Airworthiness Directives; Airbus Airplanes, 60325-60331 [2012-24393]
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alternative methods of compliance (AMOC)
in accordance with the procedures specified
in paragraph (j)(1) of this AD.
(i) Terminating Action for Certain ADs
Accomplishing the actions required by
paragraph (g) of this AD terminates the
requirements of AD 2012–02–18,
Amendment 39–16941 (77 FR 12175,
February 29, 2012); and AD 2010–26–05,
Amendment 39–16544 (75 FR 79952,
December 21, 2010); for the DASSAULT
AVIATION Model MYSTERE–FALCON 50
airplanes specified in those ADs.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1137; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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(k) Related Information
(1) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2011–
0246, dated December 22, 2011; and Section
05–40/00, Airworthiness Limitations, of
Chapter 5–40, Airworthiness Limitations, of
the Dassault Falcon 50/50EX Maintenance
Manual, Revision 21, dated June 21, 2011; for
related information.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
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Issued in Renton, Washington, on
September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–24392 Filed 10–2–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1253; Directorate
Identifier 2011–NM–079–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
that would supersede an existing AD for
certain Airbus Model A318, A319,
A320, and A321 series airplanes. For
certain airplanes, that NPRM proposed
repetitive inspections for cracks of the
forward lug of each main landing gear
(MLG) support rib 5 fitting and repair if
necessary; and removing Model 318
airplanes from the applicability. That
NPRM was prompted by reports of
cracks found in the forward lug of the
MLG support rib 5 fitting. This action
revises that NPRM by adding Model
A318 airplanes and others to the
applicability; and requiring repetitive
detailed inspections for cracks of the
MLG support 5 fitting, and repair of any
cracks. 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.
Since these actions impose an
additional burden over that proposed in
the NPRM, we are reopening the
comment period to allow the public the
chance to comment on these proposed
changes.
DATES: We must receive comments on
this proposed AD by November 19,
2012.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
ADDRESSES:
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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, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
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–2011–1253; Directorate Identifier
2011–NM–079–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 based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
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will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
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We proposed to amend 14 CFR part
39 with an earlier NPRM for the
specified products, which was
published in the Federal Register on
November 23, 2011 (76 FR 72350). That
earlier NPRM proposed to supersede AD
2008–08–04, Amendment 39–15456 (73
FR 19975, April 14, 2008), which
superseded AD 2006–11–04,
Amendment 39–14608 (71 FR 29578,
May 23, 2006), to require actions
intended to address the unsafe
condition for the products listed above.
Since that NPRM (76 FR 72350,
November 23, 2011) was issued, new
service information has been issued that
specifies additional actions that are
necessary to address the identified
unsafe condition. We have also
determined that repetitive detailed
inspections for cracks of the MLG
support rib 5 fitting, and repair of any
cracks found, must be required for
Model A318 airplanes and airplanes on
which Airbus modification 32025 has
been embodied in production. The
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0032,
dated February 24, 2012 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
Several cases of corrosion of the Main
Landing Gear (MLG) support Rib 5 fitting lug
bores have been reported on A320 family
aeroplanes. In some instances, corrosion pits
caused the cracking of the forward lug
(sometimes through its complete thickness).
If not detected, the cracking may lead to the
complete failure of the fitting and thus could
affect the structural integrity of the MLG
installation.
EASA AD 2007–0213 [which corresponds
to FAA AD 2008–08–04, Amendment 39–
15456 (73 FR 19975, April 14, 2008] was
issued to address this condition and required
a repetitive inspection program of the MLG
support Rib 5 fitting forward lugs and, as
terminating action, the embodiment of
Airbus Service Bulletin (SB) A320–57–1118.
After that [EASA] AD was issued, a case of
Rib 5, ruptured at the 4 o’clock position, was
discovered on an aeroplane on which the
terminating action of EASA AD 2007–0213
had already been embodied in accordance
with Airbus SB A320–57–1118.
Investigation of that case revealed that
corrosion damage and cracking that should
have been removed by repair machining was
below the level of detectability of the Non
Destructive Test (NDT) technique that
cleared the surfaces prior to bush
installation.
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This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To correct this potential unsafe condition,
EASA issued AD 2011–0011, [which
corresponds to FAA NPRM 2011–NM–179–
AD (76 FR 72350, November 23, 2011)]
superseding EASA AD 2007–0213, to:
—retain the requirements of EASA AD 2007–
0213 for aeroplanes on which the MLG Rib
Bushes have not been modified/repaired in
accordance with the instructions of Airbus
SB A320–57–1118, or Airbus SRM 57–26–
13, or the identified Airbus Repair
Instructions, as applicable, and
—require, for all aeroplanes on which Airbus
SB A320–57–1118 has been embodied in
service, or on which Airbus SRM 57–26–
13 or the identified Airbus Repair
Instructions have been applied, a repetitive
inspection program [for cracks] of the MLG
support Rib 5 fitting forward lugs and,
depending on findings, the
accomplishment of the associated
corrective actions, and
—reduce the Applicability by deleting A318
aeroplanes, as Airbus modification 32025
is embodied in production on both lefthand (LH) and right-hand (RH) wings for
all A318 aeroplanes.
After that AD was issued, three cases of
corrosion of Rib 5 were discovered on
aeroplanes on which Airbus modification
32025 had been embodied in production.
Investigations revealed that the unsafe
condition addressed by AD 2011–0011 could
occur or develop on those aeroplanes as well.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0011, which is superseded, extends
the applicability to all aeroplanes, and
requires for aeroplanes on which Airbus
modification 32025 has been embodied in
production, repetitive inspections of the
MLG support Rib 5 fitting forward lugs and,
depending on findings, the accomplishment
of applicable corrective actions.
The unsafe condition is 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. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A320–57A1166, Revision 01,
dated October 19, 2011; and Service
Bulletin A320–75–1168, dated
November 7, 2011. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
Comments
We have considered the following
comments received on the earlier NPRM
(76 FR 72350, November 23, 2011).
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Agreement With the Intent of the NPRM
(76 FR 72350, November 23, 2011)
United Airlines (United) stated that it
generally agrees with the intent of the
NPRM (76 FR 72350, November 23,
2011).
Agreement With Post-Modification
Inspections
US Airways stated it agrees with the
post-modification inspections in the
NPRM (76 FR 72350, November 23,
2011).
Support for the NPRM (76 FR 72350,
November 23, 2011)
Donjeta Dervisholli stated that the
NPRM (76 FR 72350, November 23,
2011) should ‘‘be passed’’ because it
will make flights safer and it will also
get things up to code. The commenter
also stated that adopting the AD will
help create jobs for the economy as well,
and will help stabilize the economy and
make money. The commenter
concluded that this regulation needs ‘‘to
pass’’ to make sure that cracking will
not happen again and there will be no
more damage.
Request To Delay Publication of Rule
Airbus requested that we postpone
issuing the final rule to ‘‘be in line with
the forthcoming EASA AD,’’ or that we
issue the final rule with caution notes.
Airbus stated it is currently in the
process with EASA of issuing a new AD
to extend the inspection program to all
Airbus Model A318, A319, A320, and
A321 airplanes, and that Airbus
modification 32025 will no longer be
considered a terminating action in the
forthcoming EASA AD.
We agree with postponing the final
rule and, instead, will release this
supplemental NPRM because it has been
recently determined that Airbus
modification 32025 does not mitigate
the unsafe condition. In addition, we
have recently determined that there is
no terminating action available for the
repetitive inspection requirement of this
supplemental NPRM.
