AD 2002-04-05

[Federal Register Volume 67, Number 38 (Tuesday, February 26, 2002)]
[Rules and Regulations]
[Pages 8705-8707]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-4225]



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Federal Register / Vol. 67, No. 38 / Tuesday, February 26, 2002 / 
Rules and Regulations

[[Page 8705]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-205-AD; Amendment 39-12662; AD 2002-04-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; Model A300 F4-605R Airplanes; Model A300 B4-600 and A300 B4-
600R Series Airplanes; and Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300 B2 and A300 B4 series 
airplanes; certain Model A300 F4-605R airplanes and Model A300 B4-600 
and A300 B4-600R series airplanes; and certain Model A310 series 
airplanes, that requires repetitive inspections to detect damage of the 
fillet seals and feeder cables, and of the wiring looms in the wing/
pylon interface area; and corrective action, if necessary. This 
amendment also provides for optional terminating action for the 
repetitive inspections. The actions specified by this AD are intended 
to prevent wire chafing and short circuits in the wing leading edge/
pylon interface area, which could result in loss of the power supply 
generator and/or system functions. This action is intended to address 
the identified unsafe condition.

DATES: Effective April 2, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 2, 2002.

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 A300 B2 and 
A300 B4 series airplanes; certain Model A300 F4-605R airplanes and 
Model A300 B4-600 and A300 B4-600R series airplanes; and certain Model 
A310 series airplanes; was published as a supplemental notice of 
proposed rulemaking (NPRM) in the Federal Register on January 2, 2002 
(67 FR 40). That action proposed to continue to require repetitive 
inspections to detect damage of the fillet seals and feeder cables, and 
of the wiring looms in the wing/pylon interface area; and corrective 
action, if necessary. That action also proposed to provide for optional 
terminating action for the repetitive inspections. Additionally, that 
action proposed to require that actions be done in accordance with 
newly revised service bulletins, and to revise the applicability.

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 107 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 6 work hours per airplane to inspect the 
seals/cables at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this required inspection on U.S. 
operators is estimated to be $38,520, or $360 per airplane, per 
inspection cycle.
    It will take approximately 5 work hours per airplane to inspect the 
wiring looms and apply the protection, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this required 
inspection on U.S. operators is estimated to be $32,100, or $300 per 
airplane, per inspection cycle.
    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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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

[[Page 8706]]

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:

2002-04-05 Airbus Industrie: Amendment 39-12662. Docket 2001-NM-205-
AD.
    Applicability: The following airplanes, certificated in any 
category:

                         Table 1.--Applicability
------------------------------------------------------------------------
                                  Excluding those modified per Airbus
           Model--                           Modification--
------------------------------------------------------------------------
A300 B2-1C, A300 B2-203, A300  11349 and 12309.
 B2K-3C, and A300 B4 series
 airplanes.
A300 B4-600 series airplanes,  11348 and 12303.
 A300 B4-600R series
 airplanes, and A300 F4-605R
 airplanes.
A310 series airplanes........  11350 and 12310.
------------------------------------------------------------------------


    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 wire chafing and short circuits in the wing leading 
edge/pylon interface area, which could result in loss of the power 
supply generator and/or system functions, accomplish the following:

Inspections

    (a) Within 600 flight hours after the effective date of this AD, 
perform a detailed visual inspection to detect damage (including 
erosion and tearing) and deterioration of the fillet seals and 
feeder cables, in accordance with Airbus Service Bulletin A300-24-
0053, Revision 06, dated September 10, 2001 (for Model A300 series 
airplanes); A300-24-6011, Revision 05, dated May 18, 2001 (for Model 
A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R series 
airplanes); or A310-24-2021, Revision 06, dated May 18, 2001 (for 
Model A310 series airplanes). Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight hours, until the actions 
specified by paragraph (c) are accomplished.
    (1) If no damage is detected: Prior to further flight following 
the initial inspection only, apply protection to each feeder cable 
in accordance with the applicable service bulletin.
    (2) If any damage is detected: Prior to further flight, repair 
in accordance with the applicable service bulletin.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Airbus Service Bulletins A300-24-0053, A300-24-6011, and 
A310-24-2021 refer to Airbus Service Bulletins A300-24-054, A300-24-
6013, and A310-24-2024, respectively, as additional sources of 
service information for repair.

