AD 94-09-15 ACTIVE

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that currently requires repetitive inspections of the aft bulkhead to detect cracks, and repair, if necessary. This amendment requires expansion of the inspection area and modication of the aft pressure bulkhead, which terminates the inspection requirements. This amendment is prompted by a tear down inspection conducted by the manufacturer, which revealed fatigue cracking in additional areas of the aft pressure bulkhead. The actions specified by this AD are intended to prevent potential loss of cabin pressurization.

Final rule.

94-09-15 AIRBUS INDUSTRIE: Amendment 39-8904. Docket 93-NM-55-AD. Supersedes AD 84-08-03, Amendment 39-4848.

Applicability: Model A300 B2-1A, B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4- 203 series airplanes, on which Airbus Modification 2476/D1842 and Airbus Modification 2476/D1869 have not been accomplished; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent loss of cabin pressurization, accomplish the following:

NOTE 1: Paragraph (a) of this AD restates the requirement for an initial and repetitive inspections contained in paragraph A. of AD 84-08-03. Therefore, for operators who have previously accomplished at least the initial inspection in accordance with AD 84-08-03, paragraph (a) of this AD requires that the next scheduled inspection be performed within the 6,000 flight cycles after the last inspection performed in accordance with paragraph A. of AD 84- 08-03.

(a) Prior to the accumulation of 12,000 total flight cycles, or within 180 days after June 11, 1984 (the effective date of AD 84-08-03, Amendment 39-4848), whichever occurs later, inspect the aft bulkhead in areas 1 and 2 to detect fatigue cracking, in accordance with Airbus Service Bulletin A300-53-152, Revision 1, dated January 30, 1981; or Revision 4, dated March 13, 1992.
(1) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles.
(2) If any crack is detected as a result of any inspection required by paragraph (a) of this AD, prior to further flight, repair the crack, in accordance with Airbus Service Bulletin A300-53-152, Revision 1, dated January 30, 1981; or Revision 4, dated March 13, 1992. Subsequent to repair, repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles.

(b) Prior to the accumulation of 17,000 total flight cycles, or within 1 year after June 11, 1984 (the effective date of AD 84-08-03, Amendment 39-4848), whichever occurs later, accomplish Airbus Modification 2476/D1869, in accordance with Airbus Service Bulletin A300- 53-122, Revision 2, dated January 30, 1981.

(c) Prior to the accumulation of 32,000 total flight cycles, or within 1 year after the effective date of this AD, whichever occurs later, inspect the aft pressure bulkhead in areas 3 and 4 to detect fatigue cracking, in accordance with Airbus Service Bulletin A300-53-152, Revision 4, dated March 13, 1992.
(1) If no crack is detected, repeat the inspection at intervals not to exceed 9,000 flight cycles.
(2) If any crack is detected as a result of any inspection required by paragraph (b) of this AD, prior to further flight, repair the crack in accordance with Airbus Structural Repair Manual 51-41-30. Subsequent to repair, repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles.

(d) Within 6 years after the effective date of this AD, accomplish Airbus Modification 2476/D1842, in accordance with Airbus Service Bulletin A300-53-121, Revision 3, dated January 30, 1981. Accomplishment of this modification constitutes terminating action for the inspections required by this AD.

(e) Accomplishment of Airbus Modification 2476/D1842, in accordance with Airbus Service Bulletin A300-53-121, Revision 3, dated January 30, 1981, constitutes terminating action for the inspection requirements of this AD.

(f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch,ANM-113.

(g) Special flight permits may be issued in accordance with Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(h) The inspections and repairs shall be done in accordance with the following Airbus service bulletins, as applicable, which contain the specified effective pages:

Service Bulletin
Referenced and Date

Page Number
Revision Level
Page Number
Date
Shown on Page
A300-53-121,
Revision 3
January 30, 1981

1-4

2, 7, 10-15, 17

6, 8, 9, 16, 18

5
3

2

1

Original
January 30, 1981

December 30, 1980

September 30, 1980

April 10, 1980
A300-53-152,
Revision 1,
January 30, 1981
1-2

3-18
1

Original
January 30, 1981

October 24, 1980
A300-53-152,
Revision 4,
March 13, 1992
1-10, 18

11-17, 19-21
4

3
March 13, 1992

(These pages are not dated.)

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective on June 8, 1994.

A proposal to amend part 39 of the Federal Aviation Regulations by superseding AD 84-08-03, Amendment 39-4848 (49 FR 16762, April 20, 1984), which is applicable to certain Airbus Model A300 series airplanes, was published in the Federal Register on September 3, 1993 (58 FR 46914). The action proposed to supersede AD 84-08-03 to require expansion of the inspection area to include areas 3 and 4 of the aft pressure bulkhead, and repair, if necessary; and modification of the aft pressure bulkhead, which will terminate the inspection requirements of this AD. This modification entails increasing the strength of the aft pressure bulkhead by attaching additional stiffeners. (This modification was optional in AD 84-08-03, Amendment 39-4848.)

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the three comments received.

All of the commenters support the proposed rule.

After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 6 airplanes of U.S. registry will be affected by this AD, that it will take approximately 738 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. Required parts will cost approximately $4,000 per airplane. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $267,540, or $44,590 per airplane.

The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

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 "significant regulatory action" under Executive Order 12866; (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 it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 of the Federal Aviation Regulations as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

39.13 - [Amended]
2. Section 39.13 is amended by removing amendment 39-4848 (49 FR 16762, April 20, 1984), and by adding a new airworthiness directive (AD), amendment 39-8904, to read as follows:

The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Stephen Slotte, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1320.