[Federal Register Volume 65, Number 25 (Monday, February 7, 2000)]
[Rules and Regulations]
[Pages 5751-5753]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-2469]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-23-AD; Amendment 39-11556; AD 2000-02-38]
RIN 2120-AA64


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

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule.

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SUMMARY:  This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300, A300-600, and A310 
series airplanes, equipped with a welded auxiliary power unit (APU) 
fuel feedline adapter. That AD currently requires repetitive dye 
penetrant inspections to detect cracks, rupture, or fuel leaks of the 
fuel feedline adapter; and replacement of the adapter, if necessary. 
That AD also provides for optional terminating action for the 
repetitive inspections. This amendment requires accomplishment of the 
previously optional terminating action. 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 in the APU compartment, which could 
result in a fire in the APU compartment.

DATES:  Effective March 13, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 13, 2000.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of October 7, 1991 (56 FR 47672, September 20, 
1991).

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

[[Page 5752]]

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, FAA, 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) by superseding AD 91-20-07, 
amendment 39-8041 (56 FR 47672, September 20, 1991), which is 
applicable to certain Airbus Model A300, A300-600, and A310 series 
airplanes, was published in the Federal Register on October 6, 1999 (64 
FR 54249). The action proposed to continue to require repetitive dye 
penetrant inspections to detect cracks, rupture, or fuel leaks of the 
fuel feedline adapter, and replacement of the adapter, if necessary. 
The action also proposed to continue to require verification of the 
correct torque values of the starter motor cable terminals and the 
generator cable terminals. The action also proposed to require 
accomplishment of the previously optional terminating action.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter requests clarification concerning the relationship 
between the adapter part number identified in the referenced French 
airworthiness directive and Airbus service bulletin and the adapter 
part number referred to in the Airbus Illustrated Parts Catalog (IPC). 
The commenter has already modified its auxiliary power units (APU) to 
incorporate the adapter [part number (P/N) A4937021700200] specified in 
the service bulletin. The Airbus IPC suggests an alternative P/N for 
the adapter, i.e., P/N A4937021700400; yet the IPC makes no reference 
to any supersedure, nor does it refer to a service bulletin authorizing 
that P/N. The commenter asks whether the installation of an adapter 
having either P/N is acceptable for compliance with the French 
airworthiness directive and this proposed AD.
    The FAA concurs that clarification is necessary. Airbus has advised 
the FAA that the only difference between the two referenced P/N's is 
that the tolerance for the B-nut thread of the adapter having P/N 
A4937021700400 has been modified following service experience. P/N 
A4937021700400 is installed on airplanes by Airbus Modification 10323 
and is two-way interchangeable with P/N A4937021700200. Airbus advises 
that an adapter having either P/N will fully comply with the intent of 
the French airworthiness directive. The FAA has determined that 
installation of an adapter having either P/N will adequately address 
the unsafe condition identified in this AD. A NOTE has been added to 
the final rule to state that installation of an adapter having P/N 
A4937021700400 is also acceptable for compliance with the requirements 
of paragraph (b) of the AD.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 165 airplanes of U.S. registry that will be 
affected by this AD.
    The actions that are currently required by AD 91-20-07 take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $120 per airplane.
    The new actions that are required by this new AD will take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$274 per airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $394 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 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 final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-8041 (56 FR 
47672, September 20, 1991), and by adding a new airworthiness directive 
(AD), amendment 39-11556, to read as follows:

2000-02-38  Airbus Industrie: Amendment 39-11556. Docket 99-NM-23-
AD. Supersedes AD 91-20-07, Amendment 39-8041.

    Applicability: Model A300, A300-600, and A310 series airplanes; 
certificated in any category; equipped with an auxiliary power unit 
(APU) fuel feedline adapter, P/N A4937021700000 (welded 
configuration).

    Note 1:  This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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.

