AD 91-06-18

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AD Number:
91-06-18
Document Type:
AD Final Rules
Docket Number:
90-NM-225-AD
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A310-200 Series Airplanes
Subject:
Wing Rear Spar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/22/1991
Make:
Airbus SAS
Model:
A310-203 | A310-221 | A310-222
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 91-06-18
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-225-AD

AMENDMENT:   39-6940

AD NUMBER:   91-06-18

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A310-200 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 22, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   91-06-18 AIRBUS INDUSTRIE: Amendment 39-6940. Docket No. 90-NM-225-AD.

Applicability: All Model A310-200 series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To detect cracks in the wing rear spar and prevent reduced structural integrity of the wings, accomplish the following:

A. Prior to the accumulation of 12,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) rototest inspection of the wing rear spar at certain bolt holes where the main landing gear (MLG) forward pick-up fittings are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A310-57-2046, dated March 5, 1990.
1. If no cracks are found at the first inspection and no cold working of the holes concerned is carried out, repeat the HFEC rototest inspection at intervals not to exceed 4,500 landings.
2. If no cracks are found at the first inspection and a spar life extension by cold working of the holes concerned is carried out in accordance with the paragraph 2.3.(1)(b) of the Accomplishment Instructions of the above service bulletin or Airbus Industrie Service Bulletin A310-57-2049, dated April 10, 1990; repeat the HFEC rototest inspection within the next 18,000 landings, and thereafter at intervals not to exceed 12,000 landings.

B. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Repeat the HFEC rototest inspection at an interval approved by the Manager, Standardization Branch, ANM-113.

C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113.

D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington.

This amendment (39-6940, AD 91-06-18) becomes effective on April 22, 1991.

FOOTER: