Document ID: FAA-2006-25658-0019
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes
Posted Date: 2008-03-12T04:00Z

[Federal Register: March 12, 2008 (Volume 73, Number 49)]
[Rules and Regulations]               
[Page 13084-13087]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12mr08-7]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25658; Directorate Identifier 2006-NM-054-AD; 
Amendment 39-15406; AD 2008-05-12]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing AD that applies to certain 
Airbus Model A318, A319, A320, and A321 airplanes. That AD currently 
requires 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 adds 
airplanes that were recently added to the type certificate data sheet 
and changes the inspection type. 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 April 16, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 16, 
2008.
    On March 24, 2006 (71 FR 8439, February 17, 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.
    On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of 
the Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a second supplemental notice of proposed rulemaking 
(NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 
2006-04-06, amendment 39-14487 (71 FR 8439, February 17, 2006). The 
existing AD applies to certain Airbus Model A318, A319, A320, and A321 
airplanes. That second supplemental NPRM was published in the Federal 
Register on August 16, 2007 (72 FR 45982). That second supplemental 
NPRM proposed to supersede an existing AD that currently requires 
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 second supplemental 
NPRM proposed to add airplanes that were recently added to the type 
certificate data sheet and change the inspection type.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Include Revised Service Information

    Airbus asks that Airbus Service Bulletin A320-57-1133, Revision 03, 
dated July 3, 2007, be incorporated into

[[Page 13085]]

the AD. (We referred to Revision 02, dated December 12, 2006, of that 
service bulletin as the appropriate source of service information for 
accomplishing certain actions specified in the second supplemental 
NPRM.)
    We agree with Airbus and have changed the applicable paragraphs in 
this AD to refer to Revision 03 of Airbus Service Bulletin A320-57-1133 
for accomplishing certain actions, as no additional work is required by 
this revision. We have also changed paragraph (k) of this AD to give 
credit to operators who have accomplished the actions in accordance 
with Airbus Service Bulletin A320-57-1133, Revision 02, dated December 
12, 2006, before the effective date of this AD.

Request To Include Inspections Removed From Second Supplemental NPRM

    Under the ``Request to Remove Certain Requirements'' section of the 
second supplemental NPRM, certain requirements were removed based on a 
previous recommendation from Airbus. Regarding that recommendation, 
Airbus notes that Model A321-211 and -231 airplanes that are pre-
modification 26495, and on which Airbus Service Bulletin A320-27-1117, 
Revision 04, dated November 6, 2001, was not applied, should have 
dedicated procedures included in the AD. Airbus states that the 
inspections specified in Airbus Service Bulletin A320-27-1108, Revision 
04, dated November 22, 1999, provide those procedures.
    We agree with Airbus, although there are no U.S. operators of Model 
A321-211 and -231 airplanes that are specified in the effectivity that 
are pre-modification 26495. In the unlikely event that an operator has 
an airplane configuration that is pre-modification 26495, or on which 
Airbus Service Bulletin A320-27-1117 was applied, we have determined 
that the alternative inspections specified in Airbus Service Bulletin 
A320-27-1108, Revision 04, can be used, as the inspections provide an 
acceptable level of safety. We have added a new paragraph (p) to this 
AD to include the alternate inspections.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
These changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Costs of Compliance

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                    Average                                                         Number  of
                                           Work      labor                                                            U.S.-
                Action                    hours     rate per            Parts               Cost per  airplane      registered         Fleet cost
                                                      hour                                                          airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification in AD 2006-04-06.........         14        $80  The manufacturer states    $1,120..................          768  $860,160.
                                                               that it will supply
                                                               required parts to
                                                               operators at no cost.
Detailed inspection in AD 2006-04-06..          2         80  None.....................  $160, per inspection              768  $122,880, per inspection
                                                                                          cycle.                                 cycle.
General visual inspection (new action)          1         80  None.....................  $80, per inspection               754  $60,320, per inspection
                                                                                          cycle.                                 cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    Currently, there are no affected Model A321-211 and -231 airplanes 
on the U.S. Register. However, if an affected airplane is imported and 
placed on the U.S. Register in the future, the required inspection 
would take about 1 work hour, at an average labor rate of $80 per work 
hour. Based on these figures, we estimate the cost of this AD to be $80 
per airplane, 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.

[[Page 13086]]

Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14487 (71 FR 8439, February 17, 2006) and adding 
the following new airworthiness directive (AD):

2008-05-12 Airbus: Amendment 39-15406. Docket No. FAA-2006-25658; 
Directorate Identifier 2006-NM-054-AD.

Effective Date

    (a) This AD becomes effective April 16, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-04-06.

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, -112, -121, and -122 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, 
-131, -211, -212, -213, -231, and -232 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 Requirements of AD 2006-04-06

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, amendment 39-12009), 
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; or Revision 04, dated November 
6, 2001. As of the effective date of this AD, only Revision 04 may 
be used.

    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.

Detailed Inspections

    (g) For Model A318-111 and -112 airplanes; 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: At the 
latest of the applicable 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; Revision 01, dated 
August 7, 2006; or Revision 03, dated July 3, 2007, except as 
provided by paragraph (n) of this AD. As of the effective date of 
this AD, only Revision 03 may be used. 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 
paragraphs (k), (l), and (m) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 4,000 flight hours until the 
inspection required by paragraph (h) of this AD is done.

    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 March 24, 2006 (the effective 
date of AD 2006-04-06).

