Airworthiness Directives; Airbus Airplanes, 9341-9346 [2013-02898]
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Federal Register / Vol. 78, No. 27 / Friday, February 8, 2013 / Proposed Rules
facts within his or her personal
knowledge, but, unless specifically
authorized to do so by the Director, the
employee must not:
(1) Disclose confidential or privileged
information; or
(2) Testify as an expert or opinion
witness with regard to any matter
arising out of the employee’s official
duties or FHFA’s mission or functions.
This provision does not apply to
requests from the United States for
expert or opinion testimony.
(d) The Director may assign FHFA
Counsel to be present for an employee’s
testimony.
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§ 1215.13 Restrictions That Apply to
Records and Information.
(a) The Director may impose
conditions or restrictions on the release
of records and information, including
but not limited to requiring that parties
to the legal proceeding obtain a
protective order or execute a
confidentiality agreement to limit access
and further disclosure, or that parties
take other appropriate steps to comply
with applicable privacy requirements.
The terms of a protective order or
confidentiality agreement must be
acceptable to the Director. In cases
where protective orders or
confidentiality agreements have already
been executed, the Director may
condition the release of records and
information on an amendment to the
existing protective order or
confidentiality agreement.
(b) If the Director so determines,
original agency records may be
presented for examination in response
to a demand or request, but they are not
to be presented as evidence or otherwise
used in a manner by which they could
lose their status as original records, nor
are they to be marked or altered. In lieu
of the original records, certified copies
will be presented for evidentiary
purposes.
(c) The scope of permissible
production is limited to that set forth in
the prior, written authorization granted
by the Director.
(d) If records or information are
produced in connection with a legal
proceeding, the demanding or
requesting party must:
(1) Promptly notify all other parties to
the legal proceeding that the records or
information are FHFA records or
information and are subject to this part
and any applicable confidentiality
agreement or protective order;
(2) Provide copies of any
confidentiality agreement or protective
order to all other parties; and
(3) Retrieve the records or information
from the court or other competent
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authority’s file when the court or other
competent authority no longer requires
the records or information and certify
that every party covered by a
confidentiality agreement, protective
order, or other privacy protection has
destroyed all copies of the records or
information.
§ 1215.14 Procedure in the Event of an
Adverse FHFA Determination.
(a) Procedure for seeking
reconsideration of FHFA’s
determination. A demanding or
requesting party seeking reconsideration
of FHFA’s rejection of a demand or
request, or of any restrictions on
receiving records, information, or
testimony, may seek reconsideration of
the rejection or restrictions as follows—
(1) Notice of Intention to Petition for
Reconsideration. The aggrieved
demanding or requesting party may seek
reconsideration by filing a written
Notice of Intention to Petition for
Reconsideration (Notice) within 10
business days of the date of FHFA’s
determination. The Notice must identify
the petitioner, the determination for
which reconsideration is being
petitioned, and any dates (such as
deposition, hearing, or court dates) that
are significant to petitioner. The Notice
must be served in accordance with
§ 1215.7.
(2) Petition for Reconsideration.
Within five business days of filing
Notice, the petitioner must file a
Petition for Reconsideration (Petition) in
accordance with § 1215.7. The Petition
must contain a clear and concise
statement of the basis for the
reconsideration with supporting
authorities. Determinations about
petitions for reconsideration are within
the discretion of the FHFA Director, and
are final.
(b) Prerequisite to judicial review.
Pursuant to section 704 of the
Administrative Procedure Act, 5 U.S.C.
704, a petition to FHFA for
reconsideration of a final determination
made under the authority of this part is
a prerequisite to judicial review.
§ 1215.15
Conflicting Court Order.
Notwithstanding FHFA’s rejection of
a demand for records, information, or
testimony, if a court or other competent
authority orders an FHFA employee to
comply with the demand, the employee
must promptly notify FHFA’s General
Counsel of the order, and the employee
must respectfully decline to comply,
citing United States ex rel. Touhy v.
Ragen, 340 U.S. 462 (1951). An
employee’s failure to notify the General
Counsel of a court or other authority’s
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9341
order is grounds for discipline or other
adverse action.
§ 1215.16
Fees.
(a) The Director may condition the
production of records, information, or
an employee’s appearance on advance
payment of reasonable costs to FHFA,
which may include but are not limited
to those associated with employee
search time, copying, computer usage,
and certifications.
(b) Witness fees will include fees,
expenses, and allowances prescribed by
the rules applicable to the particular
legal proceeding. If no fees are
prescribed, FHFA will base fees on the
rule of the federal district court closest
to the location where the witness will
appear. Such fees may include but are
not limited to time for preparation,
travel, and attendance at the legal
proceeding.
Dated: February 2, 2013.
Edward J. DeMarco,
Acting Director, Federal Housing Finance
Agency.
[FR Doc. 2013–02908 Filed 2–7–13; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0088; Directorate
Identifier 2011–NM–233–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all Airbus Model A318,
A319, A320, and A321 series airplanes.
The existing AD currently requires
repetitive inspections of the upper
support of the nose landing gear (NLG),
and related investigative and corrective
actions if necessary; and also provides
an optional terminating action for the
repetitive inspections. Since we issued
that AD, we have determined that
previously allowed terminating actions
no longer address the unsafe condition
and that a new terminating action is
necessary. This proposed AD would
require installing a new enhanced
manufacturing and maintainability
(EMM) braking and steering control unit
(BSCU) standard and adds airplanes to
SUMMARY:
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the applicability. We are proposing this
AD to prevent landings with the NLG
turned 90 degrees from centerline,
which could result in reduced
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by March 25, 2013.
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.
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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
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to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0088; Directorate Identifier
2011–NM–233–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
On August 17, 2007, we issued AD
2007–18–09, Amendment 39–15189 (72
FR 51164, September 6, 2007), which
superseded AD 2005–24–06,
Amendment 39–14386 (70 FR 70715,
November 23, 2005). That AD required
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007), The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2011–0201, dated October 13, 2011
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
In 2005, an A320 aeroplane experienced a
landing with the Nose Landing Gear (NLG)
wheels rotated at 90 degrees to the aeroplane
centreline.
Investigation showed that the upper
support of the NLG shock absorber was
damaged and the anti-rotation lugs were
ruptured. This caused the nose wheels to lose
their centred position reference. The affected
Braking and Steering Control Unit (BSCU)
had logged a steering system fault because
hydraulic power was not available at the time
of steering system checks, therefore the BSCU
was not able to proceed with the re-centring
of the wheels. Failure to centre the NLG
wheels correctly may result in a failure of the
NLG to retract.
To prevent further landing incidents with
NLG wheels rotated at 90 degrees, DGAC
France issued AD F–2005–191 [which
corresponds to FAA AD 2005–24–06,
Amendment 39–14386 (70 FR 70715,
November 23, 2005)] to require the
implementation of an operational procedure
and the accomplishment of certain
maintenance actions.
EASA AD 2006–0174, [which corresponds
to FAA AD 2007–18–09, Amendment 39–
15189 (72 FR 51164, September 6, 2007)]
which superseded AD F–2005–191, was
issued to extend the applicability and to
introduce repetitive boroscope inspections of
the NLG upper support lugs and cylinder
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lugs which have been driven by EMM BSCU
L4.1 (Part Number (P/N) E21327001) or L4.5
(P/N E21327003) and, corrective actions,
depending on findings.
Since that AD was issued, Airbus has
demonstrated the acceptability of installing
EMM BSCU L4.9B (P/N E21327006 or P/N
E21327106) or conventional BSCU std 10 (P/
N C202163392E34) or conventional BSCU std
10.1 (P/N C202163392E35) as terminating
action for the actions required by EASA AD
2006–0174, for aeroplanes fitted with twin
wheel Main Landing Gear (MLG) units.
For the reasons described above, this AD
retains some of the requirements of EASA AD
2006–0174, which is superseded, extends the
applicability to all A318, A319, A320 and
A321 aeroplanes, requires the installation of
BSCU L4.9B, or BSCU std 10, or BSCU std
10.1 for in service aeroplanes fitted with twin
wheel MLG, which constitutes terminating
action for the repetitive inspections and
checks required by this AD.
