AD 99-21-21

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310-300 and A300-600R series airplanes, that requires installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness on the trimmable horizontal stabilizer for the fuel tank water scavenge motive pump. 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 prevent fuel leakage from the seal of the water scavenge pumps, which, if not corrected, could result in leakage of fuel into fuselage areas not designed for fuel, and consequent potential for fuel to be in contact with a fuel ignition source.

Final rule.

99-21-21 AIRBUS INDUSTRIE: Amendment 39-11366. Docket 99-NM-08-AD.

Applicability: Model A310-300 and A300-600R series airplanes, except those airplanes on which Airbus Modification 10003 (reference Airbus Service Bulletin A310-28-2058, Revision 2, dated February 22, 1995, or A300-28-6035, Revision 03, dated August 5, 1999) 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 (e) 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 fuel leakage from the seal of the water scavenge pumps, which, if not corrected, could result in leakage of fuel into fuselage areas not designed for fuel, and consequent potential for fuel to be in contact with a fuel ignition source, accomplish the following:

Model A310-300 Series Airplanes: Modification
(a) For Model A310-300 series airplanes on which a water scavenge pump has been installed prior to the effective date of this AD, in accordance with Airbus Modification 8679 (reference Airbus Service Bulletin A310-28-2049, dated February 6, 1992; Revision 1, dated June 17, 1992; Revision 2, dated June 3, 1994; or Revision 3, dated April 5, 1996): Within 18 months after the effective date of this AD, install a new cover assembly, associated new drain and vent pipework, and a new electrical harness, in accordance with Airbus Service Bulletin A310- 28-2058, Revision 2, dated February 22, 1995.

(b) For Model A310-300 series airplanes on which a water scavenge pump is installed after the effective date of this AD, in accordance with Airbus Modification 8679 (reference Airbus Service Bulletin A310-28-2049, dated February 6, 1992; Revision 1, dated June 17, 1992; Revision 2, dated June 3, 1994; or Revision 3, dated April 5, 1996): The actions required by paragraph (a) of this AD must be accomplished simultaneously with Airbus Modification 8679.
Model A300-600R Series Airplanes: Modification
(c) For Model A300-600R series airplanes on which a water scavenge pump has been installed prior to the effective date of this AD, in accordance with Airbus Modification 8679 (reference Airbus Service Bulletin A300-28-6028, dated February 6, 1992; Revision 1, dated June 5, 1992; Revision 2, dated October 14, 1993; Revision 3, dated April 5, 1996; or Revision 4, dated April 3, 1997): Within 18 months after the effective date of this AD, install a new cover assembly, associated new drain and vent pipework, and a new electrical harness, in accordance with Airbus Service A300-28-6035, Revision 03, dated August 5, 1999.

NOTE 2: Installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness in accordance with Airbus Service Bulletin A300-28-6035, Revision 1, dated December 4, 1992, or Revision 2, dated March 17, 1993, is considered acceptable for compliance with the requirements specified in paragraph (c) of this AD.

(d) For Model A300-600R series airplanes on which a water scavenge pump is installed after the effective date of this AD, in accordance with Airbus Modification 8679 (reference Airbus Service Bulletin A300-28-6028, dated February 6, 1992; Revision 1, dated June 5, 1992; Revision 2, dated October 14, 1993; Revision 3, dated April 5, 1996; or Revision 4, dated April 3, 1997): The actions required by paragraph (c) of this AD must be accomplished simultaneously with Airbus Modification 8679.

Alternative Methods of Compliance
(e) 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 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
(f) 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 ADcan be accomplished.

Incorporation by Reference
(g) The actions shall be done in accordance with Airbus Service Bulletin A310 -28-2058, Revision 2, dated February 22, 1995; and Airbus Service A300-28-6035, Revision 03, dated August 5, 1999; 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 directive 98-354-256(B), dated September 9, 1998.

(h) This amendment becomes effective on November 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 A310-300 and A300-600R series airplanes was published in the Federal Register on July 20, 1999 (64 FR 38848). That action proposed to require installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness on the trimmable horizontal stabilizer for the fuel tank water scavenge motive pump.

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.

Request to Determine Parts Availability
One commenter supports the intent of the proposal, assuming that the necessary parts are available from the manufacturer. The FAA notes that the Airbus service bulletins cited as the appropriate sources of service information in the proposed AD state that kits will be available 150 to 180 days after request by an operator. The FAA is not aware of any difficulties with availability of the kits necessary to accomplish the actions required by this AD. No change is made to the final rule.

New Service Information
Since the issuance of the proposed AD, the manufacturer has issued Airbus Service Bulletin A300-28-6035, Revision 03, dated August 5, 1999. This revision of the service bulletin adds references and clarifies certain procedures and illustrations. The FAA has determined that the changes do not add any additional burden to operators. Paragraph (c) of this AD has been revised to cite Revision 03 of the service bulletin as the appropriate source of service information. For operators that may have previously accomplished the required actions in accordance with Revision 1 or 2 of the service bulletin, "NOTE 2" of the final rule has been revised to give credit for those actions. In addition, the applicability hasbeen revised to referenced Revision 03 of the service bulletin.

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 with the changes described previously. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 102 Model A310-300 and A300-600R series airplanes of U.S. registry will be affected by this AD, that it will take approximately 20 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $5,710. Based on these figures, the cost impact of the required AD on U.S. operators is estimated to be $704,820, or $6,910 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished anyof 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 adding the following new airworthiness directive: