Commonwealth legislation

AD/PA-32/27 Amdt 2 - Wing Rear Spar Inspection

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This Act has been repealed and is no longer in force. It is retained for historical reference.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 mandatory safety rule requires owners/operators of Piper PA-32 Cherokee Six aircraft to inspect the wing rear spar-to-fuselage attachment for hidden corrosion, deteriorated rivets, cracking, pitting or bulging — accessing the area by removing underwing covers or interior floor panels.

If never inspected, do so within 100 flight hours after 4 January 1996; otherwise, repeat inspections every three years. The check prevents undetectable spar corrosion that can cause catastrophic wing failure.

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AD/PA-32/27 Amdt 2 - Wing Rear Spar Inspection

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source Piper PA-32 (Cherokee Six) Series Aeroplanes

AD/PA-32/27

Amdt 2

Applicability: All models.

Wing Rear Spar Inspection 1/96

Requirement: Visually inspect the wing rear spar to fuselage attachment area for evidence of corrosion between the rear spar P/Ns 62054-() and 35174-(), and spar plate P/Ns 62056-() and 66762-().

Note: It is imperative to inspect the front face of the rear spar through the internal area of the wing after removal of the underwing fillet or fuselage floor panels in the area of the wing rear attachments. Corrosion of the aluminium alloy rear spar proceeds from the inboard end and is detected by deterioration of rivet tails, pitting, bulging and cracking of the rear spar.

Compliance: For aircraft not inspected in accordance with the previous issue of this Directive, inspect within 100 hours time in service after 4 January 1996, and thereafter at intervals not to exceed 3 calendar years. For all other aircraft, inspect at intervals not exceeding 3 calendar years.

Background: Local defect experience indicates that complete disintegration of the rear spar material can occur in the area of the rear spar and steel plate faying surfaces, without any external evidence of deterioration. Amendment 2 is issued to revise component P/N applicability to include additional aircraft.

Source text

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