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[Federal Register Volume 65, Number 37 (Thursday, February 24, 2000)]
[Proposed Rules]
[Pages 9223-9225]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-3134]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-362-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A300-600 
series airplanes. This proposal would require modification of certain 
electrical looms of the nose and main landing gear and modification of 
the rotor shaft attachment of the nose and main landing gear 
tachometers. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by the proposed AD are intended to 
prevent erratic operation of the wheel tachometers, which could result 
in degradation of the braking performance, and possible increased 
landing roll.

EFFECTIVE DATE: Comments must be received by March 27, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-362-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-362-AD.'' The

[[Page 9224]]

postcard will be date stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-362-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale 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 A300-600 series airplanes. 
The DGAC advises that it has received a report indicating that, after 
touchdown, an airplane overran the runway due to degradation of the 
braking system performance combined with non-extension of spoilers 1 
and 4. Investigation into the degradation of the braking system 
performance and the non-extension of the spoilers revealed that the 
cause was attributed to incorrect speed signals supplied by the wheel 
tachometers due to:
     Moisture, dirt, and subsequent corrosion of the electrical 
connectors of the nose and main landing gears; and
     Fracture of the coupling pins between the rotor shaft 
attachment and the drive coupling of the tachometer.
    These conditions, if not corrected, could result in erratic 
operation of the tachometers, which could cause a significant 
degradation of the braking system performance. Furthermore, if a 
tachometer on an aft wheel of the main landing gear is not operating 
correctly, this condition could affect the control logic of the spoiler 
extension and could result in an increased landing roll.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletin A300-32-6069, 
Revision 01, dated December 29, 1999, which describes procedures for 
modification of certain electrical looms of the nose and main landing 
gears. The modification involves installing heat-shrinkable sheaths on 
the ground/flight detection loom connectors and strut-locking switches, 
and draining the looms of certain locking switches.
    The manufacturer also has issued Airbus Service Bulletin A300-32-
6077, Revision 01, dated September 25, 1999, which describes procedures 
for modification of the rotor shaft attachment of the nose and main 
landing gear tachometers. This modification involves machining the 
rotor assembly and either machining or replacing the drive coupling 
with a new drive coupling, and attaching the rotor shaft to the drive 
coupling with a rivet.
    Accomplishment of the actions specified in the Airbus service 
bulletins is intended to adequately address the identified unsafe 
condition. The DGAC classified these service bulletins as mandatory and 
issued French airworthiness directive 1999-428-295(B), dated November 
3, 1999, in order to assure the continued airworthiness of these 
airplanes in France.
    The Airbus service bulletins reference Messier-Dowty Service 
Bulletin 470-32-779, dated April 14, 1997; Messier-Dowty Service 
Bulletin 470-32-777, dated July 1, 1997; and Messier-Bugatti Service 
Bulletin C20105-32-782, dated October 17, 1996, as additional sources 
of service information for accomplishing the requirements of this 
proposed AD.

FAA's Conclusions

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) 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 Proposed 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, the proposed AD would require accomplishment of 
the actions specified in the Airbus service bulletins described 
previously.

Cost Impact

    The FAA estimates that 79 airplanes of U.S. registry would be 
affected by this proposed AD.
    It would take approximately 7 work hours per airplane to accomplish 
the proposed modification of the electrical looms, at an average labor 
rate of $60 per work hour. Required parts would cost approximately $687 
per airplane. Based on these figures, the cost impact of the proposed 
AD on U.S. operators is estimated to be $87.453, or $1,107 per 
airplane.
    It would take approximately 13 work hours per airplane to 
accomplish the proposed modification of the rotor shaft attachment, at 
an average labor rate of $60 per work hour. Required parts would cost 
approximately $169 per airplane. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $74,971, 
or $949 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed 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 proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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. 3913  [Amended]

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

[[Page 9225]]

Airbus Industrie: Docket 99-NM-362-AD.

    Applicability: Model A300-600 series airplanes, certificated in 
any category, except those airplanes on which Airbus Modifications 
11661 and 11676 (Airbus Service Bulletin A300-32-6069) and 12095 
(Airbus Service Bulletin A300-32-6077) have been installed.

    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 (b) 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 erratic operation of the wheel tachometers, which 
could result in degradation of the braking performance, and possible 
increased landing roll, accomplish the following:

Modifications

    (a) Within 18 months after the effective date of this AD, 
accomplish the requirements of paragraphs (a)(1) and (a)(2) of this 
AD.
    (1) Modify the electrical looms of the nose and main landing 
gear, in accordance with Airbus Service Bulletin A300-32-6069, 
Revision 01, dated December 29, 1999; and
    (2) Modify the rotor shaft attachment of the nose and main 
landing gear tachometers, in accordance with Airbus Service Bulletin 
A300-32-6077, Revision 01, dated September 25, 1999.

    Note 2:
    Messier-Dowty Service Bulletins 470-32-779, dated April 14, 
1997, and 470-32-777, dated July 1, 1997, are referenced in Airbus 
Service Bulletin A300-32-6069. Messier-Bugatti Service Bulletin 
C20105-32-782, dated October 17, 1996, is referenced in Airbus 
Service Bulletin A300-32-6077. The Messier-Dowty and Messier-Bugatti 
service bulletins are additional sources of service information for 
accomplishing the applicable actions required by this AD.

    Note 3:
    Accomplishment of the modifications required by paragraph (a) of 
this AD, prior to the effective date of this AD, in accordance with 
Airbus Service Bulletin A300-32-6069, dated June 13, 1997, or A300-
32-6077, dated May 28, 1999, is considered acceptable for compliance 
with the applicable requirements specified by this AD.

Alternative Methods of Compliance

    (b) 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.

Special Flight Permits

    (c) 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.

    Note 5:
    The subject of this AD is addressed in French airworthiness 
directive 1999-428-295(B), dated November 3, 1999.

    Issued in Renton, Washington, on February 4, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-3134 Filed 2-23-00; 8:45 am]
BILLING CODE 4910-13-M
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