New Requirements of This AD

General Visual Inspections

    (h) For all airplanes: At the time specified in paragraph (h)(1) 
or (h)(2) of this AD, as applicable, do a general visual inspection 
of the inboard flap trunnions for any wear marks and of the sliding 
panels for any cracking at the long edges, and do all applicable 
corrective actions by accomplishing all of the applicable actions 
specified in the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1133, Revision 03, dated July 3, 2007; except as 
provided by paragraphs (i) and (o) of this AD. All 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 
paragraphs (l), (m), and (n) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 4,000 flight hours. 
Accomplishing the general visual inspection required by this 
paragraph terminates the detailed inspection requirement of 
paragraph (g) of this AD.

    Note 3: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (1) For airplanes on which the detailed inspection required by 
paragraph (g) of this AD has been done before the effective date of 
this AD: Inspect before accumulating 4,000 total flight hours on the 
inboard flap trunnion since new, or within 4,000 flight hours after 
accomplishing the most recent inspection required by paragraph (g) 
of this AD, whichever occurs later.
    (2) For airplanes other than those identified in paragraph 
(h)(1) of this AD: Inspect at the latest of the applicable times 
specified in paragraphs (h)(2)(i), (h)(2)(ii), and (h)(2)(iii) of 
this AD.
    (i) Before accumulating 4,000 total flight hours on the inboard 
flap trunnion since new.
    (ii) Within 4,000 flight hours after accomplishing paragraph (f) 
of this AD.
    (iii) Within 600 flight hours after the effective date of this 
AD.
    (i) Where Airbus Service Bulletin A320-57-1133, Revision 03, 
dated July 3, 2007, specifies to contact the manufacturer for 
instructions on how to repair certain conditions: Before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA) (or its delegated agent), or 
the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or 
its delegated agent).

Actions Done Using Previous Issues of Service Information

    (j) Accomplishing the modification required by paragraph (f) of 
this AD before the effective date of this AD, in accordance with 
Airbus Service Bulletin A320-27-1117, Revision 03, dated August 24, 
2001, is acceptable for compliance with the requirements of that 
paragraph.
    (k) Accomplishing the inspections and corrective actions 
required by paragraphs (g) and (h) of this AD before the effective 
date of this AD, in accordance with Airbus Service Bulletin A320-57-
1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or 
Revision 02, dated December 12, 2006; is acceptable for compliance 
with the requirements of that paragraph.

Compliance Times

    (l) Where Airbus Service Bulletin A320-57-1133, Revision 03, 
dated July 3, 2007, specifies replacing the sliding panel at the 
next opportunity if damaged, replace it within 600 flight hours 
after the inspection required by paragraph (g) or (h) of this AD, as 
applicable.

[[Page 13087]]

    (m) If any damage to the trunnion is found during any inspection 
required by paragraph (g) or (h) of this AD, before further flight, 
do the corrective actions specified in Airbus Service Bulletin A320-
57-1133, Revision 03, dated July 3, 2007.

Grace Period Assessment

    (n) Where Airbus Service Bulletin A320-57-1133, Revision 03, 
dated July 3, 2007, specifies contacting the manufacturer for a 
grace period assessment after replacing the trunnion or flap, 
contact the Manager, International Branch, ANM-116; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent) 
for the grace period assessment.

No Reporting Requirement

    (o) Although Airbus Service Bulletin A320-57-1133, Revision 03, 
dated July 3, 2007, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Alternate Inspections

    (p) For Model A321-211 and -231 airplanes that have not been 
modified in accordance with Airbus Modification 26495, or on which 
the actions specified in Airbus Service Bulletin A320-27-1117, 
Revision 04, dated November 6, 2001, have not been done as of the 
effective date of this AD: Do the inspections specified in Airbus 
Service Bulletin A320-27-1108, Revision 04, dated November 22, 1999; 
at the applicable time specified in paragraph 1.E., ``Compliance'' 
of the service bulletin; except, where the service bulletin 
specifies a compliance time after the date of French airworthiness 
directive 96-271-092(B), this AD requires compliance within the 
specified compliance time after the effective date of this AD. Do 
all applicable corrective actions before further flight. Do the 
actions in accordance with the Accomplishment Instructions of the 
service bulletin.

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, International Branch, ANM-116, has the 
authority to approve 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 2006-04-06, 
amendment 39-14487, are approved as AMOCs for the corresponding 
provisions of this AD.
    (3) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

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

Material Incorporated by Reference

    (s) You must use the service information contained in Table 1 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

            Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
 Airbus Service Bulletin No.       Revision               Date
------------------------------------------------------------------------
A320-27-1117.................  02.............  January 18, 2000.
A320-27-1117.................  04.............  November 6, 2001.
A320-57-1133, excluding        Original.......  July 28, 2005.
 Appendix 01.
A320-57-1133.................  01.............  August 7, 2006.
A320-57-1133, excluding        03.............  July 3, 2007.
 Appendix 01.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.

            Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
  Airbus Service Bulletin No.      Revision              Date
------------------------------------------------------------------------
A320-27-1117...................           04  November 6, 2001.
A320-57-1133...................           01  August 7, 2006.
A320-57-1133, excluding                   03  July 3, 2007.
 Appendix 01.
------------------------------------------------------------------------

    (2) On March 24, 2006 (71 FR 8439, February 17, 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.
    (3) 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.
    (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; or at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 25, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-3989 Filed 3-11-08; 8:45 am]

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