Document ID: chunk:federal_register_of_legislation:F2007L00201:body:0:p1
Version: federal_register_of_legislation:F2007L00201
Segment Type: other
Provision Reference: 
Character Range: 0–3173

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 10/10  Wing Main Spar Wooden Centre Block  3/2007 DM

Applicability:  All CAP 10B aircraft that have been fitted with major change 000302 (wood/carbon-made wing) and wood/carbon-made wings part number 11.56.00.010 with serial numbers 001 through 084.
Requirement:       1. Flick manoeuvres are prohibited on affected CAP 10B aircraft.

                   2. Inspect the spar web and fill up the surface cracks with a two component epoxy compound in accordance with the Accomplishment Instructions of Apex Aircraft Service Bulletin No. 060307 and Apex Aircraft Instruction No. 1001766, both at the latest EASA approved revision.

                   Accomplishment of Apex Aircraft Instruction No. 1001766 may only be carried out by an appropriately qualified/licensed person.

                   If any cracking or damage is detected during the inspection in either the rear or front wing spar web, before further flight, contact Apex Aircraft for a repair solution.

                   3. Install reinforcement plates 97.56.00.002 in accordance with Apex Aircraft Service Bulletin No. 060307 and Apex Aircraft Instruction No. 1001766, both at the latest EASA approved revision.

                As of the effective date of this Directive, no person shall install an Apex Aircraft wing part number 11.56.00.010 on any CAP 10B aircraft unless it has been inspected and modified in accordance with the Accomplishment Instructions of Apex Aircraft Service Bulletin No. 060307 and Apex Aircraft Instruction No. 1001766, both at the latest EASA approved revision.

                Note:  EASA AD 2007-0015 refers.
Compliance:     For Requirement 1:  As of the effective date of this Directive; until accomplishment of Requirements 2 and 3.

                For Requirements 2 and 3:  Within 50 hours after 15 March 2007, unless already accomplished.  Thereafter, inspect in accordance with the Accomplishment Instructions of Apex Aircraft Service Bulletin No. 060307 at intervals not to exceed 13 months.

             This Airworthiness Directive becomes effective on 25 January 2007.
Background:  The manufacturer received reports of recent inspections that revealed cracks in some spar wooden centre blocks.  Investigation revealed that the cracks are generated by the wood drying.  This Directive requires the installation of two reinforcement plates on the wing spar to counter the shear loading, requires implementation of corrective actions to slow