Airworthiness Directives; Airbus Model A319-100, A320-200, and A321-100 and -200 Series Airplanes

[Federal Register Volume 70, Number 218 (Monday, November 14, 2005)]
[Rules and Regulations]
[Pages 69063-69065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22217]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19863; Directorate Identifier 2003-NM-29-AD; 
Amendment 39-14363; AD 2005-23-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319-100, A320-200, and 
A321-100 and -200 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A319-100, A320-200, and 
A321-100 and -200 series airplanes. That AD currently requires 
modification of the telescopic girt bar of the escape slide/raft 
assembly, and follow-on actions. This new AD requires a new 
modification of the telescopic girt bar and the installation of 
placards on the modified girt bars, which terminates the repetitive 
functional tests required by the existing AD. This AD results from 
development of a new, improved modification. We are issuing this AD to 
prevent failure of the escape slide/raft to deploy correctly, which 
could result in the slide being unusable during an emergency evacuation 
and consequent injury to passengers or airplane crewmembers.

DATES: This AD becomes effective December 19, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 19, 
2005.
    On August 31, 2001 (66 FR 42939, August 16, 2001), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
Industrie All Operators Telex A320-52A1111, Revision 01, dated July 23, 
2001, including Airbus Industrie Technical Disposition 959.1492/01, 
Issue C, dated July 17, 2001.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that supersedes AD 2001-16-14, 
amendment 39-12383 (66 FR 42939, August 16, 2001). The existing AD 
applies to certain Airbus Model A319, A320, and A321 series airplanes. 
That supplemental NPRM was published in the Federal Register on July 
21, 2005 (70 FR 42005). That supplemental NPRM proposed to mandate the 
installation of placards on the modified girt bars, which terminates 
the repetitive functional tests required by the existing AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the additional comment that 
has been received on the supplemental NPRM. The commenter supports the 
supplemental NPRM.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have changed this AD to clarify the appropriate procedure for 
notifying the principal inspector before using any approved AMOC on any 
airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD as proposed.

Costs of Compliance

    This AD will affect about 517 airplanes of U.S. registry.
    The modification that is required by AD 2001-16-14 and retained in 
this AD takes about 7 work hours per airplane, at an average labor rate 
of $65 per work hour. The cost of required parts is negligible. Based 
on these figures, the estimated cost of the currently required 
modification for U.S. operators is $235,235, or $455 per airplane.
    The functional test that is required by AD 2001-16-14 and retained 
in this AD takes about 1 work hour per airplane, at an average labor 
rate of $65 per work hour. Based on these figures, the cost impact of 
the currently required functional test for U.S. operators is $33,605, 
or $65 per airplane, per test cycle.
    For airplanes that have not been modified in accordance with AD 
2001-16-14: The new modification (including the new placard 
installation) takes about 17 work hours per airplane, at an average 
labor rate of $65 per work hour. Required parts cost about $5,130 per 
airplane. Based on these figures, the estimated cost of the new 
modification specified in this AD is $6,235 per airplane.
    For airplanes that have been modified in accordance with AD 2001-
16-14: The new modification (including the new placard installation) 
takes about 21 work hours per airplane, at an average labor rate of $65 
per work hour. Required parts cost about $5,130 per airplane. Based on 
these figures, the estimated cost of the new modification specified in 
this AD is $6,495 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.

[[Page 69064]]

    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12383 (66 FR 42939, August 16, 2001) and by 
adding the following new airworthiness directive (AD):

2005-23-05 Airbus: Amendment 39-14363. Docket No. FAA-2004-19863; 
Directorate Identifier 2003-NM-29-AD.

Effective Date

    (a) This AD becomes effective December 19, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-16-14.

Applicability

    (c) This AD applies to Airbus Model A319-111, -112, -113, -114, 
-115, -131, -132, and -133; A320-211, -212, -214, -231, -232, and -
233; and A321-111, -112, -131, -211, and -231 airplanes; 
certificated in any category; equipped with telescopic girt bars of 
the escape slide/raft assembly installed per Airbus Modification 
20234, or Airbus Service Bulletin A320-25-1055 or A320-25-1218 in 
service; except those airplanes with Airbus Modification 31708.

