Commonwealth legislation

AD/R22/50 - Tail Rotor Pitch Control Assembly

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

Requires operators of certain Robinson R22 helicopters (specified serial numbers with tail rotor pitch control assembly P/N A031‑1 Rev J or earlier) to hand‑rotate and inspect the tail rotor pitch control assembly for roughness or binding and to replace it if it does not rotate freely. (Applicability; Requirement).

Initial inspection is due within 20 hours TIS from 26 March 2003, then every 300 hours or 12 months; CASA enforces the AD under CAR 1998. Owners/operators pay for inspections and replacements. (Compliance; Background).

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Current sections

Direct links to the current provisions in AD/R22/50 - Tail Rotor Pitch Control Assembly.

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 issues the following Airworthiness Directive (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.

Robinson R22 Series Helicopters

AD/R22/50 Tail Rotor Pitch Control Assem

AD/R22/50 Tail Rotor Pitch Control Assembly 4/2003

Applicability: Model R22 helicopters, with serial numbers up to and including 3328, except serial numbers 3167, 3326, and 3327, with tail rotor pitch control assembly, part number A031-1, Revision J or prior, installed.

Requirement: Inspect the tail rotor pitch control assembly for roughness or binding of the pitch control bearings by hand-rotating the pitch control bearing housing in accordance with Robinson Helicopter Company Service Bulletin SB-90A Revision A, dated 10 June 2002.

If the housing does not rotate freely, before further flight, replace the unserviceable pitch control assembly with a serviceable assembly.

Note: FAA AD 2003-04-04 Amdt 39-13052 refers.

Compliance: Within 20 hours time in service after 26 March 2003 for the initial inspection, unless already accomplished. Inspect thereafter at intervals not to exceed 300 hours time in service or 12 months, whichever occurs first.

This Airworthiness Directive becomes effective on 5 March 2003.

Background: The FAA received reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on Model R22 helicopters. Undetected bearing corrosion could lead to bearing failure and subsequent loss of directional control of the helicopter.

Signature of David Alan Villiers Delegate of the Civil Aviation Safety Authority

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 27 February 2003

View image in the official source

The above AD is notified in the Commonwealth of Australia Gazette on 5 March 2003.

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

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 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.

Robinson R22 Series Helicopters

AD/R22/50 Tail Rotor Pitch Control Assem AD/R22/50 Tail Rotor Pitch Control Assembly 4/2003

AD/R22/50 Tail Rotor Pitch Control Assembly 4/2003

If the housing does not rotate freely, before further flight, replace the unserviceable pitch control assembly with a serviceable assembly.

Note: FAA AD 2003-04-04 Amdt 39-13052 refers.

This Airworthiness Directive becomes effective on 5 March 2003.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 27 February 2003

The above AD is notified in the Commonwealth of Australia Gazette on 5 March 2003.