Installation of a NLG with new upper
support anti-rotation lugs and new cylinders
lugs, or installation of a NLG for which it can
be demonstrated that it was never driven by
EMM BSCU L4.1 or L4.5, is no longer
considered as terminating action for the
requirements of this AD.
The unsafe condition is the NLG turning
90 degrees from centerline, which could
result in reduced controllability of the
airplane. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued the following
service bulletins.
• Airbus Mandatory Service Bulletin
A320–32–1310, Revision 01, dated June
23, 2011.
• Airbus Mandatory Service Bulletin
A320–32–1336, Revision 01, dated
January 10, 2008.
• Airbus Service Bulletins A320–32–
1350, dated July 31, 2008.
• Airbus Service Bulletin A320–32–
1360, dated March 18, 2009.
• Airbus Service Bulletin A320–32–
1369, Revision 01, dated March 31,
2010.
• Airbus Service Bulletin A320–32–
1387, dated April 7, 2011.
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
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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.
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Differences Between This AD and the
MCAI or Service Information
Airbus Mandatory Service Bulletin
A320–32–1310, Revision 01, dated June
23, 2011, specifies to use Airbus
recommendations when restoring the
NLG, but this proposed AD would
require restoring the NLG 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).
The MCAI permits accomplishment of
MCAI paragraph 1.1 by inserting a copy
of certain Airbus airplane flight manual
(AFM) temporary revisions into the
AFM. We have not included that
provision in this proposed AD, since the
temporary revisions have already been
incorporated into the AFM.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 755 products of U.S.
registry.
The actions that are required by FAA
AD 2007–18–09, Amendment 39–15189
(72 FR 51164, September 6, 2007), and
retained in this proposed AD take about
3 work-hours per product, at an average
labor rate of $85 per work hour. Based
on these figures, the estimated cost of
the currently required actions is $255
per product.
We estimate that it would take about
35 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. 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, we estimate the cost of the
proposed AD on U.S. operators to be
$2,246,125, or $2,975 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. We have
no way of determining the number of
products that may need these actions.
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
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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.
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§ 39.13
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[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2007–18–09, Amendment 39–15189 (72
FR 51164, September 6, 2007), and
adding the following new AD:
■
Airbus: Docket No. FAA–2013–0088;
Directorate Identifier 2011–NM–233–AD.
(a) Comments Due Date
We must receive comments by March 25,
2013.
(b) Affected ADs
This AD supersedes AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007).
(c) Applicability
This AD applies to the Airbus airplanes
listed in paragraphs (c)(1), (c)(2), (c)(3), and
(c)(4) of this AD; certificated in any category;
all serial numbers.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–111, –211, –212, –214,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Reason
This AD was prompted by a report of an
airplane landing with the nose landing gear
(NLG) turned 90 degrees from centerline, and
from additional reports of upper support
anti-rotation lugs of the NLG rupturing in
service. We are issuing this AD to prevent
landings with the NLG turned 90 degrees
from centerline, which could result in
reduced controllability of the airplane.
(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 Records Review
This paragraph restates the requirements of
paragraph (f) of AD 2007–18–09, Amendment
39–15189 (72 FR 51164, September 6, 2007).
Within 5 days after November 30, 2005 (the
effective date of AD 2005–24–06,
Amendment 39–14386 (70 FR 70715,
November 23, 2005)), perform a records
review to determine whether the airplane is
equipped with or has ever been equipped
with an enhanced manufacturing and
maintainability (EMM) braking and steering
control unit (BSCU) part number (P/N)
E21327001 (standard L4.1, installed by
Airbus Modification 26965, or Airbus Service
Bulletin A320–32–1912) or P/N E21327003
(standard L4.5, installed by Airbus
Modification 33376, or Airbus Service
Bulletin A320–32–1261). Airbus Service
Bulletin A320–32–1310, dated February 8,
2006, is one approved method for doing the
records review.
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(h) Retained Statement of No Further Action
Required
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This paragraph restates the requirements of
paragraph (g) of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007). For airplanes on which
a records review required by paragraph (g) of
this AD conclusively determines that the
airplane is not and never has been equipped
with a BSCU P/N E21327001 or P/N
E21327003, no further action is required by
paragraphs (i), (j), (k), (l), and (m) of this AD.
(i) Retained Airplane Flight Manual (AFM)
Revision
This paragraph restates the requirements of
paragraph (h) of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007). For airplanes that are not
specified in paragraph (h) of this AD and on
which Airbus Modification 31152 has not
been incorporated in production (i.e.,
applicable only to aircraft with steering
powered by the green hydraulic system):
Within 10 days after November 30, 2005 (the
effective date of AD 2005–24–06,
Amendment 39–14386 (70 FR 70715,
November 23, 2005)), revise the Limitation
Section of the Airbus A318/319/320/321
Aircraft Flight Manual (AFM) to include the
following information. This may be done by
inserting a copy of this AD into the AFM:
The ECAM message, in case of a nose
wheel steering failure, will be worded as
follows:
—‘‘WHEEL N/W STRG FAULT’’ for aircraft
with the FWC E3 and subsequent standards
—‘‘WHEEL N.W. STEER FAULT’’ for aircraft
with the FWC E2 Standard.
› If the L/G SHOCK ABSORBER FAULT
ECAM caution is triggered at any time in
flight, and the WHEEL N/W STRG FAULT
ECAM caution is triggered after the landing
gear extension:
When all landing gear doors are indicated
closed on ECAM WHEEL page, reset the
BSCU:
—A/SKID&N/W STRG---------------------------OFF THEN ON
If the WHEEL N/W STRG FAULT ECAM
caution is no longer displayed, this indicates
a successful nose wheel re-centering and
steering recovery.
—Rearm the AUTO BRAKE, if necessary.
If the WHEEL N/W STRG FAULT ECAM
caution remains displayed, this indicates that
the nose wheel steering remains lost, and that
the nose wheels are not centered.
—During landing, delay nose wheel
touchdown for as long as possible.
—Refer to the ECAM STATUS.
› If the WHEEL N/W STRG FAULT
ECAM caution appears, without the L/G
SHOCK ABSORBER FAULT ECAM caution:
—No specific crew action is requested by the
WHEEL N/W STRG FAULT ECAM caution
procedure.
—Refer to the ECAM STATUS.
Accomplishment of the actions required by
paragraph (r) of this AD terminates the
requirements of this paragraph, and the AFM
limitation required by this paragraph must be
removed.
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Note 1 to paragraph (i) of this AD: When
a statement identical to that in paragraph (i)
of this AD has been included in the general
revisions of the AFM, the general revisions
may be inserted into the AFM, and the copy
of this AD or AD 2007–18–09, Amendment
39–15189 (72 FR 51164, September 6, 2007),
may be removed from the AFM.
(j) Retained Inspection Thresholds
This paragraph restates the requirements of
paragraph (i) of AD 2007–18–09, Amendment
39–15189 (72 FR 51164, September 6, 2007).
For airplanes that are not specified in
paragraph (h) of this AD, at the earlier of the
times specified in paragraphs (j)(1) and (j)(2)
of this AD: Do a special detailed inspection
(boroscopic) for broken or cracked NLG
upper support lugs and missing cylinder
lugs, and do all applicable related
investigative/corrective actions before further
flight. Do all actions in accordance with
Airbus Technical Note 957.1901/05, dated
October 18, 2005; or the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1310, dated February 8, 2006. After
October 11, 2007 (the effective date of AD
2007–18–09), only Airbus Service Bulletin
A320–32–1310, dated February 8, 2006, may
be used. Where Airbus Service Bulletin
A320–32–1310, dated February 8, 2006,
specifies that restoring the NLG is necessary
in accordance with Airbus recommendations,
this AD requires restoring the NLG 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 the applicable interval specified
in paragraph (k) or (l) of this AD until the
inspection required by paragraph (t) of this
AD is accomplished.
(1) Within 100 flight cycles following an
electronic centralized aircraft monitoring
(ECAM) caution ‘‘L/G SHOCK ABSORBER
FAULT’’ associated with at least one of the
following centralized fault display system
(CFDS) messages specified in paragraph
(j)(1)(i), (j)(1)(ii), or (j)(1)(iii) of this AD. As
of the effective date of this AD, for the
conditions specified in paragraph (j)(1) of
this AD, do the actions required by paragraph
(r) of this AD.
(i) ‘‘N L/G EXT PROX SNSR 24GA TGT
POS.’’
(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT
POS.’’
(iii) ‘‘N L/G SHOCK ABSORBER FAULT
2526GM.’’
(2) At the later of the times specified in
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 20 months, 6,000 flight hours, or
4,500 flight cycles since the date of issuance
of the original French standard airworthiness
certificate, or the original French export
certificate of airworthiness, whichever occurs
first.
(ii) Within 6 months, 1,800 flight hours, or
1,350 flight cycles after October 11, 2007 (the
effective date of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007)), whichever occurs first.
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(k) Retained Repetitive Inspection Intervals
for BSCU Standard L4.1 or L4.5
This paragraph restates the requirements of
paragraph (j) of AD 2007–18–09, Amendment
39–15189 (72 FR 51164, September 6, 2007).
For airplanes not specified in paragraph (h)
of this AD that are equipped with EMM
BSCU standard L4.1 or L4.5: Repeat the
inspection specified in paragraph (j) of this
AD thereafter at intervals not to exceed the
earliest of 6 months; 1,800 flight hours; 1,350
flight cycles; or 100 flight cycles following
certain ECAM cautions and CFDS messages,
as specified in paragraph (j)(1) of this AD.
(l) Retained Repetitive Inspection Intervals
for BSCU Standard L4.8 or Non-EMM BSCU
This paragraph restates the requirements of
paragraph (k) of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007). For airplanes not
specified in paragraph (h) of this AD that are
equipped with EMM BSCU standard L4.8 or
a non-EMM BSCU: Repeat the inspection
specified in paragraph (j) of this AD
thereafter at intervals not to exceed the
earliest of 20 months; 6,000 flight hours;
4,500 flight cycles; or 100 flight cycles
following certain ECAM cautions and CFDS
messages, as specified in paragraph (j)(1) of
this AD.
(m) Retained Optional Terminating Action
With Limiting Date Restriction
This paragraph restates the requirements of
paragraph (l) of AD 2007–18–09, Amendment
39–15189 (72 FR 51164, September 6, 2007)
with a limiting date restriction. For airplanes
that are not specified in paragraph (h) of this
AD: Installation of an NLG with new upper
support anti-rotation lugs and new cylinder
lugs, or installation of an NLG that was never
driven by EMM BSCU standard L4.1 or L4.5;
combined with installation of EMM BSCU
standard L4.8 or a non-EMM BSCU; before
the effective date of this AD; constitutes
terminating action for the requirements of
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD. Do the installations in accordance with
a method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent). Chapter 32 of
the Airbus A318/A319/A320/A321 Aircraft
Maintenance Manual (AMM) is one approved
method for doing the installations before the
effective date of this AD.
(n) Retained Statement of No Reporting
Required
This paragraph restates the requirements of
paragraph (m) of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007). Although Airbus Service
Bulletin A320–32–1310, dated February 8,
2006, specifies sending certain inspection
results to Airbus, this AD does not include
that requirement.
(o) Part Number Identification
For the purpose of this AD, the following
part numbers are identified.
(1) P/N E21327001: installed by Airbus
Modification 26965 or by Airbus Service
Bulletin A320–32–1912 in service: EMM
BSCU L4.1.
(2) P/N E21327003: installed by Airbus
Modification 33376 or Airbus Service
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Bulletin A320–32–1261 in service: EMM
BSCU L4.5.
(3) P/N E21327004: installed by Airbus
modification 35216 or Airbus Service
Bulletin A320–32–1305 or Airbus Service
Bulletin A320–32–1343/AOT A320–32A1343
in service: EMM BSCU L4.8.
(4) P/N E213270B1: installed by Airbus
modification 31931 or Airbus Service
Bulletin A320–32–1206: EMM BSCU L5–2.
(5) P/N E21327006: installed by Airbus
modification 38973 or Airbus Service
Bulletin A320–32–1350 or Airbus Service
Bulletin A320–32–1361: EMM BSCU L4.9B.
(6) P/N E21327106: installed by Airbus
modification 151575 or Airbus Service
Bulletin A320–32–1387: EMM BSCU L4.9B.