Request To Delay Issuance of the Final
Rule
US Airways requested that we review
Airbus Service Bulletin A320–57–1168,
dated November 7, 2011, with EASA so
that a single AD can be written to cover
both post-modification 32025 airplanes
and the in-service fleet and to avoid
another supersedure AD. US Airways
stated that the production modification
of the fittings and the in-service
modification according to Airbus
Mandatory Service Bulletin A320–57–
1118, Revision 04, dated June 4, 2008,
has been shown to be ineffective at
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preventing corrosion. The commenter
stated that Airbus has released Airbus
Service Bulletin SB A320–57–1168,
dated November 7, 2011, which
recommends repetitive inspections at
500-flight-cycle intervals for new
delivery and replacement of fittings
after a 5-year threshold elapses.
As stated previously, we are releasing
this supplemental NPRM because it has
been recently determined that Airbus
modification 32025 does not mitigate
the unsafe condition. In addition, we
have recently determined that there is
no terminating action available for the
repetitive inspection requirement of this
supplemental NPRM.
Airbus Repair Drawing R572 481, Issue
A, dated November 11, 2011, is not an
acceptable method of compliance for
any action in this supplemental NPRM
and, therefore, would not be included in
the conditions specified in paragraphs
(j)(1) and (j)(2) of this supplemental
NPRM. We have not changed the
supplemental NPRM in this regard.
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Requests To Clarify Approved
Alternative Methods of Compliance
(AMOCs)
United and US Airways requested
clarification of the applicability of
AMOCs previously approved for AD
2006–11–04, Amendment 39–14608 (71
FR 29578, May 23, 2006); and AD 2008–
08–04, Amendment 39–15456 (73 FR
19975, April 14, 2008).
We agree to clarify the validity of
AMOC approvals granted for AD 2006–
11–04, Amendment 39–14608 (71 FR
29578, May 23, 2006); and AD 2008–08–
04, Amendment 39–15456 (73 FR
19975, April 14, 2008). We have revised
the statement in paragraph (u)(1) of this
supplemental NPRM to state that
AMOCs approved previously in
accordance with AD 2006–11–04 and
AD 2008–08–04 are approved as
AMOCs for the corresponding
provisions of this supplemental NPRM.
Request To Include New Service
Information
United requested that we revise the
NPRM (76 FR 72350, November 23,
2011) to refer to Airbus Mandatory
Service Bulletin A320–57A1166,
Revision 01, dated October 19, 2011, for
the actions specified in paragraph (o) of
the NPRM.
We agree. As discussed previously,
Airbus Mandatory Service Bulletin
A320–57A1166, Revision 01, dated
October 19, 2011, was issued while the
comment period was open for the
NPRM (76 FR 72350, November 23,
2011). That service bulletin includes
minor edits and does not add an
additional economic burden. We have
revised paragraph (n) of this
supplemental NPRM (paragraph (o) of
the NPRM) to reference Airbus
Mandatory Service Bulletin A320–
57A1166, Revision 01, dated October
19, 2011; and added paragraph (t) to this
supplemental NPRM to give credit for
corresponding actions done before the
effective date of the AD using Airbus
Service Bulletin A320–57A1166, dated
January 12, 2011. We have also updated
the subsequent paragraph identifiers
accordingly.
Request To Reference a Repair Drawing
United requested that we revise the
NPRM (76 FR 72350, November 23,
2011) to include recently released
Airbus Repair Drawing R572 481, Issue
A, dated November 11, 2011, in
paragraphs (j)(1) and (j)(2) of the NPRM.
United also requested that if Airbus
Mandatory Service Bulletin A320–57–
1118, Revision 04, dated June 4, 2008,
is revised before the release of the final
rule, then that service bulletin should
also include Airbus Repair Drawing
R572 481, Issue A, dated November 11,
2011, and the new service information
should be referenced in the final rule.
We disagree. Paragraph (j)(1) of the
NPRM (76 FR 72350, November 23,
2011) references ‘‘Airbus Service
Bulletin A320–57–1118,’’ which
includes all revisions of that service
bulletin. Once an operator accomplishes
any revision of Airbus Service Bulletin
A320–57–1118, the affected airplane is
subject to the actions specified in
paragraphs (k), (m), and (n) of this
supplemental NPRM. In addition,
Request To Reference Specifications
Without Revision Dates
US Airways requested that we revise
the NPRM (76 FR 72350, November 23,
2011) to specify the structural repair
manual chapter and paragraph, or by
drawing number, without revision
dates. US Airways stated that
specification of corrective actions by
document dates, as specified in
paragraph (i) of the NPRM,
unnecessarily restricts the use of latest
and best repair practices. The referenced
repair documents are now roughly
between seven and eleven years old. US
Airways pointed out that Airbus has
made efforts to improve these repairs in
that time frame, and by restricting
operators to the use of historic
documents, the FAA is making it
difficult to incorporate improved repair
methods.
We partially agree. We agree with US
Airways that the most current approved
service information should be
referenced in the AD. We must reference
the revision dates in an AD when
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referring to the service document,
because not doing so violates the Office
of the Federal Register (OFR) policies
for approval of materials ‘‘incorporated
by reference’’ in rules. In general terms,
we are required by these OFR policies
to either publish the service document
contents as part of the actual AD
language; or submit the service
document to the OFR for approval as
‘‘referenced’’ material, in which case we
may only refer to such material in the
text of an AD. The AD may refer to the
service document only if the OFR
approved it for ‘‘incorporation by
reference.’’ To allow operators to use
later revisions of the referenced
document (issued after publication of
the AD), either we must revise the AD
to reference specific later revisions, or
operators may request approval to use
later revisions as an AMOC with the AD
under the provisions of paragraph (u) of
this supplemental NPRM. As stated
previously, we have revised the
supplemental NPRM to accept
previously approved AMOCs for the
corresponding provisions of this
supplemental NPRM. We have not
changed the AD regarding incorporating
service information without revision
dates.
Request To Reformat Table 1 of the
NPRM (76 FR 72350, November 23,
2011)
US Airways requested that we correct
the formatting of table 1 to paragraph (k)
of the NPRM (76 FR 72350, November
23, 2011). The commenter stated that
the details in the first two rows of that
table are data for Airbus Model A319
and A320 airplanes, while the third and
fourth rows provide information for
Model A321 airplanes.
We find that clarification is necessary.
The commenter correctly specified the
information in table 1 to paragraph (k)
of the NPRM (76 FR 72350, November
23, 2011), but identified no errors that
require correction. The information in
table 1 to paragraph (k) of this
supplemental NPRM is correct.
However, we have added a reference to
Model A318 airplanes to the first row of
the table.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
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information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Certain changes described above
expand the scope of the earlier NPRM
(76 FR 72350, November 23, 2011). As
a result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this proposed
AD.
Additional Changes to the
Supplemental NPRM
We have removed certain service
information as a method of compliance
from paragraphs (g), (h), (i), and (j) of
the NPRM (76 FR 72350, November 23,
2011), in this supplemental NPRM. We
have also added certain credit for
actions done before the effective date of
this AD in paragraph (t) of this
supplemental NPRM, using that
removed service information.
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Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 740 products of U.S.
registry.
The actions that are required by AD
2008–08–04, Amendment 39–15456 (73
FR 19975, April 14, 2008), and retained
in this proposed AD take about 73 workhours per product, at an average labor
rate of $85 per work hour. Required
parts would cost about $3,860 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, the estimated cost of the
currently required actions is $10,065 per
product.
