# AD 93-16-10: Inspect To Detect Fatigue Cracking

- Type: Airworthiness directive
- Status: Historical
- Products: Airbus A320 Series (all)
- Effective: October 13, 1993
- Superseded by: [AD 2005-20-35](https://openairdocs.org/ad/2005-20-35)
- Product type: Aircraft, Large airplane
- Amendment: 39-8667
- Docket: 93-NM-34-AD
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/21D7892268D2F7358625695E006EF189.0001
- DRS record last changed: August 7, 2025
- Page: https://openairdocs.org/ad/93-16-10

## The airworthiness directive

93-16-10 AIRBUS INDUSTRIE: Amendment 39-8667. Docket 93-NM-34-AD.

Applicability: Model A320 series airplanes having manufacturer's serial numbers (MSN) 002 through 021 inclusive, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To detect fatigue cracking in the upper stringer which may result in loss of structural integrity, accomplish the following:

  (a) Prior to the accumulation of 10,000 total landings after the effective date of this AD, perform a detailed visual inspection to detect cracks in the front and rear faces and at the crown fittings of the upper stringers of the center wing box between frame (FR)36 and FR42, in accordance with Airbus A320 Service Bulletin No. A320-57-1030, dated August 12, 1991.

NOTE 1: Particular attention should be paid to the strut fittings and reinforcing plate ends when performing this inspection. (1) If no crack is found, repeat the inspection thereafter at intervalsnot to exceed 7,500 landings, in accordance with the service bulletin. (2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. Following accomplishment of this repair, no further action is required by this AD.

  (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

  (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

  (d) The inspection shall be done in accordance with Airbus A320 Service Bulletin No. A320-57-1030, dated August 12, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

  (e) This amendment becomes effective on October 13, 1993.

## Registered aircraft it may apply to (OpenAirDocs)

No registered aircraft matched the models it names.

## Related documents

- [AD 2005-20-35](https://openairdocs.org/ad/2005-20-35): Center wing box · Airbus A320-111. Effective Oct 27, 2005. Supersedes this AD

Its text cites no advisory circulars or STCs.

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