    (b) Within 600 flight hours after the effective date of this AD: 
Perform a detailed visual inspection of the wiring looms in the area 
of the wing leading edge/pylon interface to detect damage (including 
chafing, burning, and short circuits), in accordance with Airbus 
Service Bulletin A300-24-0083, Revision 03, dated January 3, 2001 
(for Model A300 series airplanes); A300-24-6039, Revision 07, dated 
August 9, 2001 (for Model A300 F4-605R airplanes and Model A300 B4-
600 and A300 B4-600R series airplanes); or A310-24-2052, Revision 
04, dated April 6, 2001 (for Model A310 series airplanes); as 
applicable. Repeat the inspection thereafter at least every 1,000 
flight hours, until the actions specified by paragraph (c) of this 
AD have been accomplished.
    (1) If no damage is detected: Prior to further flight following 
the initial inspection only, apply protection in accordance with the 
applicable service bulletin.
    (2) If any damage is detected: Prior to further flight, repair 
in accordance with the applicable service bulletin.

Optional Terminating Action

    (c) Replacement of the fillet panel assemblies with new, 
improved assemblies, as specified by paragraphs (c)(1), (c)(2), or 
(c)(3) of this AD, as applicable, terminates the requirements of 
this AD.
    (1) For Model A300 series airplanes: Replacement of the fillet 
panel assemblies, if accomplished, must be done as specified by 
paragraph (c)(1)(i) or (c)(1)(ii) of this AD.
    (i) For airplanes in the common pylon configuration: In 
accordance with Airbus Service Bulletin A300-54-0095, Revision 01, 
dated January 3, 2001, or Revision 02, dated September 7, 2001.
    (ii) For airplanes in the basic pylon configuration: In 
accordance with Airbus Service Bulletin A300-54-0095, Revision 02, 
dated September 7, 2001.
    (2) For Model A300 F4-605R airplanes and Model A300 B4-600 and 
A300 B4-600R series airplanes: Replacement of the fillet panel 
assemblies, if accomplished, must be done in accordance with Airbus 
Service Bulletin A300-54-6032, Revision 03, dated January 3, 2001.
    (3) For Model A310 series airplanes: Replacement of the fillet 
panel assemblies, if accomplished, must be done in accordance with 
Airbus Service Bulletin A310-54-2033, Revision 01, dated January 3, 
2001.

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, 
Transport Airplane Directorate, FAA. 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 
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.

[[Page 8707]]

Incorporation by Reference

    (f) The actions required by paragraph (a) of this AD shall be 
done in accordance with Airbus Service Bulletin A300-24-0053, 
Revision 06, dated September 10, 2001; Airbus Service Bulletin A300-
24-6011, Revision 05, dated May 18, 2001; or Airbus Service Bulletin 
A310-24-2021, Revision 06, dated May 18, 2001. The actions required 
by paragraph (b) of this AD shall be done in accordance with Airbus 
Service Bulletin A300-24-0083, Revision 03, dated January 3, 2001; 
Airbus Service Bulletin A300-24-6039, Revision 07, dated August 9, 
2001; or Airbus Service Bulletin A310-24-2052, Revision 04, dated 
April 6, 2001; as applicable. The optional replacement provided in 
paragraph (c) of this AD, if accomplished, shall be done in 
accordance with Airbus Service Bulletin A300-54-0095, Revision 01, 
dated January 3, 2001; Airbus Service Bulletin A300-54-0095, 
Revision 02, dated September 7, 2001; Airbus Service Bulletin A300-
54-6032, Revision 03, dated January 3, 2001; or Airbus Service 
Bulletin A310-54-2033, Revision 01, dated January 3, 2001; 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.

Effective Date

    (g) This amendment becomes effective on April 2, 2002.

    Issued in Renton, Washington, on February 12, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-4225 Filed 2-25-02; 8:45 am]
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