Unsafe Condition

    (d) This AD was prompted by development of a new, improved 
modification of the telescopic girt bar of the escape slide/raft 
assembly. We are issuing this AD to prevent failure of the escape 
slide/raft to deploy correctly, which could result in the slide 
being unusable during an emergency evacuation and consequent injury 
to passengers or airplane crewmembers.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2001-16-14

Modification/Follow-On Actions

    (f) For airplanes listed in Airbus Industrie All Operators Telex 
(AOT) A320-52A1111, Revision 01, dated July 23, 2001: Within 1,500 
flight hours after August 31, 2001 (the effective date of AD 2001-
16-14); except as provided by paragraph (h) of this AD, modify the 
telescopic girt bar of the escape slide/raft assembly installed on 
all passenger and crew doors and do a functional test to ensure the 
girt bar does not retract, per Airbus Industrie AOT A320-52A1111, 
Revision 01, dated July 23, 2001.
    (1) If the girt bar retracts, before further flight, replace any 
discrepant parts and do another functional test to ensure the girt 
bar does not retract, per the AOT. Repeat the functional test 
thereafter at intervals not to exceed 18 months until paragraph (g) 
of this AD is accomplished.
    (2) If the girt bar does not retract, repeat the functional test 
thereafter at intervals not to exceed 18 months.

    Note 1: Modification and follow-on actions accomplished prior to 
the effective date of this AD per Airbus Industrie AOT A320-52A1111, 
dated July 5, 2001, are considered acceptable for compliance with 
the applicable actions specified in this amendment.

New Requirements of This AD

Modification

    (g) Within 20 months after the effective date of this AD: 
Accomplish the actions specified in paragraphs (g)(1) and (g)(2) of 
this AD by doing all the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1112, 
Revision 05, dated June 25, 2004. Accomplishing these actions 
terminates the repetitive functional tests required by paragraph (f) 
of this AD.
    (1) Modify the telescopic girt bar of the escape slide/raft 
assembly.
    (2) Install a placard on each modified girt bar.
    (h) For airplanes on which the modification of the telescopic 
girt bar required by paragraph (g)(1) of this AD is accomplished 
within the compliance time specified in paragraph (f) of this AD, 
accomplishing the modification required by paragraph (f) is not 
required.

Modifications Accomplished According to Previous Issues of Service 
Bulletin

    (i) Modification of the telescopic girt bar accomplished before 
the effective date of this AD in accordance with Airbus Service 
Bulletin A320-52-1112, dated January 16, 2002; Revision 01, dated 
April 3, 2002; Revision 02, dated September 6, 2002; Revision 03, 
dated June 27, 2003; or Revision 04, dated November 12, 2003; is 
considered acceptable for compliance with the modification of the 
telescopic girt bar required by paragraph (g)(1) of this AD.

Parts Installation

    (j) As of the effective date of this AD, no person may install 
on any airplane a telescopic girt bar of the escape slide/raft 
assembly unless it has been modified as required by paragraph (g) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve alternative 
methods of compliance (AMOCs) for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously in accordance with AD 2001-16-14 
are approved as AMOCs with paragraph (f) of this AD.
    (3) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (l) French airworthiness directives 2002-637(B) R1, dated April 
16, 2003, and F-2005-057, dated April 13, 2005, also address the 
subject of this AD.

Material Incorporated by Reference

    (m) You must use Airbus Service Bulletin A320-52-1112, Revision 
05, dated June 25, 2004; and Airbus Industrie All Operators Telex 
A320-52A1111, Revision 01, dated July 23, 2001, including Airbus 
Industrie

[[Page 69065]]

Technical Disposition 959.1492/01, Issue C, dated July 17, 2001; as 
applicable; to perform the actions that are required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Service Bulletin A320-52-1112, 
Revision 05, dated June 25, 2004; in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) On August 31, 2001 (66 FR 42939, August 16, 2001), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Industrie All Operators Telex A320-52A1111, 
Revision 01, dated July 23, 2001, including Airbus Industrie 
Technical Disposition 959.1492/01, Issue C, dated July 17, 2001.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.


    Issued in Renton, Washington, on October 25, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22217 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P

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