AD Amdt-39-11467

[Federal Register Volume 64, Number 244 (Tuesday, December 21, 1999)]
[Rules and Regulations]
[Pages 71278-71280]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-32508]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[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.

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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

[[Page 71279]]

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.

Comments

    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.

Conclusion

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

Cost Impact

    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.

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.

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

99-26-08 AIRBUS INDUSTRIE: Amendment 39-11467. Docket 96-NM-194-AD.

    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:

Corrective Actions

    (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, 
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

[[Page 71280]]

A300-600 series airplanes), both dated October 2, 1998; as 
applicable, is acceptable for compliance with that paragraph.

Spares

    (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.

Alternative Methods of Compliance

    (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.

Incorporation by Reference

    (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.

    (g) This amendment becomes effective on January 25, 2000.

    Issued in Renton, Washington, on December 9, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-32508 Filed 12-20-99; 8:45 am]
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