[4910-13-U]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39 [64 FR 71278 12/21/99]

[Docket No. 96-NM-194-AD; Amendment 39-11467; AD 99-26-08]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A310 and A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the rudder trim switch in the flight compartment with a new switch having a longer shaft; modification of wiring in panel 408VU; and replacement of the rudder trim control knob with an improved new knob. 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 inadvertent and uncommanded rudder trim activation, which could result in yaw and roll excursions and consequent reduced controllability of the airplane.

DATES: Effective January 25, 2000.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 25, 2000.

ADDRESSES: 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.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 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 and A300-600 series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on February 12, 1998 (63 FR 7076). That action proposed to require replacement of the rudder trim switch in the flight compartment with a new switch having a longer shaft; modification of wiring in panel 408VU; and replacement of the rudder trim control knob with an improved new knob.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the supplemental NPRM or the FAA’s determination of the cost to the public.

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 90 airplanes of U.S. registry will be affected by this AD.

Replacement of the rudder trim switch and modification of the wiring will take approximately 7 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 this action on U.S. operators is estimated to be $37,800, or $420 per airplane.

Replacement of the rudder trim control knob will take approximately 1 work hour 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 this action on U.S. operators is estimated to be $5,400, or $60 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.

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."

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

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:

Applicability: Model A310 and A300-600 series airplanes, certificated in any category; except those on which Airbus Modification 11874 [reference Airbus Service Bulletin A310-27-2087 (for Model A300 series airplanes) or A300-27-6042 (for Model A300-600 series airplanes), both dated October 2, 1998] has been accomplished.

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 inadvertent and uncommanded rudder trim activation, which could result in yaw and roll excursions and consequent reduced controllability of the airplane, accomplish the following:

(a) Within 90 days after the effective date of this AD, replace the rudder trim switch, part number (P/N) 097-023-00, in the flight compartment, with a new switch, P/N 097-023-01; and modify the wiring in panel 408VU; in accordance with Airbus Service Bulletin A310-27-2084, Revision 01 (for Model A310 series airplanes); or A300-27-6037, Revision 01 (for Model A300-600 series airplanes), both dated September 29, 1998; as applicable.

NOTE 2: Accomplishment of the actions required by paragraph (a) of this AD in accordance with Airbus Service Bulletin A310-27-2084 (for Model A310 series airplanes); or A300-27-6037 (for Model A300-600 series airplanes), both dated February 12, 1997; as applicable, is acceptable for compliance with that paragraph.

(b) Within 10 months after the effective date of this AD (i.e. NOV 2000), replace the rudder trim control knob on the rudder trim switch with an improved new knob in accordance with Airbus Service Bulletin A310-27-2087, Revision 01 (for Model A310 series airplanes); or A300-27-6042, Revision 01 (for Model A300-600 series airplanes), both dated February 17, 1999; as applicable.

NOTE 3: Accomplishment of the actions required by paragraph (b) of this AD in accordance with Airbus Service Bulletin A310-27-2087 (for Model A310 series airplanes); or A300-27-6042 (for Model A300-600 series airplanes), both dated October 2, 1998; as applicable, is acceptable for compliance with that paragraph.

(c) As of the effective date of this AD, no person shall install in the flight compartment of any airplane a rudder trim switch having P/N 097-023-00.

(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 4: 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 actions shall be done in accordance with Airbus Service Bulletin A310-27-2084, Revision 01, dated September 29, 1998; Airbus Service Bulletin A300-27-6037, Revision 01, dated September 29, 1998; Airbus Service Bulletin A310-27-2087, Revision 01, dated February 17, 1999; or Airbus Service Bulletin A300-27-6042, Revision 01, dated February 17, 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 5: The subject of this AD is addressed in French airworthiness directives 97-111-219(B), dated May 7, 1997, and 1999-012-275(B), dated January 13, 1999.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.