(7) P/N C202163392E34: installed by
Airbus Service Bulletin A320–32–1336 or
Airbus Service Bulletin A320–32–1360:
conventional BSCU standard (std) 10.
(8) P/N C202163392E35: installed by
Airbus Service Bulletin A320–32–1369:
conventional BSCU std 10.1.
(p) Records Review
Within 5 days after the effective date of
this AD: Perform a records review to
determine whether the airplane is equipped
with or has ever been equipped with an EMM
BSCU having P/N E21327001 (standard L4.1,
installed by Airbus modification 26965, or
Airbus Service Bulletin A320–32–1912) or P/
N E21327003 (standard L4.5, installed by
Airbus modification 33376, or Airbus Service
Bulletin A320–32–1261), or P/N E21327004
(standard L4.8, installed by Airbus
modification 35216, or Airbus Service
Bulletin A320–32–1305, or Airbus Service
Bulletin A320–32–1343/AOT A320–
32A1343), or P/N E213270B1 (standard L5–
2, installed by Airbus modification 31931, or
Airbus Service Bulletin A320–32–1206).
Note 2 to paragraph (p) of this AD:
Accomplishment of the actions specified in
Airbus Mandatory Service Bulletin A320–32–
1310, Revision 01, dated June 23, 2011,
before the effective date of this AD, provides
a method for doing the records review.
wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
(q) No Further Action Required for Certain
Paragraphs
For airplanes on which a records review
required by paragraph (p) of this AD
conclusively determines that the airplane is
not and never has been equipped with an
EMM BSCU having P/N E21327001, or P/N
E21327003, or P/N E21327004, or P/N
E213270B1, no further action is required by
paragraphs (r) and (s) of this AD.
(r) Airplane Flight Manual Revision
For airplanes that are not identified in
paragraph (q) of this AD and on which
Airbus Modification 31152 has not been
incorporated in production (i.e., applicable
only to aircraft with steering powered by the
green hydraulic system): Within 10 days after
the effective date of this AD, revise the
Limitation Section of the Airbus A318/319/
320/321 AFM to include the following
information. This revision may be done by
inserting a copy of this AD into the AFM.
The ECAM message, in case of a nose
wheel steering failure, will be worded as
follows:
VerDate Mar<15>2010
14:16 Feb 07, 2013
Jkt 229001
—‘‘WHEEL N/W STRG FAULT’’ for airplanes
with Flight Warning Computer (FWC)
software post E3P.
—‘‘WHEEL N.W. STEER FAULT’’ for
airplanes with FWC software pre E3P.
› If the L/G SHOCK ABSORBER FAULT
ECAM caution is triggered at any time in
flight, and the WHEEL N/W STRG FAULT
ECAM caution is triggered after the landing
gear extension:
• When all landing gear doors are
indicated closed on ECAM WHEEL page,
reset the BSCU:
—A/SKID&N/W STRG---------------------------OFF THEN ON
• If the WHEEL N/W STRG FAULT ECAM
caution is no longer displayed, this indicates
a successful nose wheel re-centering and
steering recovery.
—Rearm the AUTO BRAKE, if necessary.
• If the WHEEL N/W STRG FAULT ECAM
caution remains displayed, this indicates that
the nose wheel steering remains lost, and that
the nose wheels are not centered.
—During landing, delay nose wheel
touchdown for as long as possible.
—Refer to the ECAM STATUS.
› If the WHEEL N/W STRG FAULT
ECAM caution appears, without the L/G
SHOCK ABSORBER FAULT ECAM caution:
—No specific crew action is requested by the
WHEEL N/W STRG FAULT ECAM caution
procedure.
—Refer to the ECAM STATUS.
Note: For airplanes fitted with pre FWC
E3P standard, read N.W STEER instead of N/
W STRG.
Accomplishment of the actions required by
this paragraph terminates the requirements of
paragraph (i) of this AD and the AFM
revision required by paragraph (i) of this AD
must be removed.
Note 3 to paragraph (r) of this AD: When
a statement identical to that in paragraph (r)
of this AD has been included in the general
revisions of the AFM, the general revisions
may be inserted into the AFM, and the copy
of this AD may be removed from the AFM.
