AD/Cap 10/13 Flight Controls Tie Rod Bolts (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(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.

Avions Mudry Cap Series Aeroplanes

AD/CAP 10/13 Flight Controls Tie Rod Bolts 6/2008 DM

Applicability:

Model CAP 10B aircraft, serial numbers 300 through 317, and aircraft that have embodied APEX change 000302 - carbon fibre wing spars (trademarked as CAP 10C).

Requirement:

1.    Remove tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038 and replace them with tie rod bolts part number 95.56.11.418 and spacers part number 11.56.27.138, in accordance with the accomplishment instructions of APEX AIRCRAFT Service Bulletin 040206, original issue, or later EASA approved revision.

2.    No person shall install, on any aircraft, tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038.

Note:  EASA AD 2008-0060 refers.

Compliance:

For Requirement 1. - Within 50 flight hours after the Effective Date of this Airworthiness Directive, unless already accomplished.

For Requirement 2. - After the Effective Date of this Airworthiness Directive.

This Airworthiness Directive becomes effective on 15 April 2008.

Background:

The manufacturer has determined that the flight controls tie rod bolts currently installed on CAP 10B aircraft are not in accordance with design data.  The bolt shank length was found to be too short, and additionally, the material properties of the spacers have been found to be inadequate for the prescribed torque value.  Excessive wear on the threads of the bolts could result in play in the flight control, with consequent control surface vibration.

David Punshon
Delegate of the Civil Aviation Safety Authority

7 April 2008