We estimate that it would take about
3 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the new
actions in this proposed AD on U.S.
operators to be up to $188,700, or $255
per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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:
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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 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 this 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);
3. Will not affect intrastate aviation in
Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
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2008–08–04, Amendment 39–15456 (73
FR 19975, April 14, 2008), and adding
the following new AD:
Airbus: Docket No. FAA–2011–1253;
Directorate Identifier 2011–NM–079–AD.
(a) Comments Due Date
We must receive comments by November
19, 2012.
(b) Affected ADs
This AD supersedes AD 2008–08–04,
Amendment 39–15456 (73 FR 19975, April
14, 2008), which superseded AD 2006–11–
04, Amendment 39–14608 (71 FR 29578, May
23, 2006).
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122; A319–111, A319–
112, A319–113, A319–114, A319–115, A319–
131, A319–132, and A319–133; A320–111,
A320–211, A320–212, A320–214, A320–231,
A320–232, and A320–233; and A321–111,
A321–112, A321–131, A321–211, A321–212,
A321–213, A321–231, and A321–232
airplanes; certificated in any category; all
manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of 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.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Repetitive Detailed Inspections
With Changes
This paragraph restates the requirements of
paragraph (f) of AD 2008–08–04, Amendment
39–15456 (73 FR 19975, April 14, 2008), with
changes. Except for airplanes on which
Airbus modification 32025 has been
accomplished in production, within 8 days
after June 7, 2006 (the effective date of AD
2006–11–04, Amendment 39–14608 (71 FR
29578, May 23, 2006)), 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 the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent). Repeat the inspection
thereafter at intervals not to exceed 8 days,
or before further flight after a hard landing,
whichever is first. As of May 19, 2008 (the
effective date of AD 2008–08–04), the
repetitive inspections required by paragraph
(k) of this AD must be accomplished in lieu
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of the repetitive inspections required by this
paragraph.
(h) Retained Optional Inspection Method
With Changes
This paragraph restates the requirements of
paragraph (g) of AD 2008–08–04,
Amendment 39–15456 (73 FR 19975, April
14, 2008), with revised service information.
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 an applicable method
specified in paragraph (h)(1) or (h)(2) of this
AD is an acceptable alternative method of
compliance for the initial and repetitive
inspections required by paragraph (g) of this
AD.
(1) In accordance with a method approved
by the Manager, International Branch, ANM–
116, or the EASA (or its delegated agent).
(2) In accordance with Task 57–29–03–
270–801–A–01, Gear Rib Forward Lug
Attachment for the Main Landing Gear Before
Modification 32025J2211, of Chapter 57,
Wings, of the Airbus A318/A319/A320/A321
Nondestructive Testing Manual, Revision 89,
dated August 1, 2011.
(i) Retained Optional Terminating Action
With Changes
This paragraph restates the requirements of
paragraph (h) of AD 2008–08–04,
Amendment 39–15456 (73 FR 19975, April
14, 2008). Repair of the forward lugs of the
support rib 5 fitting of the left- and righthand MLG done before the effective date of
this AD, 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 paragraphs (g),
(h), (k), (l), and (m) of this AD.
(j) Retained Referenced Conditions With
Revised Affected Airplanes
To identify affected airplanes in
paragraphs (k), (m), and (o) of this AD, this
AD refers to the following conditions:
(1) Airplanes on which the modification of
the MLG rib bushes specified in Airbus
Service Bulletin A320–57–1118 has been
done.
(2) Airplanes on which a repair of the MLG
support rib 5 fitting has been done in
accordance with paragraph 5.C. of Subsection
57–26–13, Attachments—Main Landing Gear,
of the Airbus A319 Structural Repair Manual
(SRM), Revision November 1, 2004;
paragraph 5.D. of Subsection 57–26–13,
Attachments—Main Landing Gear, of the
Airbus A320 SRM, Revision November 1,
2004; or paragraph 5.D. of Subsection 57–26–
13, Attachments—Main Landing Gear, of the
Airbus A321 SRM, Revision February 1,
2005; as applicable.
(3) Airplanes on which replacement in
service of the MLG support rib 5 specified in
Airbus Repair Instruction R572–58507 and
Airbus Repair Drawing R57258209, or Airbus
60329
Repair Instruction R572–45020 and Airbus
Repair Drawing R57245019, as applicable,
has been done.
(k) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (i) of AD 2008–08–04, Amendment
39–15456 (73 FR 19975, April 14, 2008). For
airplanes on which none of the actions
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD have been done, except for
airplanes on which Airbus modification
32025 has been accomplished: At the
applicable time specified in table 1 to
paragraph (k) 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 to paragraph (k)
of this AD or before further flight after a hard
landing, whichever is first, until the
modification required by paragraph (m) of
this AD has been accomplished.
Accomplishing the initial inspection
terminates the requirements of paragraph (g)
of this AD.
TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES
Airplanes
(1) Model A318, A319,
and A320 airplanes.
(2) Model A321 airplanes.
Initial inspection
Repetitive interval
(i) If the most recent inspection is a detailed inspection done in accordance with paragraph (g) of this AD, inspect within 150 flight
cycles after the most recent detailed inspection.
(ii) If the most recent inspection is an ultrasonic inspection done in
accordance with paragraph (h) of this AD, inspect within 940 flight
cycles after the most recent ultrasonic inspection.
(i) If the most recent inspection is a detailed inspection done in accordance with paragraph (g) of this AD, inspect within 100 flight
cycles after the most recent detailed inspection.
(ii) If the most recent inspection is an ultrasonic inspection done in
accordance with paragraph (h) of this AD, inspect within 630 flight
cycles after the most recent ultrasonic inspection.
Within 150 flight cycles after a visual inspection.
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(l) Retained Corrective Action
This paragraph restates the requirements of
paragraph (j) of AD 2008–08–04, Amendment
39–15456 (73 FR 19975, April 14, 2008). If
any cracking is found during any inspection
required by paragraph (k) of this AD: Before
further flight, repair or replace the cracked
MLG fitting, in accordance with a method
approved by the Manager, International
Branch, ANM–116, or the EASA (or its
delegated agent).
(m) Retained Rib Bushing Modification
This paragraph restates the requirements of
paragraph (k) of AD 2008–08–04,
Amendment 39–15456 (73 FR 19975, April
14, 2008), with revised service information.
Except for airplanes on which the actions
specified in paragraph (j)(1) or (j)(3) of this
AD have been done, and except for airplanes
on which Airbus modification 32025 has
been accomplished: Within 60 months after
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14:54 Oct 02, 2012
Jkt 229001
May 19, 2008 (the effective date of AD 2008–
08–04), 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; or Airbus Mandatory
Service Bulletin A320–57–1118, Revision 04,
dated June 4, 2008. Accomplishing this
modification terminates the requirements of
paragraphs (g) and (k) of this AD, and then
the requirements of paragraph (n) of this AD
must be done.
(n) New Post-Modification/Post-Repair
Inspections
For airplanes on which the actions
specified in paragraph (j)(1), (j)(2), or (m) of
this AD have been done: At the later of the
times specified in paragraphs (n)(1) and
(n)(2) of this AD, do a detailed inspection for
cracks of the forward lug of each left-hand
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Sfmt 4702
Within 940 flight cycles after an ultrasonic inspection.
Within 100 flight cycles after a visual inspection.
Within 630 flight cycles after an ultrasonic inspection.
and right-hand MLG support rib 5 fitting, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–57A1166, Revision 01, dated
October 19, 2011. Repeat the inspection
thereafter at intervals not to exceed 500 flight
cycles.
(1) Within 2,000 flight cycles after
accomplishing the modification specified in
paragraph (j)(1) or (m) of this AD, or the
repair specified in paragraph (j)(2) of this AD,
as applicable.
(2) Within 250 flight cycles after the
effective date of this AD, without exceeding
3 months after the effective date of this AD.
(o) New Repair of Cracking Found During
Post-Modification/Post-Repair
If any crack is detected during any
inspection required by paragraph (n) of this
AD: Before further flight, repair using a
method approved by either the Manager,
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Federal Register / Vol. 77, No. 192 / Wednesday, October 3, 2012 / Proposed Rules
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the EASA (or
its delegated agent).
(p) New Optional Terminating Action
Replacement of a MLG support rib 5 fitting
at any position (left-hand or right-hand), as
specified in paragraph (j)(3) of this AD,
terminates the requirements of paragraphs (k)
and (n) of this AD for the MLG support rib
5 fitting at that position.
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(q) New Repetitive Detailed Inspection for
Certain Airplanes
For airplanes on which the actions
specified in paragraph (j)(3) of this AD have
been done: Within 60 months after the
replacement or within 500 flight cycles after
the effective date of this AD, whichever
occurs later, do a detailed inspection of the
forward lug of each left-hand and right-hand
MLG support Rib 5 fitting that has been
replaced, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–57A1166,
Revision 01, dated October 19, 2011. Repeat
the inspection thereafter at intervals not to
exceed 500 flight cycles.
(r) New Repetitive Inspections for Airplanes
with Airbus Modification 32025
For airplanes on which Airbus
modification 32025 has been accomplished:
At the applicable time specified in paragraph
(r)(1,) (r)(2), (r)(3), or (r)(4) of this AD, do a
detailed inspection for cracks of the forward
lug of each left-hand and right-hand MLG
support rib 5 fitting, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1168, dated
November 7, 2011. Repeat the inspection
thereafter at intervals not to exceed 500 flight
cycles.
(1) For airplanes on which the MLG
support rib 5 has not been modified nor
repaired since the first flight of the airplane
as of the effective date of this AD: Within 60
months after the first flight of the airplane or
within 500 flight cycles after the effective
date of this AD, whichever occurs later.
(2) For airplanes on which the MLG
support rib 5 has been replaced as specified
in paragraph (j)(3) of this AD as of the
effective date of this AD: Within 60 months
after the replacement of the MLG support rib
5 or within 500 flight cycles after the
effective date of this AD, whichever occurs
later.
(3) For airplanes on which the MLG
support rib 5 has been repaired according to
the SRM or a repair approval sheet as of the
effective date of this AD: At the later of the
times specified in paragraph (r)(3)(i) or
(r)(3)(ii) of this AD.
(i) Within 2,000 flight cycles after the
repair.
(ii) Within 250 flight cycles or 3 months
after the effective date of this AD, whichever
occurs first.
(4) For airplanes having a manufacturer
serial number listed in table 2 to paragraph
(r)(4) of this AD, and on which the MLG
support rib 5 has been inspected before the
effective date of this AD according to specific
Airbus repair instructions or technical
disposition: At the later of the times specified
in paragraph (r)(4)(i) or (r)(4)(ii) of this AD.
VerDate Mar<15>2010
14:54 Oct 02, 2012
Jkt 229001
TABLE 2 TO PARAGRAPH (r)(4) OF THIS
AD—MANUFACTURER SERIAL NUMBER (S/N)
S/N—
1965
2274
2321
2588
2688
2942
3361
3489
3937
2056
2278
2478
2612
2707
3089
3427
3806
4243
2155
2288
2586
2672
2929
3117
3486
3891
4345
(i) Within 2,000 flight cycles after the last
inspection done using specific Airbus repair
instructions or a technical disposition, or
within 60 months since first flight of the
airplane, whichever occurs later.
(ii) Within 250 flight cycles or 3 months
after the effective date of this AD, whichever
occurs first.
(s) New Repair of Cracking
If any crack is detected during any
inspection required by paragraph (q) or (r) of
this AD: Before further flight, repair using a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the EASA (or
its delegated agent).
(t) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Airbus A318/
A319/A320/A321 Nondestructive Testing
Manual, Chapter 51–90–00, Revision dated
February 1, 2003.
(2) This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using 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).
(3) This paragraph provides credit for the
actions specified in paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using paragraph 5.C.
of Subsection 57–26–13, Attachments—Main
Landing Gear, of the Airbus A319 Structural
Repair Manual (SRM), Revision November 1,
2004; paragraph 5.D. of Subsection 57–26–13,
Attachments—Main Landing Gear, of the
Airbus A320 SRM, Revision November 1,
2004; or paragraph 5.D. of Subsection 57–26–
13, Attachments—Main Landing Gear, of the
Airbus A321 SRM, Revision February 1,
2005; as applicable.
(4) This paragraph provides credit for the
inspections required by paragraphs (n) and
(r) of this AD, if the inspections were
performed before the effective date of this AD
using Airbus Service Bulletin A320–
57A1166, dated January 12, 2011.
(5) This paragraph provides credit for the
modification required by paragraph (m) of
this AD, if the modification was performed
before May 19, 2008 (the effective date of AD
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Frm 00008
Fmt 4702
Sfmt 4702
2008–08–04, Amendment 39–15456 (73 FR
19975, April 14, 2008), using service
information identified in paragraph (t)(5)(i),
(t)(5)(ii), or (t)(5)(iii) of this AD.
(i) Airbus Service Bulletin A320–57–1118,
dated September 5, 2002.
(ii) Airbus Service Bulletin A320–57–1118,
Revision 01, dated August 28, 2003.
(iii) Airbus Service Bulletin A320–57–
1118, Revision 02, dated August 2, 2006.
(u) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD. AMOCs
approved previously in accordance with AD
2006–11–04, Amendment 39–14608 (71 FR
29578, May 23, 2006); and AD 2008–08–04,
Amendment 39–15456 (73 FR 19975, April
14, 2008); are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to ensure the product is airworthy before it
is returned to service.
(v) Related Information
Refer to MCAI EASA Airworthiness
Directive 2012–0032, dated February 24,
2012, and the following service information,
for related information.
(1) Airbus Mandatory Service Bulletin
A320–57–1118, Revision 04, dated June 4,
2008.
(2) Airbus Mandatory Service Bulletin
A320–57A1166, Revision 01, dated October
19, 2011.
(3) Airbus Service Bulletin A320–57–1168,
dated November 7, 2011.
(4) Airbus Service Bulletin A320–57–1118,
Revision 03, dated April 23, 2007.
(5) Airbus Service Bulletin A320–57–1138,
Revision 01, dated October 27, 2006.
(6) Task 57–29–03–270–801–A–01, Gear
Rib Forward Lug Attachment for the Main
Landing Gear Before Modification
32025J2211, of Chapter 57, Wings, of the
Airbus A318/A319/A320/A321
Nondestructive Testing Manual, Revision 89,
dated August 1, 2011.
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Federal Register / Vol. 77, No. 192 / Wednesday, October 3, 2012 / Proposed Rules
Issued in Renton, Washington, on
September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
[FR Doc. 2012–24393 Filed 10–2–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1035; Directorate
Identifier 2011–NM–235–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by a report of an
uncommanded nose landing gear (NLG)
retraction. This proposed AD would
require installing a power interruption
protection circuit for the landing gear
control interface unit (LGCIU). We are
proposing this AD to prevent untimely
unlocking and/or retraction of the NLG,
which, while on the ground, could
result in injury to ground personnel and
damage to the airplane.
