | August 27, 1981 |
| Docket Number | Unknown | Amendment | 39-4210 |
| 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-44-180 PA-44-180T |
81-16-10 PIPER AIRCRAFT CORPORATION: Amendment 39-4210. Applies to the following Piper models of aircraft certificated in all categories: PA-44-180 Seminole, S/N 44- 7995001 through 44-8195016; PA-44-180T Turbo Seminole, S/N 44-8107001 through 44- 8107044.
Compliance is required as indicated upon receipt of this directive, unless already accomplished.
NOTE: An airmail letter was mailed to owners and operators on August 3.
To prevent possible damage to the outboard leading edge skin, as well as an aileron out- of-balance condition which could lead to aeroelastic instability, accomplish the following:
(a) Before further flight, visually check for cracks at the aileron outboard leading edge balance weight attachment screws.
(1) If cracks are found, comply with paragraph (d).
(2) If no cracks are found, make log book entry that visual check was made.
NOTE: The visual check only may be accomplished by the pilot.
(b) At intervals not to exceed25 hours until 100 hours time in service from the effective date of this AD accomplish the following:
(1) Inspect, using a 10-power magnifying glass, the left and right aileron outboard leading edge skin for cracks near the balance weight attachment screws.
(2) If the skin is cracked near any balance weight attachment screw, comply with paragraph (d) of this AD before further flight.
(3) If there are no cracks, make appropriate log book entry of each inspection.
(c) Within 100 hours time in service from the effective date of this AD comply with paragraph (d).
(d) Reinforce the ailerons outboard leading edge skins by installing Piper's aileron rework kit, Piper Part No. 764 148V in accordance with instructions included with the kit, and make appropriate log book entry.
An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region.
Airplanes on which cracks arefound may be flown in accordance with FAR 21.197 and 21.199 to a base where the aileron rework kit can be installed, provided the airplane is not flown in excess of 130 MPH indicated speed.
Piper Service Bulletin No. 725A pertains to this subject.
This amendment becomes effective September 17, 1981, and was effective upon receipt of the airmail letter mailed August 3 to owners and operators.