90-01-10 AIRBUS INDUSTRIE: Amendment 39-6448. Docket No. 89-NM-162-AD.
Applicability: All Model A300 series airplanes, Serial Number 001 through 156, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To ensure structural integrity of the airplane, accomplish the following:
A. Inspect longitudinal lap joints for cracks as follows:
1. Inspection of "special" areas, as defined in paragraph 1.C(1) of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989.
a. Prior to the accumulation of 24,000 landings, or within 10 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection in special areas of the longitudinal lap joints, in accordance with paragraph 2.B. of the service bulletin.
b. If no cracks are found, repeat this inspection at intervals not to exceed 6,000 landings.
c. If a crack is detected, repair prior to further flight, in accordance with the service bulletin.
2. Inspection of "standard" areas, as defined in paragraph 1.C(2) of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989.
a. Prior to the accumulation of 32,000 landings, or within 10 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection of the standard areas of the longitudinal lap joints, in accordance with paragraph 2.B. of the service bulletin.
b. If no crack is found, repeat the inspection at intervals not to exceed:
(1) 6,000 landings for longitudinal lap joints with bonded doublers;
(2) 8,000 landings for longitudinal lap joints without bonded doublers.
c. If a crack is found, repair prior to further flight, in accordance with the service bulletin.
3. Inspection of modified or repaired areas, as defined in Tables 1 and 2 of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989.
a. Prior to the accumulation of the threshold values (landings since first flight) identified in Tables 1 or 2 of the service bulletin, or within 60 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection of the longitudinal lap joints in modified or repaired areas in accordance with paragraph 2.B. of the service bulletin.
b. If no crack is found, repeat the inspections at intervals not to exceed 6,000 landings for each repair solution identified in Tables 1 and 2 of the service bulletin.
c. If a crack is found, repair prior to further flight, in accordance with the service bulletin.
B. Prior to the accumulation of 24,000 landings or 15 years since new, whichever occurs first, or within 60 days after the effective date of this AD, whichever occurs later, inspect fuselage bonded inner doublers of longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and corrosion, in accordance with Airbus Industrie Service Bulletin A300-53-229, dated August 29, 1988, or Revision 1, dated April 10, 1989, or Revision 2, dated July 28, 1989.
1. If no disbonding or corrosion is found in areas other than Sections 13 and 14, no further action is required in those areas.
2. If disbonding or corrosion is found in Sections 13 and 14, repeat the inspections of these areas at intervals not to exceed 12,000 landings or 8 years since last inspection, whichever occurs first, in accordance with paragraph 1.B. of the service bulletin.
3. If disbonding is detected, repair prior to further flight, in accordance with the service bulletin.
C. Prior to the accumulation of 24,000 landings or 12 years since new, whichever occurs first, or within 60 days after the effective date of this AD, whichever occurs later, inspect fuselage bonded inner doublers of longitudinal lap joints in Sections 16 and 17 at Stringer 31 left- hand and right-hand for disbonding and corrosion, in accordance with Airbus Industrie Service Bulletin A300-53-229, Revision 2, dated July 28, 1989. Airplanes older than 12 years must be inspected within 12 months after the effective date of this AD.
1. If no disbonding or corrosion is found, no further action is required.
2. If disbonding is detected, repair prior to further flight, in accordance with the service bulletin.
D. 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 will either concur or comment, and then send it to the Manager, Standardization Branch, ANM-113.
E. 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 personsaffected 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, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington.
This amendment (39-6448, AD 90-01-10) becomes effective on February 5, 1990.