AD 98-06-24

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires modification to reinforce the joints of certain fuselage frames. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking of the fuselage frames, which could result in reduced structural integrity of the airplane.

Final rule; request for comments.

98-06-24 AIRBUS INDUSTRIE: Amendment 39-10402. Docket 97-NM-324-AD.

Applicability: Model A330 and A340 series airplanes, on which Airbus Modification 42409 has not been accomplished, 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 (c) 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 asindicated, unless accomplished previously.

To prevent fatigue cracking in the fuselage frames, which could result in reduced structural integrity of the airplane, accomplish the following:

(a) Reinforce the joints for fuselage frames 53, 53.1, and 53.2, in accordance with Airbus Service Bulletin A330-53-3015, dated November 24, 1995 (for Model A330 series airplanes); or Airbus Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996 (for Model A340 series airplanes), as applicable; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable.

(1) For Airbus Model A330 series airplanes on which Airbus Modification 43475 has been accomplished, and for Airbus Model A340 series airplanes: Prior to the accumulation of 4,100 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(2) For Airbus Model A330 series airplanes on which Airbus Modification 43475 has not been accomplished: Prior to the accumulation of 4,600 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(b) Reinforce the joints for fuselage frames 48 through 52 inclusive, in accordance with Airbus Service Bulletin A330-53-3015, dated November 24, 1995 (for Model A330 series airplanes); or Airbus Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996 (for Model A340 series airplanes), as applicable; at the time specified in paragraph (b)(1) or (b)(2) of this AD, as applicable.

(1) For Airbus Model A330 series airplanes on which Airbus Modification 43475 has been accomplished, and for Airbus Model A340 series airplanes: Prior to the accumulation of 13,500 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(2) For Airbus Model A330 series airplanes on which Airbus Modification 43475 has not been accomplished: Prior to the accumulation of 15,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(c) 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.

(d) 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.

(e) The actions shall be done in accordance with Airbus Service Bulletin A330-53- 3015, dated November 24, 1995, or Airbus Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996; as applicable. Airbus Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996, contains the following list of effective pages:

Page Number
Revision Level
Shown on Page
Date
Shown on Page
1, 2, 3, 3a, 4, 4a, 5-7,
31-32, 83-87
2
May 15, 1996
8-10, 12, 14-18,
20-29, 33-82
Original
November 24, 1995
11, 13, 19, 30
1
February 22, 1996

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.

NOTE 3: The subject of this AD is addressed in French airworthiness directives 96-006-024(B) and 96-005-039(B), both dated January 3, 1996.

(f) This amendment becomes effective on April 6, 1998.

The Direction G n rale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Model A330 and A340 series airplanes. The DGAC advises that, during a full-scale fatigue test, a 4.5-millimeter crack developed in the fuselage after 31,717 simulated flight cycles. The crack was found at the lowest inboard bolt hole at the frame splice area and shear clip attachment on left fuselage frame (L FR) 48 at stringer 26. Similar damage was found at L FR 53 and right fuselage frame 52. Such fatigue cracking of fuselage frames, if not detected and corrected in a timely manner, could result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information
Airbus has issued Service Bulletin A330-53-3015, dated November 24, 1995 (for Model A330 series airplanes), and A340-53-4023, Revision 2, dated May 15, 1996 (for Model A340 series airplanes). These service bulletins describe procedures for modifying the joints of fuselage frames 48 to 53. The modification involves adding two joint straps, replacing existing fasteners with new fasteners, and replacing the existing clips with machined clips. Accomplishment of the actions specified in the service bulletins is intended to adequately address the identified unsafe condition. The DGAC classified these service bulletins as mandatory and issued French airworthiness directives 96-006-024(B) and 96-005-039(B), both dated January 3, 1996, in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions
These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of the Rule
Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to prevent fatigue cracking in the fuselage frames, which could result in reduced structural integrity of the airplane. This AD requires accomplishment of the actions specified in the service bulletins described previously.

Cost Impact
None of the airplanes affected by this action are on the U.S. Register. All airplanes included in the applicability of this rule currently are operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, the FAA considers that this rule is necessary to ensure that the unsafe condition is addressed in the event that any of these subject airplanes are imported and placed on the U.S. Register in the future.

Should an affected airplane be imported and placed on the U.S. Register in the future, it would require approximately 208 work hours to accomplish the required modification, at an average labor rate of $60 per work hour. Required parts would cost approximately $30,765 per airplane. Based on these figures, the cost impact of this AD would be $43,245 per airplane.

Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently on the U.S. register, it has no adverse economic impact and imposes no additional burden on any person. Therefore, prior notice and public procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register.

Comments Invited
Although this action is in the form of afinal rule and was not preceded by notice and opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing datefor comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 97-NM-324-AD." The postcard will be date stamped and returned to the commenter.

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 citationfor 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 adding the following new airworthiness directive: