AD 82-01-03

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AD Number:
82-01-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes
Subject:
Aft Cargo Door Frames
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/25/1982
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Superseded AD: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Superseded By: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: 82-01-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4287

AD NUMBER:   82-01-03

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

ACTION:  

SUMMARY:  

DATES:   Effective January 25, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-01-03 AIRBUS INDUSTRIE: Amendment 39-4287. Applies to Model A300 series airplanes, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To prevent failure of the aft cargo door frames 67 and 69, accomplish the following:

(a) Within the next 550 hours time in service after the effective date of this AD, unless already accomplished within the last 1450 hours time in service, inspect the rear cargo compartment door frame external flanges in accordance with paragraph 2.B.(1) of Airbus Industrie A300 Service Bulletin A300-53-108, Revision 1, dated October 15, 1979 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent.

(b) If no cracks are found during the inspection required by paragraph (a) of this AD:

(1) The airplane may be returned to service; and

(2) Repeat the inspection in paragraph (a) of this AD at intervals not to exceed 2000 hours time in service from the last inspection.

(c) If, during the inspection required by paragraph (a) of this AD, the total number of cracks found does not exceed 5, or the total length of all cracks found does not exceed 2 inches:

(1) The airplane may be returned to service; and

(2) Repeat the inspection in paragraph (a) of this AD at intervals not to exceed 550 hours time in service from the last inspection.

(d) If, during the inspection required by paragraph (a) of this AD, the total number of cracks found exceeds 5, or the total length of all cracks found exceeds 2 inches, inspect the adjacent internal flange on the forward side of frame 67 and the aft side of frame 69 in accordance with paragraph 2.B.(2)(b) of the Service Bulletin, or an FAA-approved equivalent.

(e) If no cracks are found on the internal flanges during the inspection required by paragraph (d) of this AD:

(1) The airplane may be returned to service; and

(2) Repeat the inspections in paragraphs (a) and (d) of this AD at intervals not to exceed 550 hours time in service from the last inspection.

(f) If, during inspection of the internal flanges required by paragraph (d) of this AD, the total number of cracks found does not exceed 5, or the total length of all cracks does not exceed 2 inches:

(1) The airplane may be returned to service; and

(2) Repeat the inspections in paragraphs (a) and (d) of this AD at intervals not to exceed 200 hours time in service from the last inspection.

(g) If, during the inspection of the internal flanges required by paragraph (d) of this AD, the total number of cracks found exceeds 5, or the total length of all cracks exceeds 2 inches, before further flight, except as provided in paragraph (i) of this AD, replace the frame in accordance with paragraph 2, "Accomplishment Instructions," of Airbus Industrie A300 Service Bulletin A300-53-109, Revision 4, dated April 25, 1980, or an FAA-approved equivalent.

(h) The inspections and repetitive inspections required by this AD may be discontinued when rear cargo door frames 67 and 69 have been replaced in accordance with Airbus Industrie A300 Service Bulletin A300-53-109, Revision No. 4, dated April 25, 1980, or an FAA- approved equivalent.

(i) In accordance with FAR Sections 21.197 and 21.199 the airplane may be flown to a base where the maintenance required by this AD may be accomplished.

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

(k) Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, may adjust the inspection intervals.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, BP 33, 31700 Blagnac, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591.

This amendment becomes effective January 25, 1982.

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