[Federal Register Volume 65, Number 114 (Tuesday, June 13, 2000)]
[Rules and Regulations]
[Pages 37019-37022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-14437]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-128-AD; Amendment 39-11772; AD 2000-11-23]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, 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 all Airbus Model A300, A310, and A300-600 series 
airplanes, that requires an inspection to detect damage of the 
electrical bonding leads in specified locations of the fuel tanks, and 
replacement of any damaged

[[Page 37020]]

electrical bonding leads with serviceable electrical bonding leads. For 
certain airplanes, this amendment also requires modifying the fuel pipe 
couplings in specified locations of the fuel tank. 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 electrical arcing/discharge in the fuel 
tank due to damaged electrical bonding leads or inadequate electrical 
bonding of the fuel pipe couplings, which could result in fuel ignition 
and consequent uncontained rupture of the fuel tank.

DATES: Effective July 18, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 18, 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, 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) to include an airworthiness 
directive (AD) that is applicable to all Airbus Model A300, A310, and 
A300-600 series airplanes was published in the Federal Register on 
March 27, 2000 (65 FR 16151). That action proposed to require an 
inspection to detect damage of the electrical bonding leads in 
specified locations of the fuel tanks, and replacement of any damaged 
electrical bonding leads with serviceable electrical bonding leads. For 
certain airplanes, that action also proposed to require modifying the 
fuel pipe couplings in specified locations of the fuel tank.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal 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 116 airplanes of U.S. registry will be 
affected by this AD.
    It will take between 70 and 80 work hours per airplane to 
accomplish the required inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the required 
inspection on U.S. operators is estimated to be between $487,200 and 
$556,800, or between $4,200 and $4,800 per airplane.
    It will take between 77 and 103 work hours per airplane to 
accomplish the required modification, at an average labor rate of $60 
per work hour. Required parts will cost approximately $104 per 
airplane. Based on these figures, the cost impact of the required 
modification on U.S. operators is estimated to be between $547,984 and 
$728,944, or between $4,724 and $6,284 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 adding the following new 
airworthiness directive:

2000-11-23  Airbus Industrie: Amendment 39-11772. Docket 99-NM-128-
AD.

    Applicability: All Model A300, A310, and A300-600 series 
airplanes, certificated in any category.

    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 (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 electrical arcing/discharge in the fuel tank due to 
damaged electrical bonding leads or inadequate electrical bonding of 
the fuel pipe couplings, which could result in fuel ignition and 
consequent uncontained rupture of the fuel tank, accomplish the 
following:

Inspection

    (a) Within 36 months after the effective date of this AD, 
perform a one-time inspection to detect damage (i.e., breakage, 
fraying, abrasion damage, looseness of the outer metal braid 
protection in the end crimp, looseness of the outer metal braid 
protection on the bonding lead inner core, corrosion, or missing 
leads) of the electrical bonding leads in specified locations of the 
fuel tanks, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletins A300-28-0072, Revision 01, dated October 
01, 1998, including Appendix 1, dated October 01, 1998, and Appendix 
2, dated February 20, 1998 (for

[[Page 37021]]

Model A300 series airplanes); A310-28-2128, Revision 01, dated 
October 01, 1998, including Appendix 1, dated October 01, 1998, and 
Appendix 2, dated February 20, 1998 (for Model A310 series 
airplanes); or A300-28-6057, Revision 01, dated October 01, 1998, 
including Appendix 1, dated October 01, 1998, and Appendix 2, dated 
February 20, 1998 (for Model A300-600 series airplanes); as 
applicable.

    Note 2: Inspection of the area specified in paragraph (a) of 
this AD accomplished prior to the effective date of this AD in 
accordance with Airbus Service Bulletins A300-28-0072, A310-28-2128, 
or A300-28-6057; all dated February 20, 1998; as applicable; is 
considered acceptable for compliance with the requirements of 
paragraph (a) of this AD.

Replacement

    (b) If any electrical bonding lead is damaged, prior to further 
flight, replace the bonding lead with a serviceable bonding lead in 
accordance with the applicable service bulletin specified in 
paragraph (a) of this AD.

Modification

    (c) For airplanes on which Airbus Industrie Modification 11847 
(for Model A310 series airplanes) or 11848 (for Model A300/A300-600 
series airplanes) has not been accomplished, within 36 months after 
the effective date of this AD, modify the fuel pipe couplings in the 
specified locations of the fuel tank in accordance with the 
Accomplishment Instructions of Airbus Service Bulletins A300-28-
0073, Revision 01, dated October 01, 1998 (for Model A300 series 
airplanes); A310-28-2130, Revision 01, dated October 01, 1998 (for 
Model A310 series airplanes); or A300-28-6058, Revision 01, dated 
October 01, 1998 (for Model A300-600 series airplanes); as 
applicable.

    Note 3: Modification of the fuel pipe couplings accomplished 
prior to the effective date of this AD in accordance with Airbus 
Service Bulletins A300-28-0073, A310-28-2130, or A300-28-6058; all 
dated February 20, 1998; as applicable; is considered acceptable for 
compliance with the requirements of paragraph (c) of this AD.

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.

Special Flight Permits

    (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 the following 
Airbus service bulletins, as applicable:

----------------------------------------------------------------------------------------------------------------
                                                             Revision level shown on
       Service bulletin No.                Page No.                   page                 Date shown on page
----------------------------------------------------------------------------------------------------------------
A300-28-0072, Revision 01, October  1-14.................  01........................  Oct. 01, 1998.
 01, 1998.
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                                                   Appendix 1
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                                    1-21, 23-25, 27, 29-   Original..................  Feb. 20, 1998.
                                     36, 38-84, 88-95, 97-
                                     166.
                                    22, 26, 28, 37, 85-    01........................  Oct. 01, 1998.
                                     87, 96.
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                                                   Appendix 2
----------------------------------------------------------------------------------------------------------------
                                    1-54.................  Original..................  Feb. 20, 1998.
 
A310-28-2128, Revision 01, October  1-14.................  01........................  Oct. 01, 1998.
 01, 1998.
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                                                   Appendix 1
----------------------------------------------------------------------------------------------------------------
                                    1-30, 32-83, 85-87,    Original..................  Feb. 20, 1998.
                                     89-95, 97-221, 223-
                                     226.
                                    31, 84, 88, 96, 222..  01........................  Oct. 01, 1998.
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                                                   Appendix 2
----------------------------------------------------------------------------------------------------------------
                                    1-56.................  Original..................  Feb. 20, 1998
A300-28-6057, Revision 01, October  1-14.................  01........................  Oct. 01, 1998.
 01, 1998
----------------------------------------------------------------------------------------------------------------
                                                   Appendix 1
----------------------------------------------------------------------------------------------------------------
                                    1-18, 21-25, 27-29,    Original..................  Feb. 20, 1998.
                                     31, 33, 34, 36, 38,
                                     40, 42, 44-78, 81-
                                     85, 87-89, 91, 93,
                                     94, 96, 98-100, 102,
                                     104-229, 231-234.
                                    19, 20, 26, 30, 32,    01........................  Oct. 01, 1998.
                                     35, 37, 39, 41, 43,
                                     79, 80, 86, 90, 92,
                                     95, 97, 101, 103,
                                     230.
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                                                   Appendix 2
----------------------------------------------------------------------------------------------------------------
                                    1-54.................  Original..................  Feb. 20, 1998.
 
A300-28-0073, Revision 01, October  1-67.................  01........................  Oct. 01, 1998.
 01, 1998.
 
A310-28-2130, Revision 01, October  1-91.................  01........................  Oct. 01, 1998.
 01, 1998.
A300-28-6058, Revision 01, October  1-67.................  01........................  Oct. 01, 1998.
 01, 1998.
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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

[[Page 37022]]

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 directive 98-174-248(B), dated April 22, 1998.

    (g) This amendment becomes effective on July 18, 2000.

    Issued in Renton, Washington, on June 2, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14437 Filed 6-12-00; 8:45 am]
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