AD 87-16-03

AD Final Rules - DRS_87-16-03.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
87-16-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2 and B4 Series Airplanes
Subject:
Wing Skin
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/04/1987
Make:
Airbus
Model:
A300 B2-1A | A300 B2-1C | A300 B2-203 | A300 B2K-3C | A300 B4-103 | A300 B4-203 | A300 B4-2C
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Superseded AD: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Superseded By: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: 87-16-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5623

AD NUMBER:   87-16-03

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2 and B4 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 4, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-16-03 AIRBUS INDUSTRIE: Amendment 39-5623. Applies to Model A300 B2 and B4 series airplanes, certificated in any category. To prevent the development of cracks which can lead to wing skin failure, accomplish the following within 90 days after the effective date of this AD, or upon reaching the threshold indicated below, whichever occurs later, unless already accomplished:

A. Inspect for cracks in the top skin of each wing at the level of rib 9 between front and rear spars, prior to the accumulation of 17,000 landings for B2 series airplanes, and prior to the accumulation of 14,200 landings for B4 series airplanes, in accordance with the accomplishment instructions of Airbus Industrie (AI) Service Bulletin A300-57-118, Revision 1, dated March 29, 1984. Thereafter, repeat the inspections at intervals not to exceed 7,600 landings.

B. If cracks are found during the inspections required by paragraph A., above, follow procedures described in Paragraph 1.C.(5) of AI Service Bulletin A300-57-118, Revision 1, dated March 29, 1984.

C. Incorporation of AI Modification 2099, as described in Airbus Service Bulletin A300-57-077, Revision 1, dated December 15, 1979, which replaces clearance fit HI-LOK bolts with taperlock bolts, constitutes terminating action for the inspection requirements of this AD.

D. 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, Northwest Mountain Region.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections required by this AD.

All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Centrecda, Avenue Didier Daurat, 31700 Blagnac, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This amendment becomes effective September 4, 1987.

FOOTER: