AD/PA-32/42 Amdt 2 Wing Structural Fatigue Life Limitation (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PA-32/42 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Piper PA-32 (Cherokee Six) Series Aeroplanes

AD/PA-32/42 Amdt 2 Wing Structural Fatigue Life Limitation 8/2009 DM

Applicability:

All PA-32 series aircraft, all models.

Requirement:

1.    Retire from service:

1.1. The wing main spar assembly; and

1.2. The bottom cap of the wing main spar box (carry through).

OR

2.    Inspect the lower wing joint for fatigue cracks in accordance with an approved inspection program.

Note 1:  For Requirement 1, replace retired components in accordance with approved maintenance data; Regulations 42V and 2A refer.

Note 2:  For Requirement 2, acceptable standards for the inspection program are CAO 101.22.3.61 (3) and FAR 23.573.

Compliance:

For models PA-32-260, PA-32-300, PA-32R-300, PA-32S-300, PA-32RT-300,
PA-32RT-300T:

For Requirement 1:  Retire before 11000 hours component time in service.

For Requirement 2:  Inspect before 11000 hours component time in service, and thereafter at the intervals specified in the approved inspection program.

For models PA-32-301, PA-32R-301, PA-32-301T, PA-32R-301T, PA-32-301FT, PA-32-301XTC:

For Requirement 1:  Retire before 13700 hours component time in service.

For Requirement 2:  Inspect before 13700 hours component time in service, and thereafter at the intervals specified in the approved inspection program.

This Amendment becomes effective on 29 May 2009.

Background:

Fatigue analysis predicts the possibility of cracking in the lower wing joint.  Such cracking caused a fatal accident to a similar model with the same style of wing joint.

The original issue of this Airworthiness Directive became effective on 29 October 1976.

Amendment 1 re-affirms that all PA-32 series models are subject to the life limit, even those released after the original issue of this Directive.  Amendment 1 minimises the structure to be retired by limiting it to the components which comprise the lower wing joint.

Amendment 1 provided the possibility of inspection as an alternative to retirement.

Amendment 2 adjusts the life limit for Saratoga models with a semi-tapered wing following a review of Piper fatigue reports.

David Villiers
Delegate of the Civil Aviation Safety Authority

22 May 2009