DATES: We must receive comments on
this proposed AD by November 19,
2012.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
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ADDRESSES:
VerDate Mar<15>2010
14:54 Oct 02, 2012
Jkt 229001
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
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–2012–1035; Directorate Identifier
2011–NM–235–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 based on those comments.
We will post all comments we
receive, without change, to https://
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0202,
dated October 13, 2011 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
After a push back from the gate, an A320
aeroplane was preparing to initiate taxi,
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Frm 00009
Fmt 4702
Sfmt 4702
60331
when an uncommanded nose landing gear
(NLG) retraction occurred, causing the nose
of the aeroplane to hit the ground.
Investigations revealed that the retraction
was caused by a combination of a power
interruption to LGCIUs [landing gear control
interface unit] and an internal hydraulic leak
through the landing gear (LG) selector valve
40GA.
Deeper investigations have revealed that
LGCIU power interruption appears during
engine start at each flight. Even though no
incident has been reported in service, it has
been determined that a non compliance to
the safety objective exists when combined
with a dormant single failure of the selector
valve seal leaking.
This condition, if not corrected, could lead
to further incidents of untimely unlocking
and/or retraction of the NLG which, while on
the ground, could result in injury to ground
personnel and damage to the aeroplane.
To address the possible hydraulic leak of
the LG selector valve, EASA issued AD 2007–
0065, currently at Revision 2.
For the reasons described above, this
[EASA] AD requires installation of a power
interruption protection circuit to the LGCIU
and the accomplishment of associated
modifications [install new seals on nose
landing gear (NLG)/main landing gear (MLG)
door valve selector and gear valve-selector
and for certain airplanes, re-identification of
identification plates].
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
service bulletins:
• Airbus Service Bulletin A320–32–
1346, Revision 04, including
Appendices 1 and 2, dated April 22,
2011 (for Model A318, A319, A320, and
A321 series airplanes).
• Airbus Service Bulletin A320–32–
1349, Revision 03, including Appendix
1, dated October 5, 2011 (for Model
A319CJ (corporate jet) airplanes).
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
E:\FR\FM\03OCP1.SGM
03OCP1
]]>Agencies
[Federal Register Volume 77, Number 192 (Wednesday, October 3, 2012)]
[Proposed Rules]
[Pages 60325-60331]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24393]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1253; Directorate Identifier 2011-NM-079-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) that would supersede an existing AD for certain Airbus Model A318,
A319, A320, and A321 series airplanes. For certain airplanes, that NPRM
proposed repetitive inspections for cracks of the forward lug of each
main landing gear (MLG) support rib 5 fitting and repair if necessary;
and removing Model 318 airplanes from the applicability. That NPRM was
prompted by reports of cracks found in the forward lug of the MLG
support rib 5 fitting. This action revises that NPRM by adding Model
A318 airplanes and others to the applicability; and requiring
repetitive detailed inspections for cracks of the MLG support 5
fitting, and repair of any cracks. 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. Since these actions impose an additional burden over that
proposed in the NPRM, we are reopening the comment period to allow the
public the chance to comment on these proposed changes.
DATES: We must receive comments on this proposed AD by November 19,
2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email: account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
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 Operations 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
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-2011-1253;
Directorate Identifier 2011-NM-079-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 based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
[[Page 60326]]
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We proposed to amend 14 CFR part 39 with an earlier NPRM for the
specified products, which was published in the Federal Register on
November 23, 2011 (76 FR 72350). That earlier NPRM proposed to
supersede AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14,
2008), which superseded AD 2006-11-04, Amendment 39-14608 (71 FR 29578,
May 23, 2006), to require actions intended to address the unsafe
condition for the products listed above.
Since that NPRM (76 FR 72350, November 23, 2011) was issued, new
service information has been issued that specifies additional actions
that are necessary to address the identified unsafe condition. We have
also determined that repetitive detailed inspections for cracks of the
MLG support rib 5 fitting, and repair of any cracks found, must be
required for Model A318 airplanes and airplanes on which Airbus
modification 32025 has been embodied in production. The European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, has issued EASA Airworthiness
Directive 2012-0032, dated February 24, 2012 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Several cases of corrosion of the Main Landing Gear (MLG)
support Rib 5 fitting lug bores have been reported on A320 family
aeroplanes. In some instances, corrosion pits caused the cracking of
the forward lug (sometimes through its complete thickness). If not
detected, the cracking may lead to the complete failure of the
fitting and thus could affect the structural integrity of the MLG
installation.
EASA AD 2007-0213 [which corresponds to FAA AD 2008-08-04,
Amendment 39-15456 (73 FR 19975, April 14, 2008] was issued to
address this condition and required a repetitive inspection program
of the MLG support Rib 5 fitting forward lugs and, as terminating
action, the embodiment of Airbus Service Bulletin (SB) A320-57-1118.
After that [EASA] AD was issued, a case of Rib 5, ruptured at
the 4 o'clock position, was discovered on an aeroplane on which the
terminating action of EASA AD 2007-0213 had already been embodied in
accordance with Airbus SB A320-57-1118.
Investigation of that case revealed that corrosion damage and
cracking that should have been removed by repair machining was below
the level of detectability of the Non Destructive Test (NDT)
technique that cleared the surfaces prior to bush installation.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To correct this potential unsafe condition, EASA issued AD 2011-
0011, [which corresponds to FAA NPRM 2011-NM-179-AD (76 FR 72350,
November 23, 2011)] superseding EASA AD 2007-0213, to:
--retain the requirements of EASA AD 2007-0213 for aeroplanes on
which the MLG Rib Bushes have not been modified/repaired in
accordance with the instructions of Airbus SB A320-57-1118, or
Airbus SRM 57-26-13, or the identified Airbus Repair Instructions,
as applicable, and
--require, for all aeroplanes on which Airbus SB A320-57-1118 has
been embodied in service, or on which Airbus SRM 57-26-13 or the
identified Airbus Repair Instructions have been applied, a
repetitive inspection program [for cracks] of the MLG support Rib 5
fitting forward lugs and, depending on findings, the accomplishment
of the associated corrective actions, and
--reduce the Applicability by deleting A318 aeroplanes, as Airbus
modification 32025 is embodied in production on both left-hand (LH)
and right-hand (RH) wings for all A318 aeroplanes.
After that AD was issued, three cases of corrosion of Rib 5 were
discovered on aeroplanes on which Airbus modification 32025 had been
embodied in production. Investigations revealed that the unsafe
condition addressed by AD 2011-0011 could occur or develop on those
aeroplanes as well.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0011, which is superseded, extends the
applicability to all aeroplanes, and requires for aeroplanes on
which Airbus modification 32025 has been embodied in production,
repetitive inspections of the MLG support Rib 5 fitting forward lugs
and, depending on findings, the accomplishment of applicable
corrective actions.
The unsafe condition is 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. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-57A1166, Revision
01, dated October 19, 2011; and Service Bulletin A320-75-1168, dated
November 7, 2011. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
Comments
We have considered the following comments received on the earlier
NPRM (76 FR 72350, November 23, 2011).
Agreement With the Intent of the NPRM (76 FR 72350, November 23, 2011)
United Airlines (United) stated that it generally agrees with the
intent of the NPRM (76 FR 72350, November 23, 2011).
