AD 85-05-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-31P | Airworthiness Directives; Piper Model PA-31P Airplanes |
Unsafe Condition
Propagation of cracks in the fuselage bulkhead at station 332.0 and loss of stabilizer front spar structural support.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 25 hours time-in-service after the effective date, and every 200 hours thereafter, inspect the fuselage station 332.0 bulkhead using dye-penetrant method per Piper S/B No. 802. If cracks exist within acceptable limits, stop drill cracks and install Reinforcement Kit (P/N 764-983) or reinforced bulkhead (P/N 45583-16). If cracks exceed limits, replace bulkhead with P/N 45583-16. Repetitive inspections may stop after installing specified parts. Adjust inspection intervals up to 10% for maintenance coordination.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not exceeding 200 hours time-in-service
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Model PA-31P (Serial Numbers 31P-3 through 31P-7730012)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inspection of F.S. 332.0 Bulkhead
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_85-05-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 85-05-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-31P Airplanes Subject: Inspection of F.S. 332.0 Bulkhead Status: Current Citation: This information is not available. Citation Publish Date: 03/12/1985 Effective Date: 03/15/1985 Make: Piper Aircraft Inc. Model: PA-31P Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part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: 85-05-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5011 AD NUMBER: 85-05-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-31P Airplanes ACTION: SUMMARY: DATES: Effective March 15, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 85-05-01 PIPER: Amendment 39-5011. Applies to Model PA-31P (Serial Numbers 31P-3 through 31P-7730012) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent the propagation of cracks in the fuselage bulkhead at station 332.0, and loss of stabilizer front spar structural support, accomplish paragraph (a) as follows: (a) Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not exceeding 200 hours time-in-service, inspect, using a dye-penetrant method, the fuselage station 332.0 bulkhead in accordance with Piper S/B No. 802 dated December 12, 1984. (1) If no cracks are found to exist, make appropriate maintenance record entry of compliance. (2) If cracks are found that do not exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight stop drill the crack(s), and install Reinforcement Kit, Piper Part Number 764-983, or reinforced bulkhead assembly, Piper Part Number 45583-16. (3) If cracks are found that exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight replace the bulkhead assembly with Reinforced Bulkhead Assembly, Piper Part Number 45583-16. (b) The repetitive inspections required by paragraph (a) of this AD may be discontinued when Reinforcement Kit Piper Part Number 764-983, or Replacement Bulkhead Piper Part No. 45583-16 is installed. (c) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) The airplanes may be flown, in accordance with FAR 21.197 to a location where the AD may be accomplished. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Central Region, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. This amendment becomes effective on March 15, 1985. FOOTER:
Document Text
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AD Final Rules - DRS_85-05-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 85-05-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-31P Airplanes Subject: Inspection of F.S. 332.0 Bulkhead Status: Current Citation: This information is not available. Citation Publish Date: 03/12/1985 Effective Date: 03/15/1985 Make: Piper Aircraft Inc. Model: PA-31P 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: 85-05-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5011 AD NUMBER: 85-05-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-31P Airplanes ACTION: SUMMARY: DATES: Effective March 15, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 85-05-01 PIPER: Amendment 39-5011. Applies to Model PA-31P (Serial Numbers 31P-3 through 31P-7730012) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent the propagation of cracks in the fuselage bulkhead at station 332.0, and loss of stabilizer front spar structural support, accomplish paragraph (a) as follows: (a) Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not exceeding 200 hours time-in-service, inspect, using a dye-penetrant method, the fuselage station 332.0 bulkhead in accordance with Piper S/B No. 802 dated December 12, 1984. (1) If no cracks are found to exist, make appropriate maintenance record entry of compliance. (2) If cracks are found that do not exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight stop drill the crack(s), and install Reinforcement Kit, Piper Part Number 764-983, or reinforced bulkhead assembly, Piper Part Number 45583-16. (3) If cracks are found that exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight replace the bulkhead assembly with Reinforced Bulkhead Assembly, Piper Part Number 45583-16. (b) The repetitive inspections required by paragraph (a) of this AD may be discontinued when Reinforcement Kit Piper Part Number 764-983, or Replacement Bulkhead Piper Part No. 45583-16 is installed. (c) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) The airplanes may be flown, in accordance with FAR 21.197 to a location where the AD may be accomplished. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Central Region, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. This amendment becomes effective on March 15, 1985. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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