Commonwealth legislation

AD/GAF-N22/53 - Taper Pins - Control Systems

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

4/10 complexity

What it does: Requires owners/operators of Nomad N22/N24 series aeroplanes to inspect taper pins in control‑system universal joints and, for certain column joints, to carry out a specified modification in Nomad Alert SB ANMD‑27‑39. It sets short initial inspection times, recurring checks until modification, and a final deadline.

Who it affects and why it matters: Aircraft operators and maintenance organisations must inspect and modify parts to prevent taper pins working loose and potentially allowing control columns to fall free. Operators bear the inspection and modification costs; the Civil Aviation Safety Authority oversees compliance.

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/GAF-N22/53 - Taper Pins - Control Systems.

AD/GAF-N22/53 - Taper Pins - Control Systems

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
GAF N22 and N24 Series Aeroplanes

AD/GAF-N22/53 Taper Pins - Control Systems 11/88 T

Applicability: All Nomad N22, N22B, N22C, N22S, N24 and N24A aircraft.

Requirement: 1. For L.H and R.H control column universal joints fitted with taper pins, not incorporating modification N428, action in accordance with Nomad Alert SB ANMD-27-39.

For taper pins fitted to all other control systems carry out inspection for looseness or evidence of looseness.

Compliance: 1. Within 10 hours time in service after 22 August 1988 and thereafter at intervals not exceeding 100 hours time in service until modification has been carried out in accordance with Part B of Nomad Alert S.B. ANMD-27-39, but not later than 300 hours time in service after 22 August 1988 or by 22 November 1988 whichever occurs first.

Note: If taper pins are found loose or with evidence of looseness, modification must be carried out before further flight.

Within 100 hours time in service after 22 August 1988 or at the next scheduled inspection for Maintenance Release issue after 22 August 1988, whichever occurs first. Thereafter at each inspection for Maintenance Release, unless modified in accordance with a scheme approved by the Authority.

Background: Excessive free movement of control column in service was caused by taper pin working loose at universal joint with the possibility of falling free.

Source text

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

1 AD/GAF-N22/53 - Taper Pins - Control Systems