
[Federal Register: April 14, 2008 (Volume 73, Number 72)]
[Rules and Regulations]               
[Page 19975-19977]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ap08-8]                         


[[Page 19975]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-249-AD; 
Amendment 39-15456; AD 2008-08-04]
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 airworthiness directive 
(AD), which applies to certain Airbus Model A318, A319, A320, and A321 
airplanes. That AD currently requires repetitive inspections for 
cracking in the forward lug of the support rib 5 fitting of both main 
landing gear (MLG), and repair if necessary. The existing AD also 
provides optional terminating actions for certain airplanes, as well as 
other optional methods for complying with the inspection requirements 
of the existing AD. This new AD continues to require repetitive 
inspections for cracking in the forward lug of the support rib 5 
fitting of the left and right MLG at new repetitive intervals in 
accordance with new service information, and repair or replacement of 
any cracked MLG fitting if necessary. This new AD also requires 
modification of the rib bushings of the left and right MLG, which would 
end the repetitive inspections. This AD results from cracks found in 
the forward lug of the MLG support rib 5 fitting. We are issuing this 
AD to prevent cracking in the forward lug of the MLG, which could 
result in failure of the lug and consequent collapse of the MLG during 
takeoff or landing.

DATES: This AD becomes effective May 19, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 19, 2008.

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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-11-04, amendment 
39-14608 (71 FR 29578, May 23, 2006). The existing AD applies to 
certain Airbus Model A318, A319, A320, and A321 airplanes. That NPRM 
was published in the Federal Register on January 14, 2008 (73 FR 2200). 
That NPRM proposed to continue to require repetitive inspections for 
cracking in the forward lug of the support rib 5 fitting of the left 
and right main landing gear (MLG) at new repetitive intervals in 
accordance with new service information, and repair or replacement of 
any cracked MLG fitting if necessary. That NPRM also proposed to 
require modification of the rib bushings of the left and right MLG, 
which would end the repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    This AD affects about 466 airplanes of U.S. registry.
    The actions that are required by AD 2006-11-04 and retained in this 
AD take about 2 work hours per airplane, at an average labor rate of 
$80 per work hour. Based on these figures, the estimated cost of the 
currently required actions is $160 per airplane, per inspection cycle.
    The new required inspections take between 3 and 4 work hours per 
airplane, depending on the type of inspection accomplished, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the new inspections specified in this AD for U.S. 
operators is between $111,840 and $149,120, or between $240 and $320 
per airplane, per inspection cycle.
    The new required modification takes about 73 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
cost $3,850 per airplane. Based on these figures, the estimated cost of 
the new modification specified in this AD for U.S. operators is 
$4,515,540, or $9,690 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.
    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.

[[Page 19976]]

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 39-14608 (71 FR 29578, May 23, 2006) and by adding 
the following new airworthiness directive (AD):

2008-08-04 Airbus: Amendment 39-15456. Docket No. FAA-2008-0014; 
Directorate Identifier 2007-NM-249-AD.

Effective Date

    (a) This AD becomes effective May 19, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-11-04.

Applicability

    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
airplanes, certificated in any category, except airplanes on which 
Airbus Modification 32025 has been accomplished in production.

Unsafe Condition

    (d) This AD results from cracks found in the forward lug of the 
main landing gear (MLG) support rib 5 fitting. We are issuing this 
AD to prevent cracking in the forward lug of the MLG, which could 
result in failure of the lug and consequent collapse of the MLG 
during takeoff or landing.

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 2006-11-04

Repetitive Detailed Inspections

    (f) Within 8 days after June 7, 2006 (the effective date of AD 
2006-11-04), or before further flight after a hard landing, 
whichever is first: Perform a detailed inspection for cracking in 
the forward lug of the support rib 5 fitting of the left- and right-
hand MLG, and, if any crack is found, replace the MLG fitting with a 
new fitting before further flight, in accordance with a method 
approved by either the Manager, International Branch, ANM-116, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent). Accomplishing the actions specified in the Airbus A318/A319/
A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, Revision 
dated February 1, 2003, is one approved method for performing the 
detailed inspection. Repeat the inspection thereafter at intervals 
not to exceed 8 days, or before further flight after a hard landing, 
whichever is first. As of the effective date of this AD, the 
repetitive inspections required by paragraph (i) of this AD must be 
accomplished in lieu of the repetitive inspections required by this 
paragraph.

    Note 1: 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.''

