[Federal Register Volume 60, Number 98 (Monday, May 22, 1995)]
[Rules and Regulations]
[Pages 27007-27008]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-11908]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-146-AD; Amendment 39-9229; AD 95-10-12]


Airworthiness Directives; Airbus Model A320-111, -211, and -212 
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 certain Airbus Model A320-111, -211, and -212 series 
airplanes, that requires modification of the junction box and connector 
backshells of a certain electrical harness assembly. This amendment is 
prompted by a report indicating that traces of fungus and corrosion 
have been found on the electrical harness junction box of the thrust 
reverser. The actions specified by this AD are intended to prevent such 
corrosion, which could result in multiple faults in the thrust reverser 
position indication, and subsequent uncontrolled reduction of engine 
power.

DATES: Effective June 21, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 21, 1995.

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: Stephen Slotte, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1320.

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 A320-111, -
211, and -212 series airplanes was published in the Federal Register on 
December 27, 1994 (59 FR 66493). That action proposed to require 
modification of the junction box and connector backshells of the 
electrical harness assembly of the thrust reverser.
    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.
    Since issuance of the notice, Airbus has issued Service Bulletin 
A320-71-1011, Revision 1, dated June 27, 1994. This service bulletin is 
essentially identical to the original issue, but contains certain 
editoral changes. The FAA has revised the final rule to include 
reference to this revision of the service bulletin as an alternative 
source of service information.
    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.
    The FAA estimates that 50 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 24 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Required parts will be supplied by ROHR, 
Inc. (the manufacturer of the junction box, connector backshells, and 
the electrical harness assembly) at no cost to the operators. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $72,000, or $1,440 per airplane.
    The total cost impact figure discussed above is 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 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

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

95-10-12  Airbus Industrie: Amendment 39-9229. Docket 94-NM-146-AD.

    Applicability: Model A320-111, -211, and -212 series airplanes 
powered by CFM 56-5A engines equipped with an electrical harness 
assembly having part number (P/N) 238W0908-513; on which Airbus 
Modification 23693 (reference Airbus Service Bulletin A320-71-1011) 
has not been installed; 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 use the authority 
[[Page 27008]] provided in paragraph (b) to request approval from 
the FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously. -To prevent multiple faults in the thrust reverser 
position indication, and subsequent uncontrolled reduction of engine 
power, accomplish the following:
    (a) Within 3,000 flight hours after the effective date of this 
AD, modify the junction box, connector backshells, and the 
electrical harness assembly of the thrust reverser, in accordance 
with Airbus Service Bulletin A320-71-1011, dated November 17, 1993, 
or Revision 1, dated June 27, 1994.
    (b) 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, 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) 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.
    (d) The modification shall be done in accordance with Airbus 
Service Bulletin A320-71-1011, dated November 17, 1993; or in 
accordance with Airbus Service Bulletin A320-71-1011, Revision 1, 
dated June 27, 1994, which contains the following list of effective 
pages:

------------------------------------------------------------------------
                                         Revision                       
                                           level                        
               Page No.                  shown on    Date shown on page 
                                           page                         
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1, 4-6................................  1.........  June 27, 1994.      
2, 3, 7-11............................  Original..  Nov. 17, 1993.      
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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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on June 21, 1995.

    .Issued in Renton, Washington, on May 9, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-11908 Filed 5-19-95; 8:45 am]
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