Commonwealth legislation

AD/BEECH 56/29 - Elevator Control Fittings

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires owners/operators of Beechcraft 56TC (S/N TG‑2–TG‑83) to identify whether elevator control fittings are aluminium or magnesium; if magnesium, inspect per Beechcraft Mandatory Service Bulletin 2242 Rev 1 and replace any cracked fittings with aluminium (installation of aluminium fittings terminates the directive).

Compliance is due within 100 hours’ time‑in‑service or at the next scheduled Maintenance Release after 30 Nov 1989, and every 100 hours thereafter until aluminium fittings are fitted. Owners/operators pay inspection and replacement costs; maintenance personnel must follow the Bulletin. The FAA reported magnesium fitting cracking and possible in‑flight failure.

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/BEECH 56/29 - Elevator Control Fittings.

AD/BEECH 56/29 - Elevator Control Fittings

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
Beechcraft 56TC (Turbo Baron) Series Aeroplanes

AD/BEECH 56/29 Elevator Control Fittings 12/89

Applicability: Models 56TC with S/Nos TG-2 through TG-83.

Requirement: 1. Determine the composition (aluminium or magnesium) of the elevator control fittings in accordance with Beechcraft Mandatory Service Bulletin 2242 Revision

If the fittings are determined to be aluminium, no further action is required by this Directive.

2. If the fittings are determined to be magnesium, visually inspect in accordance with Beechcraft Mandatory Service Bulletin 2242 Revision 1. Cracked fittings are to be replaced with aluminium fittings before further flight.

Note 1: The installation of aluminium fittings is considered terminating action for this Directive.

Note 2: FAA AD 89-05-02 refers.

Compliance: 1. Prior to exceeding 100 hours’ time in service after 30 November 1989, or at the next scheduled inspection for issue of Maintenance Release after 30 November 1989, whichever occurs later.

Prior to exceeding 100 hours’ time in service after 30 November 1989, or at the next scheduled inspection for issue of Maintenance Release after 30 November 1989, whichever occurs later, and thereafter at intervals not exceeding 100 hours’ time in service, until aluminium fittings are installed.

Background: Country of origin AD. The FAA has received reports of cracking and also failure of magnesium elevator control fittings. In-flight failure could result in loss of the aircraft.

Source text

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

1 AD/BEECH 56/29 - Elevator Control Fittings