Optional Inspection Method

    (g) Performing an ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left- and right-hand 
MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent; 
is an acceptable alternative method of compliance for the initial 
and repetitive inspections required by paragraph (f) of this AD. 
Doing the actions specified in the Airbus A318/A319/A320/A321 
Nondestructive Testing Manual, Chapter 57-29-03, Revision dated 
February 1, 2005 (for Model A318, A319, and A320 airplanes), or 
Chapter 57-29-04, Revision dated May 1, 2005 (for Model A321 
airplanes), as applicable, is one approved method for performing the 
ultrasonic inspection.

Optional Terminating Action

    (h) For Model A319, A320, and A321 airplanes: Repair of the 
forward lugs of the support rib 5 fitting of the left- and right-
hand MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent); 
constitutes terminating action for the requirements of this AD. 
Doing the repair in accordance with Airbus A319 Structural Repair 
Manual (SRM), Chapter 5.C., 57-26-13, Revision dated November 1, 
2004; Airbus A320 SRM, Chapter 5.D., 57-26-13, Revision dated 
November 1, 2004; or Airbus A321 SRM, Chapter 5.D., 57-26-13, 
Revision dated February 1, 2005; as applicable; is one approved 
method.

New Requirements of This AD

New Repetitive Inspections

    (i) At the applicable time specified in Table 1 of this AD, or 
before further flight after a hard landing, whichever is first: Do a 
visual inspection or ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left and right MLG, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat 
the inspection thereafter at the applicable interval specified in 
Table 1 of this AD or before further flight after a hard landing, 
whichever is first, until the modification required by paragraph (k) 
of this AD has been accomplished. Accomplishing the initial 
inspection terminates the requirements of paragraph (f) of this AD.

                                           Table 1.--Compliance Times
----------------------------------------------------------------------------------------------------------------
               Airplanes                           Initial inspection                   Repetitive interval
----------------------------------------------------------------------------------------------------------------
Model A318, A319, and A320 airplanes..  If the most recent inspection is a        Within 150 flight cycles after
                                         detailed inspection done in accordance    a visual inspection.
                                         with paragraph (f) of this AD, inspect
                                         within 150 flight cycles after the most
                                         recent detailed inspection.
                                        If the most recent inspection is an       Within 940 flight cycles after
                                         ultrasonic inspection done in             an ultrasonic inspection.
                                         accordance with paragraph (g) of this
                                         AD, inspect within 940 flight cycles
                                         after the most recent ultrasonic
                                         inspection.
Model A321 airplanes..................  If the most recent inspection is a        Within 100 flight cycles after
                                         detailed inspection done in accordance    a visual inspection.
                                         with paragraph (f) of this AD, inspect
                                         within 100 flight cycles after the most
                                         recent detailed inspection.
                                        If the most recent inspection is an       Within 630 flight cycles after
                                         ultrasonic inspection done in             an ultrasonic inspection.
                                         accordance with paragraph (g) of this
                                         AD, inspect within 630 flight cycles
                                         after the most recent ultrasonic
                                         inspection.
----------------------------------------------------------------------------------------------------------------


[[Page 19977]]

Corrective Action

    (j) If any cracking is found during any inspection required by 
paragraph (i) of this AD: Before further flight, repair or replace 
the cracked MLG fitting using a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or the EASA (or its delegated agent).

Terminating Action

    (k) Within 60 months after the effective date of this AD, modify 
the rib bushings of the left and right MLG, by accomplishing all of 
the applicable actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A320-57-1118, Revision 03, dated April 
23, 2007. Accomplishing the modification terminates the requirements 
of this AD.

Credit for Actions Done According to Previous Issue of Service Bulletin

    (l) For Model A319, A320, and A321 airplanes, modifying the lugs 
of the support rib 5 fitting of the left and right MLG is acceptable 
for compliance with the requirements of paragraph (k) of this AD if 
done before the effective date of this AD in accordance with one of 
the following service bulletins: Airbus Service Bulletin A320-57-
1118, dated September 5, 2002; Revision 01, dated August 28, 2003; 
or Revision 02, dated August 2, 2006.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) 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.
    (3) AMOCs approved previously in accordance with AD 2006-11-04 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (n) EASA airworthiness directive 2007-0213, dated August 7, 
2007, also addresses the subject of this AD.

Material Incorporated by Reference

    (o) You must use Airbus Service Bulletin A320-57-1118, Revision 
03, dated April 23, 2007; and Airbus Service Bulletin A320-57-1138, 
Revision 01, dated October 27, 2006; as applicable; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. 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; 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 March 31, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-7182 Filed 4-11-08; 8:45 am]

BILLING CODE 4910-13-P