(s) Inspection Following Certain Centralized
Fault Display System Messages
(1) For airplanes other than those
identified in paragraph (q) of this AD: Within
100 flight cycles following an ECAM caution
‘‘L/G SHOCK ABSORBER FAULT’’
associated with at least one of the following
CFDS messages specified in paragraph
(s)(1)(i), (s)(1)(ii), or (s)(1)(iii) of this AD, do
the actions in paragraph (s)(2) of this AD.
(i) ‘‘N L/G EXT PROX SNSR 24GA TGT
POS.’’
(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT
POS.’’
(iii) ‘‘N L/G SHOCK ABSORBER FAULT
2526GM.’’
(2) For airplanes identified in paragraph
(s)(1) of this AD: Do the actions specified in
paragraphs (s)(2)(i) and (s)(2)(ii) of this AD.
(i) Check the NLG strut inflation pressure,
weight-off- and weight-on-wheels, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–32–1310, Revision 01, dated
June 23, 2011, and before further flight, do
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9345
all applicable corrective actions and
adjustments, in accordance with Airbus
A318/A319/A320/A321, Task 12–12–32–
610–001–A Check NLG Shock Absorber
Fluid Level and Charge Pressure (‘‘Two-Point
Check’’—Aircraft on Jacks to start), Revision
August 1, 2012.
(ii) Do a boroscopic inspection for broken
or cracked NLG upper support lugs and
missing or cracked cylinder lugs, and do all
applicable related investigative and
corrective actions before further flight. Do all
actions in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–32–1310,
Revision 01, dated June 23, 2011. Where
Airbus Mandatory Service Bulletin A320–32–
1310, Revision 01, dated June 23, 2011,
specifies restoring the NLG in accordance
with Airbus recommendations, this AD
requires restoring the NLG before further
flight, in accordance with a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA (or its delegated agent).
(t) Initial Boroscopic Inspection
At the applicable times specified in
paragraphs (t)(1) and (t)(2) of this AD: Do a
boroscopic inspection for broken or cracked
NLG upper support lugs and missing or
cracked cylinder lugs, and do all applicable
related investigative and corrective actions
before further flight. Do all actions in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–32–1310, Revision 01, dated
June 23, 2011. Where Airbus Mandatory
Service Bulletins A320–32–1310, Revision
01, dated June 23, 2011, specifies restoring
the NLG in accordance with Airbus
recommendations, this AD requires restoring
the NLG before further flight, in accordance
with a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA (or
its delegated agent). Accomplishment of the
actions required by this paragraph terminate
the requirements of paragraphs (j), (k), and (l)
of this AD.
(1) For airplanes fitted with twin wheel
main landing gear (MLG) that have been
equipped with EMM BSCU standard L4.1,
L4.5, or L4.8: At the later of the times
specified in paragraphs (t)(1)(i) and (t)(1)(ii)
of this AD.
(i) Within 20 months, 6,000 flight hours, or
4,500 flight cycles since first flight of the
airplane, whichever occurs first.
(ii) Within 6 months, or 1,800 flight hours,
or 1,350 flight cycles after the effective date
of this AD, whichever occurs first.
(2) For airplanes fitted with bogie MLG: At
the later of the times specified in paragraphs
(t)(2)(i) and (t)(2)(ii) of this AD.
(i) Within 20 months, or 6,000 flight hours,
or 4,500 flight cycles after the installation of
EMM BSCU standard L5–2, whichever occurs
first.
(ii) Within 6 months, or 1,800 flight hours,
or 1,350 flight cycles after the effective date
of this AD, whichever occurs first.
(u) Repetitive Boroscopic Inspections
After accomplishing the inspection
specified in paragraph (t) of this AD: Repeat
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the inspection required by paragraph (t) of
this AD thereafter at the applicable interval
specified in paragraphs (u)(1), (u)(2), and
(u)(3) of this AD.
(1) For airplanes fitted with twin wheel
MLG that have been equipped with EMM
BSCU standard L4.8: At intervals not to
exceed 20 months, or 6,000 flight hours, or
4,500 flight cycles, whichever occurs first.
