AD 84-03-08

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AD Number:
84-03-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Airplanes
Subject:
Main Landing Gear Hinge Arms
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/19/1984
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Superseded AD: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Superseded By: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: 84-03-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4806

AD NUMBER:   84-03-08

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 19, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-03-08 AIRBUS INDUSTRIE: Amendment 39-4806. Applies to Model A300 airplanes, certificated in all categories and whose serial numbers are listed in paragraph 1, Planning Information, of Airbus Industrie (AI) Service Bulletin A300-32-356, Revision 1, dated December 1, 1982. To prevent failure of main landing gear hinge arms, accomplish the following unless previously accomplished:

A. Within 120 days from the effective date of this AD, measure the displacement of the bronze bushing fitted in the stirrup on the actuating cylinder side of all affected hinge arms in accordance with paragraph 2.B of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-422, Revision 1, dated December 3, 1982. Depending on the results of the above measurements and within the number of landings specified in the service bulletin, repeat the measurement of the displacement or visually inspect for corrosion, as appropriate, the blending radii of attachment between the trunnions and the hinge arm body in accordance with the instructions of the service bulletin.

1. If no trace of corrosion is found, incorporate the modifications AI 4544/S5351 and AI 4544/S5548, described in AI Service Bulletins A300-32-348, Revision 2 and A300-32-355, Revision 2, both dated May 16, 1983, and in accordance with the instructions of MHB Service Bulletins 470-32-421, Revision 2 and 470-32-407, Revision 2, both dated March 31, 1983.

2. If corrosion is detected, replace the affected hinge arms prior to further flight either with new arms or with arms modified in accordance with the instructions of MHB Service Bulletin 470-32-431, dated December 24, 1982, related to AI Service Bulletin A300-32- 362, dated June 15, 1983, after incorporating the modifications required by paragraph A.1. of this AD.

B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

C. 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 inspections and/or modifications required by this AD.

This amendment becomes effective March 19, 1984.

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