AD/PA-32/27 Amdt 2 - Wing Rear Spar Inspection
1AD/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
Image unavailable in extracted text 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.