55 FR 261-01, 1990 Page 1

RULES and REGULATIONS

DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 89-NM-162-AD; Amdt. 39-6448]

Airworthiness Directives; Airbus Industrie Model A300 Series Airplanes

Thursday, January 4, 1990

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain 

Airbus Industrie Model A300 series airplanes, which requires repetitive inspections for disbonding and corrosion; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints 

for cracks; and repair, if necessary. This amendment is prompted by full-scale fatigue testing 

which has identified certain structural components which are prone to fatigue cracks. This condition, if not corrected, could result in reduction of the structural integrity of these airplanes.

DATE: Effective February 5, 1990.

ADDRESSES: The applicable service information may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information 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.

FOR FURTHER INFORMATION CONTACT: Mr. Greg Holt, Standardization Branch, ANM113; telephone (206) 431-1918. Mailing address: FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation 

Regulations to include a new airworthiness directive, applicable to certain Airbus Industrie Model A300 series airplanes, which requires repetitive inspections for disbonding and corrosion; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracks; and repair, 

if necessary, was published in the Federal Register on October 25, 1989 (54 FR 43430).

Interested persons have been afforded an opportunity to participate in the making of this 

amendment. Due consideration has been given to the single comment received.
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The commenter supported the rule.

Paragraph B. of the final rule has been clarified to indicate that if no disbonding or corrosion is found in areas other than Section 13 and 14, no further action is required.

After careful review of the available data, including the comment noted above, the FAA 

has determined that air safety and the public interest require the adoption of the rule with the 

change noted above.

It is estimated that 66 airplanes of U.S. registry will be affected by this AD, that it will 

take approximately 2,379 manhours per airplane to accomplish the required actions, and that the 

average labor cost will be $40 per manhour. Based on these figures, the total cost impact of the 

AD on U.S. operators is estimated to be $6,280,560.

The regulations adopted herein will not have substantial direct effects on the States, on 

the relationship between the national government and the States, or on the distribution of power 

and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a “major rule” under 

Executive Order 12291; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) will not have a significant economic impact, 

positive or negative, on a substantial number of small entities under the criteria of the Regulatory

Flexibility Act. A final evaluation has been prepared for this action and is contained in the regulatory docket. A copy of it may be obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

ADOPTION OF THE AMENDMENT

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal 

Aviation Administration amends part 39 of the Federal Aviation Regulations as follows:

PART 39—[AMENDED]

1. The authority citation for part 39 continues to read as follows:

 Authority: 49 U.S.C. 1354(a), 1421 and 1423; 49 U.S.C. 106(g) (Revised

 Pub. L. 97-449, January 12, 1983); and 14 CFR 11.89.
55 FR 261-01, 1990 Page 3

§ 39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

AIRBUS INDUSTRIE: Applies to all Model A300 series airplanes, Serial Number 001 through 

156, certificated in any category. Compliance is 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.
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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 an 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.
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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 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, Transport Airplane Directorate, 17900 Pacific 

Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way

South, Seattle, Washington.

This amendment becomes effective February 5, 1990.

Issued in Seattle, Washington, on December 20, 1989.

Leroy A. Keith,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 90-112 Filed 1-3-90; 8:45 am]

BILLING CODE 4910-13-M

55 FR 261-01, 1990

END OF DOCUMENT