| AD Number | 87-24-04 | Status | Active |
| Effective Date | December 24, 1987 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-5771 |
| 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 B2-1A A300 B2-1C A300 B2-203 A300 B2K-3C A300 B4-103 A300 B4-203 A300 B4-2C |
87-24-04 AIRBUS INDUSTRIE: Amendment 39-5771. Applicable to Model A300 series airplanes, Serial Number 1 through Serial Number 107, certificated in any category. Compliance required as indicated, unless previously accomplished.
To prevent decompression of the airplane, accomplish the following:
A. Prior to the accumulation of 24,000 landings or 12 years since first revenue flight, whichever occurs first, modify the fuselage lap splices in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986.
B. For airplanes with more than 9 years since first revenue flight as of the effective date of this AD: The modification required by paragraph A., above, may be deferred not to exceed 26,000 landings or 15 years since first revenue flight, whichever occurs first, provided the conditions specified in paragraph 1.B. of Airbus Service Bulletin A300-53-206, dated December 1, 1986, are met.
C. For airplanes which have had lap splices repaired, as noted below, accomplish the following, as applicable:
1. For airplanes repaired with an external doubler in accordance with Chapter 53-10-20, Revision 46 of the Structural Repair Manual: Inspect the repaired area for corrosion when the modification required by paragraph A., above, is accomplished. If there is any sign of corrosion, remove the repair and modify prior to further flight, in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986.
2. For airplanes repaired by cutout in accordance with Chapter 53-10-20 of the Structural Repair Manual, figure 701, sheet 2, Revision dated July 1, 1986, or previous issues; or repaired by cutout in accordance with the Structural Repair Manual Chapter 53-10-20, figure 701, sheet 3, Revision dated January 30, 1985, or previous issues, and where cutout repair exceeds half a frame bay: Prior to the accumulation of 16,000 landings since the repairs were installed, modify the repaired lap splices in accordance with FAA-approved methods.
3. For airplanes repaired in accordance with Airbus Service Bulletin 53-215 or 53-216: No further action is necessary in the repaired areas.
D. Modification of the longitudinal lap joints in Sections 13 and 14 in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986, constitutes terminating action from the inspections required by AD 85-07-09 for the splices which have been modified.
E. An alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.
F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of 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 becomes effective December 24, 1987.