[[Page 5753]]

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 an APU compartment fire, accomplish the following:

Restatement of Requirements of AD 91-20-07, Amendment 39-8041

Repetitive Inspections

    (a) Within 100 hours time-in-service after October 7, 1991 (the 
effective date of AD 91-20-07, amendment 39-8041), and thereafter at 
intervals not to exceed 400 hours time-in-service: Perform a dye 
penetrant inspection to detect cracks, rupture or fuel leaks at the 
weld of the fuel feedline adapter, in accordance with Airbus 
Industrie All Operators Telex (AOT) 49-01, Issue 3, dated April 25, 
1991. If cracks, rupture, or fuel leaks are found, replace the 
adapter with an improved, non-welded one-piece-body adapter prior to 
the next APU operation, or placard the APU inoperative until the 
adapter is replaced with the improved adapter, in accordance with 
Airbus Industrie Service Bulletin A300-49-0049, A300-49-6009, or 
A310-49-2012; all dated July 12, 1991; as applicable.
    (b) Within 100 hours time-in-service after October 7, 1991, 
verify the correct torque values of the starter motor cable 
terminals and the generator cable terminals in accordance with 
Airbus Industrie All Operators Telex (AOT) 49-01, Issue 3, dated 
April 25, 1991. Correct any torque value discrepancies prior to 
further flight, in accordance with the AOT.

New Requirements of This AD

Installation

    (c) Within 15 months after the effective date of this AD, 
install an improved APU fuel feedline adapter in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-49-0049, 
Revision 1 (for Model A300 series airplanes); A300-49-6009, Revision 
1 (for Model A300-600 series airplanes); or A310-49-2012, Revision 1 
(for Model A310 series airplanes); all dated November 28, 1991; as 
applicable. Such installation constitutes terminating action for the 
requirements of this AD.

    Note 2: Although the service bulletins referenced in paragraph 
(b) of this AD specify installation of an APU fuel feedline adapter 
having part number P/N A4937021700200, installation of an adapter 
having P/N A4937021700400 is also acceptable for compliance with the 
requirements of that paragraph.

Spares

    (d) As of the effective date of this AD, no person shall install 
an APU fuel feedline adapter, P/N A4937021700000 (welded 
configuration), on any airplane.

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 
Secs. 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

    (g) The actions shall be done in accordance with the following 
Airbus All Operators Telex (AOT) and Airbus service bulletins:

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Service information referenced and
               date                                 Page No.                       Revision level shown on page               Date shown on page
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AOT 49-01, Issue 3, April 25, 1991  1-3....................................  3......................................  April 25, 1991.
A300-49-0049, July 12, 1991.......  1-11...................................  Original...............................  July 12, 1991.
A300-49-0049, Revision 1, November  1-4, 7, 8, 11..........................  1......................................  November 28, 1991.
 28, 1991.
                                    5, 6, 9, 10............................  Original...............................  July 12, 1991.
A300-49-6009, July 12, 1991.......  1-9....................................  Original...............................  July 12, 1991.
A300-49-6009, Revision 1, November  1-6, 9.................................  1......................................  November 28, 1991.
 28, 1991.
                                    7, 8...................................  Original...............................  July 12, 1991.
A310-49-2012, July 12, 1991.......  1-11...................................  Original...............................  July 12, 1991.
A310-49-2012, Revision 1, November  1-4, 7, 8, 11..........................  1......................................  November 28, 1991.
 28, 1991.
                                    5, 6, 9, 10............................  Original...............................  July 12, 1991.
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    (1) The incorporation by reference of Airbus Service Bulletin 
A300-49-0049, Revision 1, dated November 28, 1991; Airbus Service 
Bulletin A300-49-6009, Revision 1, dated November 28, 1991; and 
Airbus Service Bulletin A310-49-2012, Revision 1, dated November 28, 
1991; is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Airbus All Operators Telex 
(AOT) 49-01, Issue 3, dated April 25, 1991; Airbus Service Bulletin 
A300-49-0049, dated July 12, 1991; Airbus Service Bulletin A300-49-
6009, dated July 12, 1991; and Airbus Service Bulletin A310-49-2012; 
dated July 12, 1991; was approved previously by the Director of the 
Federal Register as of October 7, 1991 (56 FR 47672, September 20, 
1991).
    (3) 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 98-480-269(B), dated December 2, 1998.


    (h) This amendment becomes effective on March 13, 2000.

    Issued in Renton, Washington, on January 31, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-2469 Filed 2-4-00; 8:45 am]
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