AD 98-18-16

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that currently requires reinforcement of the tail section of the fuselage at frames 68 and 69. This amendment adds a requirement for reinforcement of the tail section of the fuselage at frames 65 to 67. This action also revises the applicability of the existing AD. This amendment is prompted by reports indicating that the tail section has struck the runway during takeoffs and landings. The actions specified by this AD are intended to prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight.

Final rule.

98-18-16 AIRBUS INDUSTRIE: Amendment 39-10732. Docket 98-NM-01-AD. Supersedes AD 97-08-04, Amendment 39-9992.

Applicability: Model A320 series airplanes on which Airbus Modification 22764 has not been installed, certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight, accomplish the following:

RESTATEMENT OF REQUIREMENT OF AD 97-08-04:
(a) For airplanes listed in Airbus Service Bulletin A320-53-1110, dated August 28, 1995: Within 6 years after May 15, 1997 (the effective date of AD 97-08-04, amendment 39-9992), modify the fuselage by reinforcing frames 68 and 69 in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995; or Revision 1, dated November 27, 1995.

NEW REQUIREMENTS OF THIS AD:
(b) For airplanes other than those identified in paragraph (a) of this AD: Within 5 years after the effective date of this AD, modify the fuselage by reinforcing frames 68 and 69 in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995, or Revision 1, dated November 27, 1995.

(c)For all airplanes: Within 5 years after the effective date of this AD, modify the fuselage by reinforcing frames 65 to 67 in accordance with Airbus Service Bulletin A320-53- 1131, dated July 24, 1997.

(d) 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, International Branch, ANM-116, 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, International Branch, ANM-116.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) The modifications shall be done in accordance with Airbus Service Bulletin A320-53-1131, dated July 24, 1997; Airbus Service Bulletin A320-53-1110, dated August 28, 1995; and Airbus Service Bulletin A320-53-1110, Revision 1, dated November 27, 1995, which contains the following list of effective pages:

Page Number
Revision Level
Shown on Page
Date
Shown on Page
1-8, 10-13, 15-20,
23-40, 42, 44-45
Original
August 28, 1995
9, 14, 21-22, 41, 43
Revision 1
November 27, 1995

(1) The incorporation by reference of Airbus Service Bulletin A320-53-1110, Revision 1, dated November 27, 1995, and Airbus Service Bulletin A320-53-1131, dated July 24, 1997, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of Airbus Service Bulletin A320-53-1110, dated August 28, 1995, was approved previously by the Director of the Federal Register as of May 15, 1997 (62 FR 17532, April 10, 1997).

(3) 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.

NOTE 3: The subject of this AD is addressed in French airworthiness directive 97-315- 109(B), dated October 22, 1997.

(g) This amendment becomes effective on October 8, 1998.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 97-08-04, amendment 39-9992 (62 FR 17532, April 10, 1997), which is applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, was published in the Federal Register on July 9, 1998 (63 FR 37078). The action proposed to supersede AD 97-08-04 to continue to require reinforcement of the tail section of the fuselage at frames 68 and 69. It also proposed to add a requirement for reinforcement of the tail section of the fuselage at frames 65 to 67. The action also proposed to revise the applicability of the existing AD.

Comments
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.

The commenter supports the proposed rule.

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

Cost Impact
There are approximately 118 airplanes of U.S. registry that will be affected by this AD.

The actions that are currently required by AD 97-08-04, and retained in this AD, take approximately 196 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the currently required actions on U.S. operators is estimated to be $1,387,680, or $11,760 per airplane.

The new actions that are required by this new AD will take approximately 488 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the new requirements of this AD on U.S. operators is estimated to be $3,455,040, or $29,280 per airplane.

The cost impact figures discussed above are 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.

Regulatory Impact
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 part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9992 (62 FR 17532, April 10, 1997), and by adding a new airworthiness directive (AD), amendment 39-10732, to read as follows: