AD/STRIKEMASTER/2 - Control Column Cracking
1AD/STRIKEMASTER/2 - Control Column Cracking
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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BAe (BAC 167) Strikemaster Series Aeroplanes
AD/STRIKEMASTER/2 Control Column Cracking 12/96 DM
Applicability: BAe BAC 167 Strikemaster all Mks.
Requirement: 1. Inspect the control column in accordance with BAe CSTM/SM/156.
- Inspect by NDI, the control column lugs for cracks in accordance with BAe CSI/STRIKEMASTER/51.
Note: UK CAA Mandatory Permit Directive 1995-108 refers.
Compliance: 1. Unless already accomplished, before further flight after 25 September 1996.
- Within 150 hours time in service or 28 days after 25 September 1996, whichever occurs last, after the initial inspection in accordance with Requirement 1; thereafter at intervals not exceeding 150 hours time in service.
Background: A case has occurred where the upper part of the Post Mod 1759 control column has cracked at the aft lug, which forms part of the column top to base pivot point. As a result, permit holders are required to assure the integrity of the control column structure through ensuring that Requirement 1. has been carried out, and continuing to inspect thereafter.