1AD/PA-31/130 - Rudder Torque Tube Assembly and Rudder Rib

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AIRWORTHINESS DIRECTIVE

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For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (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.

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Piper PA-31 Series Aeroplanes

AD/PA-31/130 Rudder Torque Tube Assembly and

Rudder Rib

2/2004

Applicability: Model

PA-31, PA-31-300, PA-31-325 PA-31-350

PA-31P

PA-31P-350 PA-31T

PA-31T1 PA-31T2 PA-31T3

Serial numbers

31-2 through 31-8312019

31-5001 through 31-8553002

31P-1 through 31P-7730012

31P-8414001 through 31P-8414050

31T-7400001 through 31T-8120104

31T-7804001 through 31T-1104017

31T-8166001 through 31T-1166008

31T-8275001 through 31T-5575001

Requirement: 1. Install an inspection hole in the rudder skin for the rudder torque tube assembly in accordance with Piper Aircraft Service Bulletin (SB) No. 1105A, dated 22 September 2003; or, instead of installing an inspection hole, use the tooling hole in the rudder bottom rib. Enlargement of the diameter of the tooling hole by a maximum of 0.25 inches may be accomplished to facilitate inspection and corrosion treatment.

2. Visually inspect the rudder torque tube and associated ribs for corrosion in accordance with SB No. 1105A.

3. If corrosion damage is detected:

Replace the rib/rudder torque tube assembly; or,

b. Repair the damaged torque tube using an approved repair design. FAA AD 2003-24-07 paragraph (f) specifies repair issues to be addressed.

Note: FAA AD 2003-24-07 Amdt 39-13376 refers.

Piper PA-31 Series Aeroplanes

AD/PA-31/130 (continued)

Compliance: 1. Within 150 hours time in service after 19 February 2004, unless already accomplished.

2. Before further flight after accomplishment of Requirement 1, and thereafter at intervals not to exceed 12 calendar months.

3. Before further flight after any Requirement 2 inspection where corrosion damage is detected.