[Federal Register Volume 61, Number 245 (Thursday, December 19, 1996)]
[Rules and Regulations]
[Pages 66881-66884]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-31113]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-176-AD; Amendment 39-9846; AD 96-25-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 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 A320 series airplanes, that 
currently requires inspections to detect chafing of the wire looms 
(bundles) in the wing and the horizontal stabilizer; and repair or 
replacement, protection, and realignment, if necessary. This amendment 
requires that those actions also be accomplished in certain areas of 
the main landing gear (MLG) bays. This amendment also requires 
installation of protective sleeves around the wire bundles, and 
realignment of bundles that are not guided centrally into the conduit 
end fittings, which constitutes terminating action for the repetitive 
inspections. This amendment is prompted by a report that electrical 
short circuiting could occur in the wire bundles in the MLG bays. The 
actions specified by this AD are intended to prevent such electrical 
short circuiting due to chafing of the wire bundles in the wing, 
horizontal stabilizer, or MLG bays.

DATES: Effective January 27, 1997. The incorporation by reference of 
Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993; 
and Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 
1993, as listed in the regulations, is approved by the Director of the 
Federal Register as of January 27, 1997.
    The incorporation by reference of Airbus Service Bulletin A320-24-
1044, Revision 2, dated March 3, 1992; and Airbus Service Bulletin 
A320-24-1045, Revision 2, dated April 12, 1992; as listed in the 
regulations was approved previously by the Director of the Federal 
Register as of December 3, 1992 (57 FR 48957).

ADDRESSES: The service information referenced in this AD may be 
obtained

[[Page 66882]]

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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 92-22-02, 
amendment 39-8388 (57 FR 48957, October 29, 1992), which is applicable 
to certain Airbus Model A320 series airplanes, was published in the 
Federal Register on September 11, 1996 (61 FR 47835). The action 
proposed to supersede AD 92-22-02 to continue to require inspections to 
detect chafing of the wire bundles in the wing and the horizontal 
stabilizer; and repair or replacement, protection, and realignment, if 
necessary. The action also proposed to require that these actions be 
accomplished in certain areas of the MLG bays. Additionally, the action 
proposed to require installation of protective sleeves around the wire 
bundles, and realignment of bundles that are not guided centrally into 
the conduit end fittings, which would constitute terminating action for 
the repetitive inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    Both commenters support the proposed rule.

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 as proposed.

Cost Impact

    There are approximately 30 Model A320 series airplanes of U.S. 
registry that will be affected by this proposed AD.
    The actions that are currently required by AD 92-22-02 take 
approximately 31 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 actions currently required on U.S. operators is estimated 
to be $55,800, or $1,860 per airplane.
    The inspections that are required by this new AD action will take 
approximately 31 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 required inspections on U.S. operators is estimated to be 
$55,800, or $1,860 per airplane.
    The installation that is required by this AD action takes 
approximately 59 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. The cost for required parts is 
negligible. Based on these figures, the cost impact of the installation 
on U.S. operators is estimated to be $106,200, or $3,540 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 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 39-8388 (57 FR 
48957, October 29, 1992), and by adding a new airworthiness directive 
(AD), amendment 39-9846, to read as follows:

    96-25-04 Airbus Industrie: Amendment 39-9846. Docket 95-NM-176-
AD. Supersedes AD 92-22-02, Amendment 39-8388.

    Applicability: Model A320 series airplanes on which Airbus 
Modification No. 22109 (Airbus Service Bulletin A320-24-1045, 
Revision 3, dated June 10, 1993) has not 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 (h) 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 short circuiting due to chafing of the 
wire bundles in the wing, horizontal stabilizer, or main landing 
gear (MLG) bay, accomplish the following:

Restatement of Requirements of AD 92-22-02

    (a) For airplanes having manufacturer's serial numbers through 
169 inclusive: Prior to the accumulation of 450 hours time-in-
service after December 3, 1992 (the effective date of AD 92-22-02, 
amendment 39-8388), inspect the wire bundles in wing zones 574 and 
674 through panels 574AB and 674AB to detect chafing or contact with 
the end fittings of the protective conduit, in accordance with 
Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 
1992, or Revision 3, dated March 12, 1993. Thereafter, repeat this 
inspection at intervals not to exceed 450 hours time-in-service 
until the inspection required by paragraph (c) of this AD is 
accomplished.
    (1) If any chafed or damaged wire is found, prior to further 
flight, repair or replace it in accordance with the Airplane 
Maintenance Manual or the Aircraft Wiring Manual.
    (2) If any wire bundle is found in contact with the edge of the 
conduit end fitting, or

