Document ID: chunk:federal_register_of_legislation:F2006B08593:body:0:p2
Version: federal_register_of_legislation:F2006B08593
Segment Type: other
Provision Reference: 
Character Range: 3115–4605

of the web are visually confirmed to be crack free; and,

c.         No crack extends under the angles; and,

d.         Aircraft shall be re- inspected at intervals not exceeding 100 flight cycles; and,

e.         The cracked bulkhead is to be repaired before the aircraft accumulates 600 flight cycles or within 12 months, whichever occurs first, after the date of initial detection of the crack.

            The compliance times remain unchanged by this issue. This amendment becomes effective on 11 July 2002.
            Background: A check of 105 Challenger aircraft has revealed 13 aircraft with fatigue cracks in the pressure bulkhead frame at the forward end of the wing box cutout.

Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes

 AD/CL-600/32 Amdt 2 (Continued)

            Amendment 1 deleted a specific repair date.

            Amendment 2 is issued in response to a revision of the related Transport Canada AD, which introduces a modification that provides terminating action for the repeat inspection requirements for those aircraft that have never developed cracks.
            Amendment 1 of this Airworthiness Directive became effective on 3 December 1998. The original issue of this Airworthiness Directive became effective on
            5 November 1997.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 30 May 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 19 June 2002.