AD 81-16-10
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-44-180 | Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories |
| aircraft | Piper Aircraft Inc. | PA-44-180T | Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories |
Unsafe Condition
Cracks at the aileron outboard leading edge balance weight attachment screws could lead to an aileron out-of-balance condition and aeroelastic instability.
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Required Actions
Visually check for cracks at the aileron outboard leading edge balance weight attachment screws before further flight. If cracks are found, install Piper's aileron rework kit (Part No. 764 148V) and make log book entries. If no cracks, log the visual check. Inspect using a 10-power magnifying glass at intervals not exceeding 25 hours until 100 hours time in service from the AD's effective date. After 100 hours, comply with paragraph (d) to reinforce the ailerons.
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Compliance Time
Compliance is required as indicated upon receipt of this directive, unless already accomplished.
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Affected Aircraft
Piper Model PA-44-180 Seminole, serial numbers 44-7995001 through 44-8195016; PA-44-180T Turbo Seminole, serial numbers 44-8107001 through 44-8107044.
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Federal Register Abstract
Outboard Leading Edge Skin
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-16-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-16-10 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories Subject: Outboard Leading Edge Skin Status: Current Citation: This information is not available. Citation Publish Date: 09/10/1981 Effective Date: 09/17/1981 Make: Piper Aircraft Inc. Model: PA-44-180 | PA-44-180T Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-16-10 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4210 AD NUMBER: 81-16-10 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories ACTION: SUMMARY: DATES: Effective September 17, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 exceed 25 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 are found 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. FOOTER:
Document Text
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AD Final Rules - DRS_81-16-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-16-10 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories Subject: Outboard Leading Edge Skin Status: Current Citation: This information is not available. Citation Publish Date: 09/10/1981 Effective Date: 09/17/1981 Make: Piper Aircraft Inc. Model: PA-44-180 | PA-44-180T Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-16-10 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4210 AD NUMBER: 81-16-10 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-44-180 Airplanes In All Categories ACTION: SUMMARY: DATES: Effective September 17, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 exceed 25 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 are found 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. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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