AD/CASA/28 Outer to Centre Wing Attachment Fittings (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.

Casa 212 Series Aeroplanes

AD/CASA/28 Outer to Centre Wing Attachment Fittings 2/2007 TX

Applicability:

Model C-212-DF and C-212-EE aircraft, serial numbers 444 through 477, except if EADS-CASA AOL 212-010 Revision 1 or Revision 2 has been previously accomplished on both upper and lower fittings in both outer and centre wings on both left and right hand sides of the aircraft.

Requirement:

1.    Inspect the eight upper and lower fittings in both outer and centre wings on both left and right hand sides of the aircraft to verify the fitting material, in accordance with EADS-CASA COM 212-303 original issue.

For fittings verified to be made of 2024-T42 (L-3140-T42) alloy material, no further action is required.

2.    For fittings verified to be made of 7050-T7451 (L-3767-T7451), remove the affected outer wing and perform a one-time inspection in accordance with EADS-CASA COM 212-301 Revision 1 and EADS-CASA COM 212-302 Revision 1.

If a crack is detected during the Requirement 2 inspection, before further flight, replace the affected fitting.

Note:  EASA Emergency AD 2006-0359-E refers.

Compliance:

1.    Before further flight after 1 December 2006.

2.    Before further flight.

This Airworthiness Directive becomes effective on 1 December 2006.

Background: Cracks were discovered in outer to centre wing attachment fittings during final assembly of a production aircraft, and also in several in-service aircraft.  Investigation revealed the cracking was caused by a defective manufacturing process at the supplier facility.  This condition, which involves fittings that are principal structural elements, could result in reduced structural integrity of the aircraft unless detected and corrected.

David Villiers
Delegate of the Civil Aviation Safety Authority

30 November 2006