| AD Number | 89-03-14 | Status | Active |
| Effective Date | March 07, 1989 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-6125 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Airbus |
| Model(s) | A300 B4-601 A300 B4-603 A300 B4-605R A300 B4-620 A300 B4-622 A300 B4-622R A300 C4-605R Variant F A300 F4-605R A300 F4-622R |
89-03-14 AIRBUS INDUSTRIE: Amendment 39-6125.
Applicability: Model A300-600 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988.
Compliance: Required as indicated, unless previously accomplished.
To prevent separation of the rear passenger/crew door from the airplane and subsequent rapid decompression, accomplish the following:
A. Prior to the accumulation of 8,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect frame 73A RH and LH between beams 5 and 7 in accordance with Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988.
1. If cracks are detected that are less than 0.4 inch, modify the frame within the next 2,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 1,250 landings until the modification is accomplished.
2. If cracks are detected that are equal to or more than 0.4 inch but less than 0.8 inch, modify the frame within the next 1,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 750 landings until the modification is accomplished.
3. If cracks are detected that are equal to or more than 0.8 inch, prior to further flight, modify the frame in accordance with Airbus Industrie Service Bulletin A300-53- 6019, Revision 3, dated October 13, 1988.
4. If no cracks are detected, repeat the inspection at intervals not to exceed 4,000 landings.
B. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification of the door frame structure in accordance with Airbus Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988.
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, Northwest Mountain Region.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it 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 for the accomplishment of inspections and/or modifications required by 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, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.
This amendment (39-6125, AD 89-03-14) becomes effective March 7, 1989.