Commonwealth legislation

AD/AA-5/27 Amdt 1 - Wing Attach Shoulder Bolts

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This airworthiness directive requires owners/operators of Gulfstream (Grumman American/American Aviation) AA-5, AA-5A, AA-5B and AG-5B aeroplanes to remove, non-destructively inspect (Magnaflux or fluorescent dye) and replace wing-attach shoulder bolts in line with American General Aviation SB-185, then repeat inspections at 500‑hour intervals. Compliance deadlines are measured by bolt time in service. It matters because a cracked or fractured shoulder bolt can undermine structural integrity and flight control.

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AD/AA-5/27 Amdt 1 - Wing Attach Shoulder Bolts

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Gulfstream (Grumman American/ American Aviation) AA-5 Series Aeroplanes

AD/AA-5/27

Amdt 1

Wing Attach Shoulder Bolts 10/95 DM

Applicability: AA-5, AA-5A, AA-5B, and AG-5B aircraft.

Requirement: 1. Remove the subject bolts or other approved replacement bolts, in accordance with American General Aviation SB-185.

2. Inspect the bolts for cracking at the bolt shoulder using either the Magnaflux or Fluorescent Dye NDI technique and discard any bolts with indications of cracking.

3. Install bolts in accordance with the requirements of American General Aviation SB-185.

Compliance: Unless already accomplished, prior to attaining 1000 hours bolt time in service, or within 10 hours’ time in service after 23 August 1995, whichever occurs last; thereafter at intervals not exceeding 500 hours’ time in service.

Background: A MDR was received stating that a bolt had been found cracked when inspected using magnaflux, instead of visually, in accordance with the Requirement document. The defect was highlighted in the AAC Major Defect Summary. However, subsequent laboratory examination of the bolt has revealed that the fatigue cracking could be attributable to the rapid change in section at the shoulder and the sharp edge revealed at X230 magnification.

Failure of a shoulder bolt may compromise the structural integrity of an aircraft and could result in a loss of flight control.

Amendment 1 is raised as the result of a random inspection of a second aircraft where one of the bolts was found to be fully fractured.

Source text

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

1 AD/AA-5/27 Amdt 1 - Wing Attach Shoulder Bolts