Agreement With Post-Modification Inspections
US Airways stated it agrees with the post-modification inspections
in the NPRM (76 FR 72350, November 23, 2011).
Support for the NPRM (76 FR 72350, November 23, 2011)
Donjeta Dervisholli stated that the NPRM (76 FR 72350, November 23,
2011) should ``be passed'' because it will make flights safer and it
will also get things up to code. The commenter also stated that
adopting the AD will help create jobs for the economy as well, and will
help stabilize the economy and make money. The commenter concluded that
this regulation needs ``to pass'' to make sure that cracking will not
happen again and there will be no more damage.
Request To Delay Publication of Rule
Airbus requested that we postpone issuing the final rule to ``be in
line with the forthcoming EASA AD,'' or that we issue the final rule
with caution notes. Airbus stated it is currently in the process with
EASA of issuing a new AD to extend the inspection program to all Airbus
Model A318, A319, A320, and A321 airplanes, and that Airbus
modification 32025 will no longer be considered a terminating action in
the forthcoming EASA AD.
We agree with postponing the final rule and, instead, will release
this supplemental NPRM because it has been recently determined that
Airbus modification 32025 does not mitigate the unsafe condition. In
addition, we have recently determined that there is no terminating
action available for the repetitive inspection requirement of this
supplemental NPRM.
Request To Delay Issuance of the Final Rule
US Airways requested that we review Airbus Service Bulletin A320-
57-1168, dated November 7, 2011, with EASA so that a single AD can be
written to cover both post-modification 32025 airplanes and the in-
service fleet and to avoid another supersedure AD. US Airways stated
that the production modification of the fittings and the in-service
modification according to Airbus Mandatory Service Bulletin A320-57-
1118, Revision 04, dated June 4, 2008, has been shown to be ineffective
at
[[Page 60327]]
preventing corrosion. The commenter stated that Airbus has released
Airbus Service Bulletin SB A320-57-1168, dated November 7, 2011, which
recommends repetitive inspections at 500-flight-cycle intervals for new
delivery and replacement of fittings after a 5-year threshold elapses.
As stated previously, we are releasing this supplemental NPRM
because it has been recently determined that Airbus modification 32025
does not mitigate the unsafe condition. In addition, we have recently
determined that there is no terminating action available for the
repetitive inspection requirement of this supplemental NPRM.
Requests To Clarify Approved Alternative Methods of Compliance (AMOCs)
United and US Airways requested clarification of the applicability
of AMOCs previously approved for AD 2006-11-04, Amendment 39-14608 (71
FR 29578, May 23, 2006); and AD 2008-08-04, Amendment 39-15456 (73 FR
19975, April 14, 2008).
We agree to clarify the validity of AMOC approvals granted for AD
2006-11-04, Amendment 39-14608 (71 FR 29578, May 23, 2006); and AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008). We have
revised the statement in paragraph (u)(1) of this supplemental NPRM to
state that AMOCs approved previously in accordance with AD 2006-11-04
and AD 2008-08-04 are approved as AMOCs for the corresponding
provisions of this supplemental NPRM.
Request To Reference a Repair Drawing
United requested that we revise the NPRM (76 FR 72350, November 23,
2011) to include recently released Airbus Repair Drawing R572 481,
Issue A, dated November 11, 2011, in paragraphs (j)(1) and (j)(2) of
the NPRM. United also requested that if Airbus Mandatory Service
Bulletin A320-57-1118, Revision 04, dated June 4, 2008, is revised
before the release of the final rule, then that service bulletin should
also include Airbus Repair Drawing R572 481, Issue A, dated November
11, 2011, and the new service information should be referenced in the
final rule.
We disagree. Paragraph (j)(1) of the NPRM (76 FR 72350, November
23, 2011) references ``Airbus Service Bulletin A320-57-1118,'' which
includes all revisions of that service bulletin. Once an operator
accomplishes any revision of Airbus Service Bulletin A320-57-1118, the
affected airplane is subject to the actions specified in paragraphs
(k), (m), and (n) of this supplemental NPRM. In addition, Airbus Repair
Drawing R572 481, Issue A, dated November 11, 2011, is not an
acceptable method of compliance for any action in this supplemental
NPRM and, therefore, would not be included in the conditions specified
in paragraphs (j)(1) and (j)(2) of this supplemental NPRM. We have not
changed the supplemental NPRM in this regard.
Request To Include New Service Information
United requested that we revise the NPRM (76 FR 72350, November 23,
2011) to refer to Airbus Mandatory Service Bulletin A320-57A1166,
Revision 01, dated October 19, 2011, for the actions specified in
paragraph (o) of the NPRM.
We agree. As discussed previously, Airbus Mandatory Service
Bulletin A320-57A1166, Revision 01, dated October 19, 2011, was issued
while the comment period was open for the NPRM (76 FR 72350, November
23, 2011). That service bulletin includes minor edits and does not add
an additional economic burden. We have revised paragraph (n) of this
supplemental NPRM (paragraph (o) of the NPRM) to reference Airbus
Mandatory Service Bulletin A320-57A1166, Revision 01, dated October 19,
2011; and added paragraph (t) to this supplemental NPRM to give credit
for corresponding actions done before the effective date of the AD
using Airbus Service Bulletin A320-57A1166, dated January 12, 2011. We
have also updated the subsequent paragraph identifiers accordingly.
Request To Reference Specifications Without Revision Dates
US Airways requested that we revise the NPRM (76 FR 72350, November
23, 2011) to specify the structural repair manual chapter and
paragraph, or by drawing number, without revision dates. US Airways
stated that specification of corrective actions by document dates, as
specified in paragraph (i) of the NPRM, unnecessarily restricts the use
of latest and best repair practices. The referenced repair documents
are now roughly between seven and eleven years old. US Airways pointed
out that Airbus has made efforts to improve these repairs in that time
frame, and by restricting operators to the use of historic documents,
the FAA is making it difficult to incorporate improved repair methods.
We partially agree. We agree with US Airways that the most current
approved service information should be referenced in the AD. We must
reference the revision dates in an AD when referring to the service
document, because not doing so violates the Office of the Federal
Register (OFR) policies for approval of materials ``incorporated by
reference'' in rules. In general terms, we are required by these OFR
policies to either publish the service document contents as part of the
actual AD language; or submit the service document to the OFR for
approval as ``referenced'' material, in which case we may only refer to
such material in the text of an AD. The AD may refer to the service
document only if the OFR approved it for ``incorporation by
reference.'' To allow operators to use later revisions of the
referenced document (issued after publication of the AD), either we
must revise the AD to reference specific later revisions, or operators
may request approval to use later revisions as an AMOC with the AD
under the provisions of paragraph (u) of this supplemental NPRM. As
stated previously, we have revised the supplemental NPRM to accept
previously approved AMOCs for the corresponding provisions of this
supplemental NPRM. We have not changed the AD regarding incorporating
service information without revision dates.
Request To Reformat Table 1 of the NPRM (76 FR 72350, November 23,
2011)
US Airways requested that we correct the formatting of table 1 to
paragraph (k) of the NPRM (76 FR 72350, November 23, 2011). The
commenter stated that the details in the first two rows of that table
are data for Airbus Model A319 and A320 airplanes, while the third and
fourth rows provide information for Model A321 airplanes.
We find that clarification is necessary. The commenter correctly
specified the information in table 1 to paragraph (k) of the NPRM (76
FR 72350, November 23, 2011), but identified no errors that require
correction. The information in table 1 to paragraph (k) of this
supplemental NPRM is correct. However, we have added a reference to
Model A318 airplanes to the first row of the table.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent
[[Page 60328]]
information and determined an unsafe condition exists and is likely to
exist or develop on other products of the same type design.
