Commonwealth legislation

AD/BELL 204/10 Amdt 1 - Tail Rotor Blade Grip

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Commonwealth

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legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires operators of Bell 204 helicopters with certain tail rotor hubs to inspect specific tail rotor blade grip assemblies (P/N 204‑011‑728 or 204‑011‑706) for minimum hardness or conductivity, using Rockwell or Eddy‑current testers. The inspection must be completed before the aircraft flies again or before a grip is installed. It is intended to prevent grip failure; the compliance timing and testing methods are specified in the AD and impose testing costs and maintenance time on operators and maintenance providers.

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Current sections

Direct links to the current provisions in AD/BELL 204/10 Amdt 1 - Tail Rotor Blade Grip.

AD/BELL 204/10 Amdt 1 - Tail Rotor Blade Grip

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
View image in the official source
Bell Helicopter Textron 204 Series Helicopters

AIRWORTHINESS DIRECTIVE

View image in the official source

View image in the official source
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BELL 204/10 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/BELL 204/10

Amdt 1

Tail Rotor Blade Grip 8/2000

Applicability: All models 204 fitted with tail rotor hub P/N 204-011-801-5 or -7; or P/N 204-011- 701-11 or -13 or -19.

Requirement: Inspect the P/N 204-011-728 or P/N 204-011-706 tail rotor blade grip assemblies for minimum hardness of:

Rockwell 79 on "B" Scale or

b. below a conductivity of 39 on the international annealed copper standard.

Reading should be taken adjacent top the vibro etched serial number between the blade retention bolts and the grip face.

The test may be accomplished using a Rockwell Hardness tester or Eddy Current tester Magnates FM120 or equivalent.

Note: FAA AD 70-6-2 refers.

Compliance: Before further flight after 3 March 1970, and before installation on an aircraft.

This Amendment becomes effective on 10 August 2000.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Background: This Directive was initially issued to prevent failure of the Subject grip assemblies.

Amendment 1 is issued to provide the country of manufacture AD reference, and to prevent any existing deficient grips from returning to service. It also follows the re- introduction of the AD Series after sixteen years.

The original issue of this Airworthiness Directive became effective on 3 March 1970.

View image in the official source

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 6 July 2000

View image in the official source

The above AD is notified in the Commonwealth of Australia Gazette on 12 July 2000.

Source text

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

1 AD/BELL 204/10 Amdt 1 - Tail Rotor Blade Grip

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Bell Helicopter Textron 204 Series Helicopters

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BELL 204/10 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/BELL 204/10

Amdt 1

Tail Rotor Blade Grip 8/2000

Applicability: All models 204 fitted with tail rotor hub P/N 204-011-801-5 or -7; or P/N 204-011- 701-11 or -13 or -19.

Requirement: Inspect the P/N 204-011-728 or P/N 204-011-706 tail rotor blade grip assemblies for minimum hardness of:

Rockwell 79 on "B" Scale or

b. below a conductivity of 39 on the international annealed copper standard.

Reading should be taken adjacent top the vibro etched serial number between the blade retention bolts and the grip face.

The test may be accomplished using a Rockwell Hardness tester or Eddy Current tester Magnates FM120 or equivalent.

Note: FAA AD 70-6-2 refers.

Compliance: Before further flight after 3 March 1970, and before installation on an aircraft.

This Amendment becomes effective on 10 August 2000.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Background: This Directive was initially issued to prevent failure of the Subject grip assemblies.

The original issue of this Airworthiness Directive became effective on 3 March 1970.