Commonwealth legislation

AD/A320/91 - Frames 43 and 44 Pressure Floor Connection

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

4/10 complexity

This airworthiness directive requires operators of specified Airbus A320 family aeroplanes (listed MSNs, excluding aircraft with Modification 20941 or Service Bulletin A320‑53‑1015 already incorporated) to inspect the bolts and fittings that join frames 43–44 to the pressure floor and to carry out Airbus‑specified corrective actions if defects are found. Operators must meet set inspection deadlines (initial and repeat intervals); the regulator enforces compliance to prevent bolt/fitting failure identified in fatigue testing.

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Current sections

Direct links to the current provisions in AD/A320/91 - Frames 43 and 44 Pressure Floor Connection.

AD/A320/91 - Frames 43 and 44 Pressure Floor Connection

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/91 Frames 43 and 44 Pressure Floor Connection 2/98

Applicability: Model A320 with MSN 005 through 008, 010 through 014, and 016 through 043, without Modification 20941 or Service Bulletin A320-53-1015 incorporated.

Requirement: 1. Inspect bolts and fittings of the frame to pressure floor connection at frames 43 and 44 in accordance with Airbus Industrie Service Bulletin A320-53-1083 revision 2.

2. If bolts are found cracked and/or missing and/or fittings are cracked, apply the corresponding inspection program and corrective actions in accordance with the instructions given in Service Bulletins A320-53-1083 revision 2 and A320-53- 1015.

3. If no crack is detected on the frames and bolts, repeat the inspection as defined in Requirement 1 of this Directive.

Note: DGAC AD 97-316-110 (B) refers.

Compliance: 1. Before the accumulation of 20,000 flights.

2. At the thresholds and intervals specified in the Requirement 2 documents.

3. At intervals not to exceed 5,100 flights after initial inspection. This airworthiness directive becomes effective on 29 January 1998.

Background: During a full scale fatigue test, a bolt at frame 43, which connects the frame segment with the pressure floor, sheared off. A crack developed after further simulated flights.

Source text

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

1 AD/A320/91 - Frames 43 and 44 Pressure Floor Connection