AD 99-23-16

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, which could result in reduced structural integrity of the belly fairing.

Final rule.

99-23-16 AIRBUS INDUSTRIE: Amendment 39-11412. Docket 99-NM-184-AD.
Applicability: Model A330 and A340 series airplanes; except those airplanes on which Airbus Modification 42605, or Airbus Service Bulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-4028 (for Model A340 series airplanes) has 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, ifthe unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct fatigue cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, which could result in reduced structural integrity of the belly fairing, accomplish the following:

Repetitive Detailed Visual Inspections
(a) Prior to the accumulation of 5,500 total flight cycles, or within 500 flight hours after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, in accordance with Airbus Service Bulletin A330-53-3020 (for Model A330 series airplanes) or A340-53-4029 (for Model A340 series airplanes); each dated November 30, 1995; as applicable.

NOTE 2: For thepurposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required."

(1) If no cracking is detected, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles, until the requirements of paragraph (b) of this AD are accomplished.

Corrective Actions
(2) If any cracking is detected during any inspection required by this AD, prior to further flight, modify the vertical flange of both inboard Z-stiffeners of the centerline panel of the fuselage belly fairing and re-inspect the modified area to determine if cracking has been eliminated, in accordance with Airbus Service Bulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-4028 (for Model A340 series airplanes); each dated November 30, 1995; as applicable.

(i) If all cracking is not eliminated after accomplishment of the modification, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

(ii) If all cracking is eliminated after the accomplishment of the modification, no further action is required by this AD.

Optional Terminating Action
(b) Modification of the vertical flange of both inboard Z-stiffeners of the centerline panel of the fuselage belly fairing in accordance with Airbus ServiceBulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-4028 (for Model A340 series airplanes); each dated November 30, 1995; as applicable; constitutes terminating action for the requirements of this AD.

Alternative Methods of Compliance
(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. 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits
(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.

Incorporation by Reference
(e) The inspections and modification shall be done in accordance with Airbus Service Bulletin A330-53-3020, dated November 30, 1995; Airbus Service Bulletin A340-53-4029, dated November 30, 1995; Airbus Service Bulletin A330-53-3019, dated November 30, 1995; and Airbus Service Bulletin A340-53-4028, dated November 30, 1995; as applicable. 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 4: The subject of this AD is addressed in French airworthiness directives96-056-029 (B) and 96-057-042 (B); each dated March 13, 1996.

(f) This amendment becomes effective on December 17, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A330 and A340 series airplanes was published in the Federal Register on September 10, 1999 (64 FR 49110). That action proposed to require repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. That action also proposed to provide for optional terminating action for the repetitive inspections.

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

One commenter, an operator, states that it will have the terminating modification incorporated prior to delivery of its airplanes.

Conclusion
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 as proposed.

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 1 work hour to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this AD would be $60 per airplane, per inspection cycle.

Should an operator elect to accomplish the optional terminating action provided by this AD, it would require approximately 7 work hours to accomplish the optional terminating action, at an average labor rate of $60 per work hour. Required parts would cost approximately $2,350 per airplane. Based on these figures, the cost impact of the optional terminating action is estimated to be $2,770 per airplane.

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 nota"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 adding the following new airworthiness directive: