Commonwealth legislation

AD/PA-31/94 Amdt 2 - Fuselage Bulkhead at STA.317.5

RepealedCTH

This Act has been repealed and is no longer in force. It is retained for historical reference.

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This directive requires owners/operators of specified Piper PA‑31 series (Navajo, Chieftain, Mojave; certain serial ranges) to inspect the fuselage bulkhead at station 317.5 for cracks where the vertical fin attaches and to install a permanent reinforcement kit—Kit 764‑028 if cracks are found, Kit 763‑917 if not. Work must be done within 100 flight hours after 12 Sep 1996. It replaces recurring inspections with a one‑time structural fix to prevent tail failure.

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Current sections

Direct links to the current provisions in AD/PA-31/94 Amdt 2 - Fuselage Bulkhead at STA.317.5.

AD/PA-31/94 Amdt 2 - Fuselage Bulkhead at STA.317.5

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Piper PA-31 Series Aeroplanes

AD/PA-31/94

Amdt 2

Fuselage Bulkhead at STA.317.5 10/96

Applicability: Models Serial Numbers

PA31, PA31-300 and PA31-325 31-2 through 31-7912039 PA31-350 31-5001 through 31-7952071

Requirement: 1. Inspect the upper section of the Fuselage Station 317.75 bulkhead for cracks in accordance with the Instructions section of Piper Service Bulletin 636A.

If any crack is found, incorporate Piper Kit 764-028 in accordance with the instructions included with that kit, revised 18 June 1990.

b. If no crack is found, incorporate Piper Kit 763-917 in accordance with the instructions included with that kit, revised 18 June 1990.

Note: FAA AD 96-12-12 Amdt 39-9654 refers.

Compliance: Within 100 hours time in service after 12 September 1996, unless Piper Kit 764-028 or Piper Kit 763-917 is already incorporated.

Background: Instances have occurred of cracks developing in the bulkhead flange area of STA.317.75 at the attachment point for the vertical fin forward spar.

Amendment 1 introduced amendment A of the Requirement Document.

Amendment 2 is issued to reflect a new FAA AD which was issued in response to further reports of cracks and the Federal Aviation Administration's policy on ageing commuter-class aircraft by eliminating or, in certain instances, reducing the number of repetitive short-interval inspections when improved parts or modifications are available.

The original issue of this Airworthiness Directive became effective on 30 September 1980.

Amendment 1 of this Airworthiness Directive became effective on 30 November 1980.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/PA-31/94 Amdt 2 - Fuselage Bulkhead at STA.317.5