Certain changes described above expand the scope of the earlier
NPRM (76 FR 72350, November 23, 2011). As a result, we have determined
that it is necessary to reopen the comment period to provide additional
opportunity for the public to comment on this proposed AD.
Additional Changes to the Supplemental NPRM
We have removed certain service information as a method of
compliance from paragraphs (g), (h), (i), and (j) of the NPRM (76 FR
72350, November 23, 2011), in this supplemental NPRM. We have also
added certain credit for actions done before the effective date of this
AD in paragraph (t) of this supplemental NPRM, using that removed
service information.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 740 products of U.S. registry.
The actions that are required by AD 2008-08-04, Amendment 39-15456
(73 FR 19975, April 14, 2008), and retained in this proposed AD take
about 73 work-hours per product, at an average labor rate of $85 per
work hour. Required parts would cost about $3,860 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
parts. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, the estimated cost of the currently required actions is
$10,065 per product.
We estimate that it would take about 3 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the new actions in this proposed AD on U.S. operators to be
up to $188,700, or $255 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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 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 this 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), and
adding the following new AD:
Airbus: Docket No. FAA-2011-1253; Directorate Identifier 2011-NM-
079-AD.
(a) Comments Due Date
We must receive comments by November 19, 2012.
(b) Affected ADs
This AD supersedes AD 2008-08-04, Amendment 39-15456 (73 FR
19975, April 14, 2008), which superseded AD 2006-11-04, Amendment
39-14608 (71 FR 29578, May 23, 2006).
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122;
A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-
132, and A319-133; A320-111, A320-211, A320-212, A320-214, A320-231,
A320-232, and A320-233; and A321-111, A321-112, A321-131, A321-211,
A321-212, A321-213, A321-231, and A321-232 airplanes; certificated
in any category; all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of 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.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Repetitive Detailed Inspections With Changes
This paragraph restates the requirements of paragraph (f) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with
changes. Except for airplanes on which Airbus modification 32025 has
been accomplished in production, within 8 days after June 7, 2006
(the effective date of AD 2006-11-04, Amendment 39-14608 (71 FR
29578, May 23, 2006)), 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 the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the European Aviation
Safety Agency (EASA) (or its delegated agent). Repeat the inspection
thereafter at intervals not to exceed 8 days, or before further
flight after a hard landing, whichever is first. As of May 19, 2008
(the effective date of AD 2008-08-04), the repetitive inspections
required by paragraph (k) of this AD must be accomplished in lieu
[[Page 60329]]
of the repetitive inspections required by this paragraph.
(h) Retained Optional Inspection Method With Changes
This paragraph restates the requirements of paragraph (g) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with
revised service information. 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 an applicable method
specified in paragraph (h)(1) or (h)(2) of this AD is an acceptable
alternative method of compliance for the initial and repetitive
inspections required by paragraph (g) of this AD.
(1) In accordance with a method approved by the Manager,
International Branch, ANM-116, or the EASA (or its delegated agent).
(2) In accordance with Task 57-29-03-270-801-A-01, Gear Rib
Forward Lug Attachment for the Main Landing Gear Before Modification
32025J2211, of Chapter 57, Wings, of the Airbus A318/A319/A320/A321
Nondestructive Testing Manual, Revision 89, dated August 1, 2011.
(i) Retained Optional Terminating Action With Changes
This paragraph restates the requirements of paragraph (h) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008). Repair
of the forward lugs of the support rib 5 fitting of the left- and
right-hand MLG done before the effective date of this AD, 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 paragraphs (g), (h), (k),
(l), and (m) of this AD.
(j) Retained Referenced Conditions With Revised Affected Airplanes
To identify affected airplanes in paragraphs (k), (m), and (o)
of this AD, this AD refers to the following conditions:
(1) Airplanes on which the modification of the MLG rib bushes
specified in Airbus Service Bulletin A320-57-1118 has been done.
(2) Airplanes on which a repair of the MLG support rib 5 fitting
has been done in accordance with paragraph 5.C. of Subsection 57-26-
13, Attachments--Main Landing Gear, of the Airbus A319 Structural
Repair Manual (SRM), Revision November 1, 2004; paragraph 5.D. of
Subsection 57-26-13, Attachments--Main Landing Gear, of the Airbus
A320 SRM, Revision November 1, 2004; or paragraph 5.D. of Subsection
57-26-13, Attachments--Main Landing Gear, of the Airbus A321 SRM,
Revision February 1, 2005; as applicable.
(3) Airplanes on which replacement in service of the MLG support
rib 5 specified in Airbus Repair Instruction R572-58507 and Airbus
Repair Drawing R57258209, or Airbus Repair Instruction R572-45020
and Airbus Repair Drawing R57245019, as applicable, has been done.
(k) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (i) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008). For
airplanes on which none of the actions specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD have been done, except for
airplanes on which Airbus modification 32025 has been accomplished:
At the applicable time specified in table 1 to paragraph (k) 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 to paragraph (k) of this AD or before further
flight after a hard landing, whichever is first, until the
modification required by paragraph (m) of this AD has been
accomplished. Accomplishing the initial inspection terminates the
requirements of paragraph (g) of this AD.
Table 1 to Paragraph (k) of This AD--Compliance Times
----------------------------------------------------------------------------------------------------------------
Airplanes Initial inspection Repetitive interval
----------------------------------------------------------------------------------------------------------------
(1) Model A318, A319, and A320 (i) If the most recent inspection is a Within 150 flight cycles after
airplanes. detailed inspection done in accordance a visual inspection.
with paragraph (g) of this AD, inspect
within 150 flight cycles after the most
recent detailed inspection.
(ii) If the most recent inspection is an Within 940 flight cycles after
ultrasonic inspection done in an ultrasonic inspection.
accordance with paragraph (h) of this
AD, inspect within 940 flight cycles
after the most recent ultrasonic
inspection.
(2) Model A321 airplanes.............. (i) If the most recent inspection is a Within 100 flight cycles after
detailed inspection done in accordance a visual inspection.
with paragraph (g) of this AD, inspect
within 100 flight cycles after the most
recent detailed inspection.
(ii) If the most recent inspection is an Within 630 flight cycles after
ultrasonic inspection done in an ultrasonic inspection.
accordance with paragraph (h) of this
AD, inspect within 630 flight cycles
after the most recent ultrasonic
inspection.
----------------------------------------------------------------------------------------------------------------
(l) Retained Corrective Action
This paragraph restates the requirements of paragraph (j) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008). If any
cracking is found during any inspection required by paragraph (k) of
this AD: Before further flight, repair or replace the cracked MLG
fitting, in accordance with a method approved by the Manager,
International Branch, ANM-116, or the EASA (or its delegated agent).
(m) Retained Rib Bushing Modification
This paragraph restates the requirements of paragraph (k) of AD
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with
revised service information. Except for airplanes on which the
actions specified in paragraph (j)(1) or (j)(3) of this AD have been
done, and except for airplanes on which Airbus modification 32025
has been accomplished: Within 60 months after May 19, 2008 (the
effective date of AD 2008-08-04), 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; or Airbus
Mandatory Service Bulletin A320-57-1118, Revision 04, dated June 4,
2008. Accomplishing this modification terminates the requirements of
paragraphs (g) and (k) of this AD, and then the requirements of
paragraph (n) of this AD must be done.
