55 FR 261 - 01, 1990 Page 1

RUL ES 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 inspectio ns for disbon ding and corrosion; edd y 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 cond ition, 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, Ai rbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transp ort Airplane Directorate, 17900 P aci f ic Highway

South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. FOR FURTHER INFORMATION CONTACT: Mr. Greg Holt, Stand ardization Branch, ANM 113; telephone (206) 431 - 1918. Mailing address: FAA, Northwest Mountain Region, 17900 P acific Highway

South, C - 68966, Seattle, Washington 98168. SUPPL EMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations to include a new airworthiness directive, applicable to certain Airbus Industrie Mo del A300 series airplanes, which requires repetitive inspections for disbonding and corrosion; e ddy current and ultrasonic inspectio ns of the fuselage longitudinal lap joints for cracks; and r e pair, 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 amen dment. Due consideration has been given to the single comment received.55 FR 261 - 01, 1990 Page 2

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 d e termined that air safety and the public interest require the adoption of the rule with the change noted above. It is estimated that 66 airpl anes of U.S. registry will be affected by

this AD, that it will take a p proximately

2,379 manhours per airplane to accomplish the required actions, and that the ave r age 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 rel ationship 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 E xecutive Order 12612 , it is determined that this final rule does not have sufficient federalism i mplications to warrant the preparation of a Federalis m 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 Proc edures (44 FR 11034; February 26, 1979); and (3) will no t 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 co py

of it may be obtained from the Rules Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safet y, Safety.

A DOPTION OF THE AMENDMENT Accordingl y, pursuant to the authority delegated to me by the Administrator, the Federal Avi ation Administration amends part 39 of the Federal Aviation Regulations as follows: PART 39

— [AMENDED] 1. The authorit y 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, Janu ary

12, 1983); and 14 CFR 11.89.55 FR 261 - 01, 1990 Page 3

§ 39.13 [Amended] 2. Section 39.13 is amended by ad ding the following new airworthiness directive: AIRBUS INDUSTRIE : Applies to all Model A300 series airplanes, Serial Number 001 through 156, certificated in an y category. Compliance is required as indicated, unless previously acco mplished. To ensure stru ctural integrit y 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 Bu l letin A300 - 53 - 211, Revision 1, dated Ap ril 10, 1989. a. Prior to the accumulation of 24,000 landings, or within 10 day s after the effective date of this AD, whichever occurs later, perform an edd y current inspection in special areas of the longitud i nal 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 serv ice bulletin. 2. Inspection of “standard” areas, as defined in paragraph 1.C(2) of Airbus Industrie Service Bu lletin A300 - 53 - 211, Revision 1, dated April 10, 1989. a. Prior to the accumulation of 32,000 landings, or within 10 day s after the effective dat e of this AD, whichever occurs later, perform an edd y current inspection of the standard areas of the lo ngitudinal 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 ex ceed: (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. Inspe ction of modified or repaired areas as defined in Tables 1 and 2 of Airbus Industrie Se rvice Bulletin A300 - 53 - 211, Revision 1, dated April 10, 1989.55 FR 261 - 01, 1990 Page 4

a. Prior to the accumulation of the threshold values (landings since first flight) identified in T a bles 1 or 2 of the service bulletin, or within 60 day s after the effective date of this AD, wh ichever occurs later, perform an edd y current inspection of the longitudinal lap joints in modified or r e paired areas in accordance with paragraph 2.B. of the service bu lletin. 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 th e service bulletin. B. Prior to the accumulation of 24,000 landings or 15 y ears since new, whichever occurs first, or within 60 day s after the effective date of this AD, whichever occurs later, inspect fuselage bonded inner doublers of longitudinal lap jo ints 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 ye ars since last inspection, whichever occurs first, in accordance with paragraph 1.B. of the service bullet in. 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 y ears since new, whichever occurs first, or within 60 day s after the effective date of this A D, 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, Revisi on 2, dated July 28, 1989. Airplanes older than 12 y ears 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 furth er 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.55 FR 261 - 01, 1990 Page 5

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 issu ed 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 b y this directive who have not alread y received the appropriate service do cuments from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be e xamined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pa cific 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. Lero y 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