AD/DHC-8/37 Amdt 1 - Fuselage Skin and Frames at Floor Level (Cth)

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES

Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes

AD/DHC-8/37 Amdt 1

Fuselage Skin and Frames at Floor Level 7/95

Applicability: DHC-8 aircraft Models 102 and 103, Serial Numbers 101 to 180 inclusive, with de Havilland Modification 8/0427 incorporated which have exceeded 15543 landings at 25 May 1995 and which have not been inspected in accordance with the Maintenance Program Manual PSM 1-8-7 Task 5310/30C (Section 3-53, Page 12 dated 10 August 1993).

Requirement: 1. Thoroughly clean the external fuselage skin from fuselage station X253.00 to X653.349 from stringer 20 to stringer 24. Perform a detailed visual inspection of the area for cracking in accordance with de Havilland Service Bulletin 8-53-48.

2. Internally inspect the fuselage frames and skin in accordance with PSM 1-8-7, Structural Inspection Program Task 5310/30C (Section 3-53 page 12 dated 12 August 1993).

Accomplishment of the internal inspection terminates the Requirements of this Directive.

Note: Transport Canada AD CF-94-17 refers.

Compliance: 1. Initially inspect in accordance with Requirement 1 within 200 flights after 27 April 1995. Repeat the inspections at intervals not to exceed 769 flights.

2. Inspect in accordance with Requirement 2 before 31086 flights or before further flight if cracks are found as a result of Requirement 1 inspection.

Note: Aircraft which have been inspected internally in accordance with PSM 1-8-7 Task 5310/30C revert to the on-going inspection requirements of the PSM.

Amendment 1 makes no change to the technical requirements of this Directive.