(n) New Post-Modification/Post-Repair Inspections
For airplanes on which the actions specified in paragraph
(j)(1), (j)(2), or (m) of this AD have been done: At the later of
the times specified in paragraphs (n)(1) and (n)(2) of this AD, do a
detailed inspection for cracks of the forward lug of each left-hand
and right-hand MLG support rib 5 fitting, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-57A1166, Revision 01, dated October 19, 2011. Repeat the
inspection thereafter at intervals not to exceed 500 flight cycles.
(1) Within 2,000 flight cycles after accomplishing the
modification specified in paragraph (j)(1) or (m) of this AD, or the
repair specified in paragraph (j)(2) of this AD, as applicable.
(2) Within 250 flight cycles after the effective date of this
AD, without exceeding 3 months after the effective date of this AD.
(o) New Repair of Cracking Found During Post-Modification/Post-Repair
If any crack is detected during any inspection required by
paragraph (n) of this AD: Before further flight, repair using a
method approved by either the Manager,
[[Page 60330]]
International Branch, ANM-116, Transport Airplane Directorate, FAA,
or the EASA (or its delegated agent).
(p) New Optional Terminating Action
Replacement of a MLG support rib 5 fitting at any position
(left-hand or right-hand), as specified in paragraph (j)(3) of this
AD, terminates the requirements of paragraphs (k) and (n) of this AD
for the MLG support rib 5 fitting at that position.
(q) New Repetitive Detailed Inspection for Certain Airplanes
For airplanes on which the actions specified in paragraph (j)(3)
of this AD have been done: Within 60 months after the replacement or
within 500 flight cycles after the effective date of this AD,
whichever occurs later, do a detailed inspection of the forward lug
of each left-hand and right-hand MLG support Rib 5 fitting that has
been replaced, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320-57A1166, Revision 01, dated
October 19, 2011. Repeat the inspection thereafter at intervals not
to exceed 500 flight cycles.
(r) New Repetitive Inspections for Airplanes with Airbus Modification
32025
For airplanes on which Airbus modification 32025 has been
accomplished: At the applicable time specified in paragraph (r)(1,)
(r)(2), (r)(3), or (r)(4) of this AD, do a detailed inspection for
cracks of the forward lug of each left-hand and right-hand MLG
support rib 5 fitting, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1168, dated November
7, 2011. Repeat the inspection thereafter at intervals not to exceed
500 flight cycles.
(1) For airplanes on which the MLG support rib 5 has not been
modified nor repaired since the first flight of the airplane as of
the effective date of this AD: Within 60 months after the first
flight of the airplane or within 500 flight cycles after the
effective date of this AD, whichever occurs later.
(2) For airplanes on which the MLG support rib 5 has been
replaced as specified in paragraph (j)(3) of this AD as of the
effective date of this AD: Within 60 months after the replacement of
the MLG support rib 5 or within 500 flight cycles after the
effective date of this AD, whichever occurs later.
(3) For airplanes on which the MLG support rib 5 has been
repaired according to the SRM or a repair approval sheet as of the
effective date of this AD: At the later of the times specified in
paragraph (r)(3)(i) or (r)(3)(ii) of this AD.
(i) Within 2,000 flight cycles after the repair.
(ii) Within 250 flight cycles or 3 months after the effective
date of this AD, whichever occurs first.
(4) For airplanes having a manufacturer serial number listed in
table 2 to paragraph (r)(4) of this AD, and on which the MLG support
rib 5 has been inspected before the effective date of this AD
according to specific Airbus repair instructions or technical
disposition: At the later of the times specified in paragraph
(r)(4)(i) or (r)(4)(ii) of this AD.
Table 2 to Paragraph (r)(4) of This AD--Manufacturer Serial Number (S/N)
------------------------------------------------------------------------
------------------------------------------------------------------------
S/N--
------------------------------------------------------------------------
1965 2056 2155
2274 2278 2288
2321 2478 2586
2588 2612 2672
2688 2707 2929
2942 3089 3117
3361 3427 3486
3489 3806 3891
3937 4243 4345
------------------------------------------------------------------------
(i) Within 2,000 flight cycles after the last inspection done
using specific Airbus repair instructions or a technical
disposition, or within 60 months since first flight of the airplane,
whichever occurs later.
(ii) Within 250 flight cycles or 3 months after the effective
date of this AD, whichever occurs first.
(s) New Repair of Cracking
If any crack is detected during any inspection required by
paragraph (q) or (r) of this AD: Before further flight, repair using
a method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the EASA (or its
delegated agent).
(t) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus A318/A319/A320/A321
Nondestructive Testing Manual, Chapter 51-90-00, Revision dated
February 1, 2003.
(2) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using 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).
(3) This paragraph provides credit for the actions specified in
paragraph (i) of this AD, if those actions were performed before the
effective date of this AD using paragraph 5.C. of Subsection 57-26-
13, Attachments--Main Landing Gear, of the Airbus A319 Structural
Repair Manual (SRM), Revision November 1, 2004; paragraph 5.D. of
Subsection 57-26-13, Attachments--Main Landing Gear, of the Airbus
A320 SRM, Revision November 1, 2004; or paragraph 5.D. of Subsection
57-26-13, Attachments--Main Landing Gear, of the Airbus A321 SRM,
Revision February 1, 2005; as applicable.
(4) This paragraph provides credit for the inspections required
by paragraphs (n) and (r) of this AD, if the inspections were
performed before the effective date of this AD using Airbus Service
Bulletin A320-57A1166, dated January 12, 2011.
(5) This paragraph provides credit for the modification required
by paragraph (m) of this AD, if the modification was performed
before May 19, 2008 (the effective date of AD 2008-08-04, Amendment
39-15456 (73 FR 19975, April 14, 2008), using service information
identified in paragraph (t)(5)(i), (t)(5)(ii), or (t)(5)(iii) of
this AD.
(i) Airbus Service Bulletin A320-57-1118, dated September 5,
2002.
(ii) Airbus Service Bulletin A320-57-1118, Revision 01, dated
August 28, 2003.
(iii) Airbus Service Bulletin A320-57-1118, Revision 02, dated
August 2, 2006.
(u) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD. AMOCs approved previously in
accordance with AD 2006-11-04, Amendment 39-14608 (71 FR 29578, May
23, 2006); and AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April
14, 2008); are approved as AMOCs for the corresponding provisions of
this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to ensure the product
is airworthy before it is returned to service.
(v) Related Information
Refer to MCAI EASA Airworthiness Directive 2012-0032, dated
February 24, 2012, and the following service information, for
related information.
(1) Airbus Mandatory Service Bulletin A320-57-1118, Revision 04,
dated June 4, 2008.
(2) Airbus Mandatory Service Bulletin A320-57A1166, Revision 01,
dated October 19, 2011.
(3) Airbus Service Bulletin A320-57-1168, dated November 7,
2011.
(4) Airbus Service Bulletin A320-57-1118, Revision 03, dated
April 23, 2007.
(5) Airbus Service Bulletin A320-57-1138, Revision 01, dated
October 27, 2006.
(6) Task 57-29-03-270-801-A-01, Gear Rib Forward Lug Attachment
for the Main Landing Gear Before Modification 32025J2211, of Chapter
57, Wings, of the Airbus A318/A319/A320/A321 Nondestructive Testing
Manual, Revision 89, dated August 1, 2011.
[[Page 60331]]
Issued in Renton, Washington, on September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-24393 Filed 10-2-12; 8:45 am]
BILLING CODE 4910-13-P
