AD/DHC-8/54 Amdt 2 - Fuselage Cable Trough
1AD/DHC-8/54 Amdt 2 - Fuselage Cable Trough
Start here
Get a plain-English read of 1
Turn the raw legal text into a practical explanation grounded in AD/DHC-8/54 Amdt 2 - Fuselage Cable Trough.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text
Image unavailable in extracted text
Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes
AIRWORTHINESS DIRECTIVE
Image unavailable in extracted text
Image unavailable in extracted text
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/DHC-8/54 Amdt 1 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
AD/DHC-8/54
Amdt 2
Fuselage Cable Trough 10/2000
Applicability: DHC-8 aeroplanes Models 102, 103, 106, 201, 202, 301, 311, 314 and 315 with serial
numbers 3 through 540 inclusive, excluding serial number 462.
Requirement: Inspect the wiring in the underfloor cable trough and incorporate Bombardier Modification 8/2705 in accordance with the following Bombardier Inc de Havilland Dash 8 Service Bulletins:
| Model | Service Bulletin | Date of Issue |
|---|---|---|
| 102, 103, 106, 201 and 202 | 8-53-66and8-53-80 | 27 March 1998 and22 December 1999 |
| 301, 311, 314 and 315 | 8-53-66 | 27 March 1998 |
Note: Transport Canada AD CF-98-08 R2 refers.
Compliance: The compliance remains unchanged as ‘At the next ‘C’ check, but no later than 36 months after 18 June 1998 (the effective date of the original issue of this Directive)’.
This Amendment becomes effective on 5 October 2000.
Background: A DHC-8 aeroplane experienced an uncommanded engine shut-down in flight due to a short circuit between adjacent wires located in the left underfloor cable trough. The short circuit resulted in a 28 volt signal being applied to the fuel shut-off valve. An investigation revealed that the short circuit was caused by chafing of wires on sharp edges on the cherrymax rivets in the cable trough.