[Federal Register Volume 63, Number 243 (Friday, December 18, 1998)]
[Proposed Rules]
[Pages 70068-70069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-33539]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-301-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 removal of the fuel level 
sensing amplifier (FLSA) of the trim tank system, modification of the 
polarization pin code in the electronics bay, and installation of a 
new, improved FLSA. 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 continuous aft transfer of fuel due to the FLSA not supplying 
electrical power to the trim tank overflow sensor, which could result 
in potential loss of fuel during flight.

DATES: Comments must be received by January 19, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-301-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 98-NM-301-AD.'' The 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. 98-NM-301-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, on airplanes equipped with a trim tank system 
and with a certain fuel level sensing amplifier (FLSA), electrical 
power is not being supplied to the trim tank overflow sensor during 
flight. This condition is caused by the existing design of the FLSA, 
and could result in fuel loss from the trim tank during flight. Such 
fuel loss could occur if all of the following conditions are present:
     Failure of the high-level sensor or associated circuits of 
the trim tank while the trim tank is empty; and
     Balance of the airplane such that the center of gravity 
with no fuel on board is 24 percent mean aerodynamic chord of the wing 
or further forward of that location; and
     Fuel weight of the airplane before departure is greater 
than 20,000 kilograms (44,000 pounds), which is the minimum amount of 
fuel required to fill the trim tank.
     Lack of electrical power to the trim tank overflow sensor, 
if not corrected, could result in continuous aft transfer of fuel, and 
potential loss of fuel during flight.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletin A300-28-6055, 
Revision 01, dated July 24, 1998, which describes procedures for 
removal of the FLSA of the trim tank system, modification of the 
polarization pin code in the electronics bay, and installation of a 
new, improved FLSA. Accomplishment of the actions specified in the 
service bulletin is intended to adequately address the identified 
unsafe condition. The DGAC classified this service bulletin as 
mandatory and issued French airworthiness directive 98-249-252(B), 
dated July 1, 1998, in order to assure the continued airworthiness of 
these airplanes in France.

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

[[Page 70069]]

in the service bulletin described previously.

Cost Impact

    The FAA estimates that 61 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would be 
supplied by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the actions proposed by this AD on 
U.S. operators is estimated to be $10,980, or $180 per airplane.
    The cost impact figure discussed above is 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 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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. 39.13  [Amended]

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

Airbus Industrie: Docket 98-NM-301-AD.

    Applicability: Model A300-600 series airplanes on which Airbus 
Modification 4801 was accomplished during production and on which 
Airbus Modification 10778 (reference Airbus Service Bulletin A300-
31-6051, dated June 28, 1996) has been accomplished; except those 
airplanes on which Airbus Modification 11683 (reference Airbus 
Service Bulletin A300-28-6055, dated January 28, 1997, and Revision 
01, dated July 24, 1998) 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 (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 continuous aft transfer of fuel due to the fuel level 
sensing amplifier (FLSA) not supplying electrical power to the trim 
tank overflow sensor, which could result in potential loss of fuel 
during flight, accomplish the following:
    (a) Except as provided by paragraph (b) of this AD, within 2 
months after the effective date of this AD, remove the FLSA of the 
trim tank system, modify the polarization pin code in the 
electronics bay, and install a new, improved FLSA, in accordance 
with Airbus Service Bulletin A300-28-6055, Revision 01, dated July 
24, 1998.

    Note 2: Accomplishment of the actions specified in paragraph (a) 
of this AD, prior to the effective date of this AD, in accordance 
with Airbus Service Bulletin A300-28-6055 dated January 28, 1997, is 
considered acceptable for compliance with the applicable actions 
specified in this AD.

    (b) For airplanes on which Airbus Service Bulletin A300-31-6051, 
dated June 28, 1996, is accomplished after the effective date of 
this AD: Concurrent with the accomplishment of Airbus Service 
Bulletin A300-31-6051, accomplish the actions required by paragraph 
(a) of this AD, in accordance with Airbus Service Bulletin A300-28-
6055, Revision 01, dated July 24, 1998.
    (c) As of the effective date of this AD, no person shall install 
a FLSA having part number 722-295-2, on any airplane.
    (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 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.

    (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.

    Note 4: The subject of this AD is addressed in French 
airworthiness directive 98-249-252(B), dated July 1, 1998.

    Issued in Renton, Washington, on December 14, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-33539 Filed 12-17-98; 8:45 am]
BILLING CODE 4910-13-P