Document ID: chunk:federal_register_of_legislation:F2009L03111:body:0:p3
Version: federal_register_of_legislation:F2009L03111
Segment Type: other
Provision Reference: 
Character Range: 5924–9103

of the fluorescent penetrant inspection, conducted in accordance with either the above referenced SB or one of the SBs listed in Table 2, also meets the intent of Requirement 2 of this AD.

      Table 2
   Bombardier Alert SB A670BA-24-020  Original Issue  Dated 20 April 2005
   Bombardier Alert SB A670BA-24-020  Revision A      Dated 17 May 2005

             Bombardier Alert SB A670BA-24-020     Revision B      Dated 7 December 2006
             Hamilton Sundstrand SB ERPS10AG-24-3  Original Issue  Dated 14 April 2005
             Hamilton Sundstrand SB ERPS10AG-24-3  Revision 1      Dated 19 April 2005
             Hamilton Sundstrand SB ERPS10AG-24-3  Revision 2      Dated 14 November 2006
             Hamilton Sundstrand SB ERPS10AG-24-3  Revision 3      Dated 12 March 2009

             Following completion of Requirement 2, no further action is required and compliance with this AD is complete.

             Note 6:  Requirement 2 is only applicable if required by Requirement 1.b.iii.A. and Requirement 1.b.iv of this AD.

             Note 7:  For ADGs specified in Requirement 1.b.iii.A repeat fluorescent penetrant inspections (per Hamilton Sundstrand SB ERPS10AG-24-3) are required as part of the periodic ADG Functional Check procedure. Refer to Airworthiness Requirements, Part 2 of Maintenance Requirements Manual, Appendix A - Certification Maintenance Requirements (CMR) and the Aircraft Maintenance Manual (AMM), as follows:

                - CMR Task No. 24-23-00-102.

                - AMM Task No: 24-23-01-720-802.

             Note 8:  For ADGs specified in Requirement 1.b.iii.A  fluorescent penetrant inspection (per Hamilton Sundstrand SB ERPS10AG-24-3) is required following each future unscheduled in-flight ADG deployment, as specified in the following task:

                - AMM Task No: 05-51-19-210-801.

             Note 9:  In Hamilton Sundstrand SB ERPS10AG-24-3, the fluorescent penetrant inspection is referred to as a "Penetrant Check".

             Note 10:  Transport Canada AD CF-2009-27 dated 8 June 2009 refers.
Compliance:  For Requirements 1 and 2 - Within 1,000 flight hours or before the next scheduled ADG functional check, whichever comes first, after the effective date of this AD.

             This Airworthiness Directive becomes effective on 27 August 2009.
Background:  Two cases of a crack on a "dry" ADG (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL-600-2B19 aircraft.  The same part is also installed on CL-600-2C10,
             -2D15 and -2D24 aircraft.  Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs.  Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure.  If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls.

James Coyne
Delegate of the Civil Aviation Safety Authority

15 July 2009