Document ID: FAA-2008-0014-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes
Posted Date: 2008-01-14T05:00Z

[Federal Register: January 14, 2008 (Volume 73, Number 9)]
[Proposed Rules]               
[Page 2200-2204]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ja08-20]                         

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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]
RIN 2120-AA64

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

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

[[Page 2201]]

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A318, A319, A320, 
and A321 airplanes. The existing 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 proposed AD would 
continue 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 
proposed AD would also require modification of the rib bushings of the 
left and right MLG, which would end the repetitive inspections. This 
proposed AD results from cracks found in the forward lug of the MLG 
support rib 5 fitting. We are proposing 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: We must receive comments on this proposed AD by February 13, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov.
 Follow the instructions for submitting comments.

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0014; 
Directorate Identifier 2007-NM-249-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We 

will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 15, 2006, we issued AD 2006-11-04, amendment 39-14608 (71 FR 
29578, May 23, 2006), for certain Airbus Model A318, A319, A320, and 
A321 airplanes. AD 2006-11-04 requires repetitive detailed inspections 
for cracking in the forward lug of the support rib 5 fitting of both 
main landing gear (MLG), and repair if necessary. AD 2006-11-04 also 
provides optional terminating actions for certain airplanes, as well as 
other optional methods for complying with the inspection requirements 
of the existing AD. That AD resulted from a new crack that was found in 
the forward lug of the MLG support rib 5 fitting. We issued that AD to 
detect and correct 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-11-04, the European Aviation Safety Agency 
(EASA), which is the technical agent for the Member States of the 
European Union, notified us that the repetitive inspection intervals 
must be adjusted and that the optional terminating action, which would 
end the repetitive inspections, must be mandated for all airplanes. In 
the preamble to AD 2006-11-04, we indicated that the actions required 
by that AD were considered ``interim action,'' and that we were 
considering further rulemaking to require the modification of the lugs 
of the support rib 5 fitting of both MLG, which would terminate the 
repetitive inspections required by AD 2006-11-04. We have now 
determined that further rulemaking action is indeed necessary, and this 
proposed AD follows from that determination.

Relevant Service Information

    Airbus has issued Service Bulletin A320-57-1138, Revision 01, dated 
October 27, 2006. The service bulletin describes procedures for (1) 
doing repetitive visual inspections or repetitive ultrasonic 
inspections for cracking in the forward lug of the support rib 5 
fitting of the left and right MLG, (2) doing repetitive visual 
inspections for cracking in the forward lug of the support rib 5 
fitting if any cracking is found during an ultrasonic inspection, and 
(3) contacting the manufacturer for instructions if any cracking is 
found during a visual inspection. The service bulletin also specifies 
that accomplishing Airbus Service Bulletin A320-57-1118 eliminates the 
need for the repetitive inspections.
    Airbus has also issued Service Bulletin A320-57-1118, Revision 03, 
dated April 23, 2007. The service bulletin describes procedures for 
modifying the rib bushings of the left and right MLG. The modification 
includes removing the existing bushings, doing a visual inspection for 
corrosion and damage to the bores and spotfaces, repairing any 
corrosion or damage found during the detailed inspection, and 
installing new improved bushings and applying a certain protective 
sealant to the bores and spotfaces of the lugs for the pintle-pin 
bushings of gear rib 5. Accomplishing the modification eliminates the 
need for the repetitive inspections specified in Airbus Service 
Bulletin A320-57-1138.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2007-0213, 
dated August 7, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

[[Page 2202]]

FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2006-11-04 and would retain the 
requirements of the existing AD, until the new inspections have been 
initiated. This proposed AD would also require accomplishing the 
actions specified in service information described previously, except 
as discussed under ``Differences between Proposed AD and Service 
Bulletin.''

Differences Between Proposed AD and Service Bulletin

    Although EASA airworthiness directive 2007-0213 specifies repeating 
the inspections at the intervals defined in Airbus Service Bulletin 
A320-57-1138, the intent is to require the repetitive inspections at 
those intervals, or before further flight after a hard landing, 
whichever is first. We have coordinated this difference with the EASA.
    EASA airworthiness directive 2007-0213 and Airbus Service Bulletin 
A320-57-1138 permit further flight if cracking is found during the 
ultrasonic inspection but is not detected by a visual inspection. This 
proposed AD, however, would require repair or replacement of any 
cracked MLG fitting before further flight. We have determined that 
because of the safety implications and consequences associated with 
cracking in the subject area, the MLG fitting must be repaired or 
replaced before further flight regardless of how the crack is detected. 
We note that cracking found during the ultrasonic inspection may be 
repaired with oversized bushings, whereas cracking detected during the 
visual inspection would require extensive repair or replacement of the 
MLG fitting.
    Airbus Service Bulletin A320-57-1138 specifies to contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require repairing those conditions using a 
method approved by the FAA or the EASA (or its delegated agent). In 
light of the type of repair that would be required to address the 
unsafe condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this proposed AD, a repair 
approved by the FAA or the EASA would be acceptable for compliance with 
this proposed AD.

Costs of Compliance

    This proposed AD would affect about 466 airplanes of U.S. registry.
    The actions that are required by AD 2006-11-04 and retained in this 
proposed 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 proposed inspections would 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 proposed AD for 
U.S. operators is between $111,840 and $149,120, or between $240 and 
$320 per airplane, per inspection cycle.
    The new proposed modification would take about 73 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost $3,850 per airplane. Based on these figures, the estimated 
cost of the new modification specified in this proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14608 (71 FR 29578, May 23, 2006) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-
249-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
13, 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

[[Page 2203]]

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 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    If the most recent    Within 150 flight
 airplanes.                    inspection is a       cycles after a
                               detailed inspection   visual inspection.
                               done in accordance
                               with paragraph (f)
                               of this AD, inspect
                               within 150 flight
                               cycles after the
                               most recent
                               detailed inspection.
                              If the most recent    Within 940 flight
                               inspection is an      cycles after an
                               ultrasonic            ultrasonic
                               inspection done in    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    Within 100 flight
                               inspection is a       cycles after a
                               detailed inspection   visual inspection.
                               done in accordance
                               with paragraph (f)
                               of this AD, inspect
                               within 100 flight
                               cycles after the
                               most recent
                               detailed inspection.
                              If the most recent    Within 630 flight
                               inspection is an      cycles after an
                               ultrasonic            ultrasonic
                               inspection done in    inspection.
                               accordance with
                               paragraph (g) of
                               this AD, inspect
                               within 630 flight
                               cycles after the
                               most recent
                               ultrasonic
                               inspection.
------------------------------------------------------------------------

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, 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

[[Page 2204]]

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.

    Issued in Renton, Washington, on December 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-383 Filed 1-11-08; 8:45 am]

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