AD/HU 369/114 - Forward and Centre Thruster Control Cable Assemblies Connector
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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AIRWORTHINESS DIRECTIVE
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For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 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.
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McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters
AD/HU 369/114 Forward and Centre Thruster Control Cable
Assemblies Connector
12/2004
DM
Applicability: Model 500N helicopters, serial numbers LN001 through LN099, and equipped with forward thrusters cable assembly part number 500N7201-55, and centre cable assembly part number 500N7201-57.
Model 600N helicopters, serial numbers RN003 through RN068, and equipped with forward thrusters cable assembly part number 500N7201-55, and centre cable assembly part number 500N7201-59.
Requirement: Inspect in accordance with the Accomplishment Instructions of MD Helicopters Inc.
Service Bulletin SB500N-027 or SB600N-042, as applicable.
If inspection results reveal corrosion pitting or cracking, before further flight, replace the affected cable assembly with a serviceable cable assembly.
Note: FAA AD 2004-20-08 Amdt 39-13813 refers.
Compliance: Within 10 hours time in service or 30 days after 20 October 2004, whichever occurs first.
This Airworthiness Directive becomes effective on 20 October 2004.
Background: A report was received of a fractured inner female connector on a forward thruster control cable assembly due to stress corrosion cracking. An undetected corrosion- pitted or cracked connector could result in failure of the cable assembly and subsequent loss of control of the helicopter.
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David Villiers
Delegate of the Civil Aviation Safety Authority 14 October 2004
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The above AD is notified in the Commonwealth of Australia Gazette on 20 October 2004.
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