[[Page 66883]]

which might come in contact with the edge of the conduit end fitting 
due to vibration in flight, prior to further flight, realign and 
protect the bundle in accordance with Airbus Service Bulletin A320-
24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 
10, 1993; or in accordance with the temporary repair described in 
paragraph 2.B.(2)(b) of Airbus Service Bulletin A320-24-1044, 
Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 
1993.
    (b) For airplanes having manufacturer's serial numbers through 
169 inclusive: Prior to the accumulation of 1,500 hours time-in-
service after December 3, 1992, inspect the wire bundles in the wing 
and horizontal stabilizer, excluding wing zones 574 and 674 through 
panels 574AB and 674AB, to detect chafing or contact with the ending 
fittings of the protective conduit, in accordance with Airbus 
Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or 
Revision 3, dated March 12, 1993. Thereafter, repeat this inspection 
at intervals not to exceed 3,500 hours time-in-service until the 
inspection required by paragraph (d) of this AD is accomplished.
    (1) If any chafed or damaged wire is found, prior to further 
flight, repair or replace it in accordance with the Airplane 
Maintenance Manual or the Aircraft Wiring Manual.
    (2) If any wire bundle is found in contact with the edge of the 
conduit end fitting, or which might come in contact with the edge of 
the conduit end fitting due to vibration in flight, prior to further 
flight, realign and protect the bundle in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or 
Revision 3, dated June 10, 1993; or in accordance with the temporary 
repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin 
A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated 
March 12, 1993.

New Requirements of This AD

    (c) For all airplanes: Prior to the accumulation of 450 hours 
time-in-service after the effective date of this AD, inspect the 
wire bundles in wing zones 574 and 674 through panels 574AB and 
674AB to detect damage, contact chafing, or contact with the end 
fittings of the protective conduit, in accordance with Airbus 
Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or 
Revision 3, dated March 12, 1993. Thereafter, repeat this inspection 
at intervals not to exceed 450 hours time-in-service. Accomplishment 
of this inspection terminates the inspections required by paragraph 
(a) of this AD.
    (1) If any chafed or damaged wire is found, prior to further 
flight, accomplish the requirements of paragraphs (c)(1)(i) and 
(c)(1)(ii) of this AD.
    (i) Repair or replace the wire in accordance with the Airplane 
Maintenance Manual or the Aircraft Wiring Manual. And
    (ii) Protect the wire bundle in accordance with Airbus Service 
Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 
3, dated June 10, 1993; or in accordance with the temporary repair 
described in paragraph 2.B.(2)(b) of Airbus Service Bulletin A320-
24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 
12, 1993.
    (2) If any wire bundle is found in contact with the edge of the 
conduit end fitting, or which might come in contact with the edge of 
the conduit end fitting due to vibration in flight, prior to further 
flight, realign and protect the bundle in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or 
Revision 3, dated June 10, 1993; or in accordance with the temporary 
repair described in paragraph 2.B.(2)(b) of Airbus Service Bulletin 
A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated 
March 12, 1993.
    (d) For all airplanes: Prior to the accumulation of 1,500 hours 
time-in-service after the effective date of this AD, inspect the 
wire bundles in the wing and horizontal stabilizer, excluding wing 
zones 574 and 674 through panels 574AB and 674AB, to detect chafing 
or contact with the ending fittings of the protective conduit, in 
accordance with Airbus Service Bulletin A320-24-1044, Revision 2, 
dated March 3, 1992, or Revision 3, dated March 12, 1993. 
Thereafter, repeat this inspection at intervals not to exceed 3,500 
hours time-in-service. Accomplishment of this paragraph terminates 
the inspections required by paragraph (b) of this AD.
    (1) If any chafed or damaged wire is found, prior to further 
flight, accomplish the requirements of paragraphs (d)(1)(i) and 
(d)(1)(ii) of this AD.
    (i) Repair or replace the wire in accordance with the Airplane 
Maintenance Manual or the Aircraft Wiring Manual. And
    (ii) Protect the wire bundle in accordance with Airbus Service 
Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 
3, dated June 10, 1993; or in accordance with the temporary repair 
described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320-
24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 
12, 1993.
    (2) If any wire bundle is found in contact with the edge of the 
conduit end fitting, or which might come in contact with the edge of 
the conduit end fitting due to vibration in flight, prior to further 
flight, realign and protect the bundle in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or 
Revision 3, dated June 10, 1993; or in accordance with the temporary 
repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin 
A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated 
March 12, 1993.
    (e) For all airplanes: Prior to the accumulation of 1,500 hours 
time-in-service after the effective date of this AD, inspect the 
wire bundles in the MLG bays to detect chafing or contact with the 
end fittings of the protective conduit, in accordance with Airbus 
Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993. 
Thereafter, repeat this inspection at intervals not to exceed 3,500 
hours time-in-service.
    (1) If any chafed or damaged wire is found, prior to further 
flight, accomplish the requirements of paragraphs (e)(1)(i) and 
(e)(1)(ii) of this AD.
    (i) Repair or replace the wire in accordance with the Airplane 
Maintenance Manual or the Aircraft Wiring Manual. And
    (ii) Protect the wire bundle in accordance with Airbus Service 
Bulletin A320-24-1045, Revision 3, dated June 10, 1993; or in 
accordance with the temporary repair described in paragraph 
2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 3, 
dated March 12, 1993.
    (2) If any wire bundle is found in contact with the edge of the 
conduit end fitting, or which might come in contact with the edge of 
the conduit end fitting due to vibration in flight, prior to further 
flight, realign and protect the bundle in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993; or 
in accordance with the temporary repair described in paragraph 
2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 3, 
dated March 12, 1993.
    (f) If a temporary repair over a damaged length of wire bundle 
is accomplished in accordance with paragraph (a)(2), (b)(2), (c)(2), 
(d)(2), or (e)(2) of this AD: Prior to the accumulation of 450 hours 
time-in-service, replace the temporary repair with a protective 
sleeve around the wire bundle, and realign the bundle if it is not 
guided centrally into the conduit end fittings. Accomplish these 
actions in accordance with Airbus Service Bulletin A320-24-1045, 
Revision 3, dated June 10, 1993. Accomplishment of these actions 
terminates the repetitive inspections required by paragraph (c), 
(d), or (e) of this AD, as applicable.

    Note 2: Accomplishment of the actions in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, is 
acceptable for compliance with the requirements of paragraph (f) of 
this AD for the areas specified in paragraphs (c) and (d) of this 
AD.

    (g) For all airplanes: Prior to the accumulation of 7,000 hours 
time-in-service after the effective date of this AD, install 
protective sleeves around the wire bundles, and realign any bundle 
that is not guided centrally into the conduit end fittings, in wing 
zones 574 and 674 through panels 574AB and 674AB, in the wing and 
horizontal stabilizer, excluding wing zones 574 and 674 through 
panels 574AB and 674AB, and in the MLG bays, in accordance with 
Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 
1993. Accomplishment of these actions constitutes terminating action 
for the repetitive inspections required by this AD.

    Note: 3: Accomplishment of the actions in accordance with Airbus 
Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, is 
acceptable for compliance with the requirements of paragraph (g) of 
this AD for the areas specified in paragraphs (c) and (d) of this 
AD.

    (h) 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, Manager, Standardization Branch, 
ANM-113, 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, 
Standardization Branch, ANM-113.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be

[[Page 66884]]

obtained from the Standardization Branch, ANM-113.
    (i) 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.
    (j) The actions shall be done in accordance with the following 
Airbus Industrie service bulletins, as applicable, which contain the 
specified list of effective pages:

----------------------------------------------------------------------------------------------------------------
 Service bulletin  referenced                             Revision level  shown on                              
           and date                    Page No.                     page                 Date  shown on page    
----------------------------------------------------------------------------------------------------------------
A320-24-1044, Revision 2 March  1-6, 8, 8A, 8B, 9, 12,  2..........................  March 3, 1992.             
 3, 1992.                        16.                                                                            
                                7, 10, 11, 13-15, 17-   1..........................  August 23, 1991.           
                                 23.                                                                            
A320-24-1044, Revision 3,       1-6, 8A, 13, 24.......  3..........................  March 12, 1993.            
 March 12, 1993.                                                                                                
                                7, 10, 11, 14, 15, 17-  1..........................  August 23, 1991.           
                                 23.                                                                            
                                8, 8B, 9, 12, 16......  2..........................  March 3, 1992.             
A320-24-1045, Revision 2,       1, 2, 4-8, 8A, 8B, 23.  1..........................  August 23, 1991.           
 April 12, 1992.                                                                                                
                                3, 9, 14-16, 10-13, 17- Original...................  February 1, 1991.          
                                 22.                                                                            
A320-24-1045, Revision 3, June  1-3, 6, 8A, 9 11, 21,   3..........................  June 10, 1993.             
 10, 1993.                       22.                                                                            
                                4, 5, 7, 8, 8B, 23....  2..........................  April 12, 1992.            
                                10, 12-14, 17-20......  Original...................  February 1, 1991.          
                                15, 16................  1..........................  August 23, 1991.           
----------------------------------------------------------------------------------------------------------------

    The incorporation by reference of Airbus Service Bulletin A320-
24-1044, Revision 2, dated March 3, 1992; and Airbus Service 
Bulletin A320-24-1045, Revision 2, dated April 12, 1992; was 
approved previously by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of December 3, 
1992 (57 FR 48957, October 29, 1992). The incorporation by reference 
of Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 
1993; and Airbus Service Bulletin A320-24-1045, Revision 3, dated 
June 10, 1993; 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.
    (k) This amendment becomes effective on January 23, 1997.

    Issued in Renton, Washington, on December 2, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-31113 Filed 12-18-96; 8:45 am]
BILLING CODE 4910-13-U