[Federal Register Volume 71, Number 33 (Friday, February 17, 2006)]
[Rules and Regulations]
[Pages 8439-8441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-1405]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23143; Directorate Identifier 2005-NM-177-AD; 
Amendment 39-14487; AD 2006-04-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 Series Airplanes, 
Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-
200 Series Airplanes, and Model A321-100 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, A320, and A321 series 
airplanes. That AD currently requires repetitive inspections to detect 
wear of the inboard flap trunnions, and to detect wear or de-bonding of 
the protective half-shells; corrective actions, if necessary; and 
terminating action. This new AD removes the repetitive inspections to 
detect wear of the inboard flap trunnions and to detect wear or de-
bonding of the protective half-shells; and corrective actions if 
necessary. This new AD adds repetitive detailed inspections of the 
inboard flap trunnions for any wear marks and of the sliding panels for 
any cracking at the long edges, and corrective actions if necessary. 
This new AD also adds airplanes to the applicability. This AD results 
from reports of wear damage to the inboard flap trunnions after 
incorporation of the terminating modification. We are issuing this AD 
to detect and correct wear of the inboard flap trunnions, which could 
lead to loss of flap surface control and consequently result in the 
flap detaching from the airplane. A detached flap could result in 
damage to the tail of the airplane.

DATES: This AD becomes effective March 24, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A320-57-1133, excluding Appendix 
01, dated July 28, 2005, as of March 24, 2006.
    On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000.

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: 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:

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 notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2000-24-02, amendment 
39-12009 (65 FR 75603, December 4, 2000). The existing AD applies to 
certain Airbus Model A319, A320, and A321 series airplanes. That NPRM 
was published in the Federal Register on December 1, 2005 (70 FR 
72085). That NPRM proposed to remove the repetitive inspections to 
detect wear of the inboard flap trunnions and to detect wear or de-
bonding of the protective half-shells; and corrective actions if 
necessary. That NPRM also proposed to add repetitive detailed 
inspections of the inboard flap trunnions for any wear marks and of the 
sliding panels for any cracking at the long edges, and corrective 
actions if necessary. That NPRM also proposed to add airplanes to the 
applicability.

Comments

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

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined

[[Page 8440]]

that air safety and the public interest require adopting the AD as 
proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
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                                                                                                                          Number of U.S.-
                  Action                      Work hours     Average labor              Parts                Cost per       registered      Fleet cost
                                                             rate per hour                                   airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Terminating modification (required by AD                14             $65  Provided by manufacturer....            $910             719        $654,290
 2000-24-02).
Detailed inspection (new action)..........               2              65  None........................         \1\ 130             719      \1\ 93,470
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Per inspection cycle.

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.
    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 39-12009 (65 FR 75603, December 4, 2000) and by 
adding the following new airworthiness directive (AD):

2006-04-06 Airbus: Amendment 39-14487. Docket No. FAA-2005-23143; 
Directorate Identifier 2005-NM-177-AD.

Effective Date

    (a) This AD becomes effective March 24, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-24-02.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A318-111 and -112 airplanes on which Airbus 
Modification 26495 has been incorporated in production.
    (2) All Airbus Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -
212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, 
and -131 airplanes.

Unsafe Condition

    (d) This AD results from reports of wear damage to the inboard 
flap trunnions after incorporation of the terminating modification. 
We are issuing this AD to detect and correct wear of the inboard 
flap trunnions, which could lead to loss of flap surface control and 
consequently result in the flap detaching from the airplane. A 
detached flap could result in damage to the tail of the airplane.

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 Certain Requirements of AD 2000-24-02

Modification

    (f) For Model A319-111, -112, -113, -114, -115, -131, -132, and 
-133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -
131 airplanes; except those on which Airbus Modification 26495 has 
been accomplished in production: Within 18 months after January 8, 
2001 (the effective date of AD 2000-24-02), modify the sliding panel 
driving mechanism of the flap drive trunnions, in accordance with 
Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 
2000.

    Note 1: Accomplishment of the modification required by paragraph 
(f) of this AD before January 8, 2001, in accordance with Airbus 
Service Bulletin A320-27-1117, dated July 31, 1997; or Revision 01, 
dated June 25, 1999, is acceptable for compliance with that 
paragraph.

Requirements of This AD

Detailed Inspections

    (g) For all airplanes: At the latest of the applicable 
compliance times specified in paragraphs (g)(1), (g)(2), and (g)(3) 
of this AD, do a detailed inspection of the inboard flap trunnions 
for any wear marks and of the sliding panels for any cracking at the 
long edges, and do any corrective actions as applicable, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1133, 
dated July 28, 2005; except as provided by paragraph (h) of this AD. 
Any corrective actions must be done at the compliance times 
specified in Figures 5 and 6, as applicable, of the service 
bulletin; except as provided by paragraph (i) of this AD. Repeat the 
detailed inspections

[[Page 8441]]

thereafter at intervals not to exceed 4,000 flight hours.

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

    (1) Before accumulating 4,000 total flight hours on the inboard 
flap trunnion since new.
    (2) Within 4,000 flight hours after accomplishing paragraph (f) 
of this AD.
    (3) Within 600 flight hours after the effective date of this AD.

No Reporting Requirement

    (h) Although Airbus Service Bulletin A320-57-1133, dated July 
28, 2005, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Compliance Times

    (i) Where Airbus Service Bulletin A320-57-1133, dated July 28, 
2005, specifies replacing the sliding panel at the next opportunity, 
replace it within 600 flight hours after the inspection required by 
paragraph (g) of this AD. If the trunnion is found damaged during 
any inspection required by paragraph (g) of this AD, do the 
corrective actions specified in the service bulletin before further 
flight. Where the service bulletin specifies contacting the 
manufacturer for a grace period assessment after replacing the 
trunnion or flap, contact the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) for the grace 
period assessment.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) 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

    (k) French airworthiness directive F-2005-139, dated August 3, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus Service Bulletin A320-27-1117, Revision 
02, dated January 18, 2000; and Airbus Service Bulletin A320-57-
1133, excluding Appendix 01, dated July 28, 2005, 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 A320-57-1133, 
excluding Appendix 01, dated July 28, 2005, in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) On January 8, 2001 (65 FR 75603, December 4, 2000), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A320-27-1117, Revision 02, 
dated January 18, 2000.
    (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 February 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-1405 Filed 2-16-06; 8:45 am]
BILLING CODE 4910-13-P