AD 82-03-08

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AD Number:
82-03-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes
Subject:
Main Landing Gear Hinge Arms
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/15/1982
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Superseded AD: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Superseded By: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: 82-03-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4307

AD NUMBER:   82-03-08

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

ACTION:  

SUMMARY:  

DATES:   Effective February 15, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-03-08 AIRBUS INDUSTRIE: Amendment 39-4307. Applies to Model A300 series airplanes, certificated in all categories, with main landing gear hinge arms, P/N C65-381-2, which have accumulated more than 2,500 takeoff/landing cycles and which have not been modified in accordance with Airbus Industrie Service Bulletin No. A300-32-118, dated August 21, 1979.

Compliance required as indicated, unless already accomplished.

To prevent failure of the main landing gear hinge arms, accomplish the following:

(a) Within the next 8 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 12 hours time in service from the last inspection, but at least once each operating day, visually inspect the main landing gear hinge arms, P/N C65-381-2, for cracks in accordance with Airbus Industrie All Operators Telex AOT 32/80/105/SC1/0644/EM/AK/ME, dated March 21, 1980, and AOT 32/80/107/SC1/0795/EM/AK/ME, dated April 8, 1980, or FAA approved equivalents. Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)

NOTES: 1. Compliance times specified in Airbus Industrie All Operators Telex AOT 32/80/105/SC1/0644/EM/AK/ME, dated March 21, 1980, and AOT 32/80/107/SC1/0795/EM/AK/ME, dated April 8, 1980, are not applicable to this AD.

2. Pay particular attention to -

(a) the inner edge of the hinge arm fork and the inner upper and lower edge between the LH and RH attachment lugs.

(b) the hinge arm between the fork webs and cylindrical lugs or MLG actuator attachments.

(c) the surrounding area of the cylindrical attachment lugs.

(b) If the inspection required by paragraph (a) of this AD reveals cracks in a hinge arm, prior to further flight, replace the affected hinge arm with a serviceable hinge arm, P/N C65- 381-2 or P/N C65-381-4, in accordance with Airbus Industrie Service Bulletin No. A300-32-118. Repetitive inspections may be discontinued upon installation of P/N C65-381-4 hinge arms.

(c) Prior to February 15, 1982, unless already accomplished, perform the visual and ultrasonic inspections, rework, and modification specified in Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent. Repetitive inspections are required as follows:

(1) If the depth of the corrosion pitting on the hinge arm does not exceed 0.008 inches, within sixty (60) days from accomplishment of the inspection required by Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent, and thereafter at intervals not to exceed 120 days, ultrasonically inspect the hinge arm in accordance with Airbus Industrie Service Bulletin No. A300-32-288, dated May 19, 1980, or an FAA-approved equivalent.

(2) If the depth of the corrosion pitting on the hinge arm exceeds 0.008 inches, within thirty (30) days from accomplishment of the inspection required by Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent, and thereafter at intervals not to exceed thirty (30) days, ultrasonically inspect the hinge arms in accordance with Airbus Industrie Service Bulletin No. A300-32-288, dated May 19, 1980, or an FAA-approved equivalent.

(d) Cracked hinge arms must be replaced prior to further flight.

(e) Accomplishment of paragraph (c) of this AD terminates the visual inspection requirements of paragraph (a).

(f) Airplanes may be ferried in accordance with FAR Sections 21.197 and 21.199 to a place where the inspections and or repairs can be made in order to comply with this AD.

(g) Upon request of an operator and submission of substantiating data, the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, may upon recommendation of the cognizant FAA aviation safety inspector, adjust the inspection intervals.

(h) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.

All persons affected by this directive who have not already received the referenced documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, B.P. 33, 31700 Blagnac, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591.

This amendment amends telegraphic AD T80EU16, as amended by telegraphic AD T80EU16A.

This amendment becomes effective February 15, 1982.

FOOTER: