[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]
BILLING CODE 4910-13-U
