Commonwealth legislation

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

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires operators of Bombardier DHC‑8 Models 102 and 103 (S/N 101–180 with de Havilland Mod 8/0427) that have exceeded 15,543 landings to clean and visually inspect a specified fuselage skin area and to carry out an internal frame/skin inspection under the manufacturer's Structural Inspection Program. Completing the internal inspection ends the AD's requirements.

It was issued to restore the intended inspection intervals after a maintenance‑program wording error; operators meet specified flight‑count deadlines, bear the inspection costs, and must follow Service Bulletin 8‑53‑48 and PSM Task 5310/30C.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/DHC-8/37 Amdt 1 - Fuselage Skin and Frames at Floor Level.

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

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
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.

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.

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.

Background: In an early issue of the manufacturer’s Maintenance Program Airworthiness Limitations List, one if the tasks included a misleading remark about the task effectively. Consequently, on post Modification 8/0427 aircraft the fuselage frames may not have been inspected at the intervals intended. This out-of-sequence inspection will bring the affected aircraft into compliance with the current airworthiness limitations. Amendment 1 corrects a typographical error in the Applicability and adds the current note to the Compliance paragraph.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

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