(2) For airplanes fitted with twin wheel
MLG that have been equipped with EMM
BSCU standard L4.1 or L4.5: At intervals not
to exceed 6 months, or 1,800 flight hours, or
1,350 flight cycles, whichever occurs first.
(3) For airplanes fitted with bogie MLG: At
intervals not to exceed 20 months, or 6,000
flight hours, or 4,500 flight cycles, whichever
occurs first.
(v) Modification
For airplanes fitted with twin wheel MLG:
Within 6 months after the effective date of
this AD, modify the airplane by installing
EMM BSCU standard L4.9B, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1350,
dated July 3, 2008.
(w) Optional Method of Modification
Doing a modification specified in
paragraph (w)(1), (w)(2), or (w)(3) of this AD,
is acceptable for compliance with the
requirements of paragraph (v) of this AD.
(1) Modification of the airplane by
installing EMM BSCU standard L4.9B, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1387, dated April 7, 2011.
(2) Modification of the airplane by
installing conventional EMM BSCU standard
10, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1360, dated March 18, 2009; or Airbus
Mandatory Service Bulletin A320–32–1336,
Revision 01, dated January 10, 2008.
(3) Modification of the airplane by
installing conventional EMM BSCU standard
10.1 in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1369, Revision 01, dated March 31, 2010.
wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
(x) Terminating Action
In-service modification of an airplane fitted
with twin wheel MLG as required by
paragraph (v) of this AD constitutes
terminating action for the initial and
repetitive inspections required by paragraph
(t) of this AD. In addition, the AFM changes
required by paragraph (r) of this AD may be
removed from the AFM; and the
requirements of paragraph (s) of this AD are
no longer required.
(y) Exemption From Certain Actions
Except for paragraph (y) of this AD,
airplanes that have been delivered with
Airbus modification 38973 and/or Airbus
modification 151575 that install EMM BSCU
standard L4.9B are not affected by the
requirements of this AD, provided that no
installation of previous EMM BSCU
standards L4.1, L4.5, or L4.8 has been
performed since the airplane first flight.
(z) Parts Installation
For airplanes that do not have EMM BSCU
L4.1, or EMM BSCU L4.5, or EMM BSCU
VerDate Mar<15>2010
14:16 Feb 07, 2013
Jkt 229001
L4.8 installed: As of the effective date of this
AD, no person may modify an airplane by
installing EMM BSCU standards L4.1, L4.5,
or L4.8 on any airplane.
(aa) Credit for Previous Actions
(1) This paragraph restates the
requirements of paragraph (n) of AD 2007–
18–09, Amendment 39–15189 (72 FR 51164,
September 6, 2007). This paragraph provides
credit for the inspections required by
paragraph (j) of this AD, if those inspections
were performed before October 11, 2007 (the
effective date of AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007)) using Chapter 12,
Subject 12–14–32 of the Airbus A318/A319/
A320/A321 AMM, as revised by Airbus
A318/A319/A320/A321 AMM Temporary
Revision 12–001, dated November 13, 2005.
(2) This paragraph provides credit for the
inspections and related investigative/
corrective actions required by paragraphs (j),
(k), and (l) of this AD, if those inspections
were performed before the effective date of
this AD using Airbus Service Bulletin A320–
32–1310, dated February 8, 2006.
(3) This paragraph provides credit for the
modifications specified in paragraph (w)(2)
of this AD, if those modifications were
performed before the effective date of this AD
using Airbus Mandatory Service Bulletin
A320–32–1336, dated September 19, 2007.
(4) This paragraph provides credit for the
modifications required by paragraph (w)(3) of
this AD, if those modifications were
performed before the effective date of this AD
using Airbus Service Bulletin A320–32–1369,
dated March 22, 2009.
(bb) 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:
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: 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. AMOCs approved previously in
accordance with AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
September 6, 2007), are not approved as
AMOCs with 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
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
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.
(cc) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2011–0201, dated October 13, 2011,
and the service information service
information identified in paragraphs (cc)(1)(i)
through (cc)(1)(viii) for related information.
(i) Airbus A318/A319/A320/A321, Task
12–12–32–610–001–A Check NLG Shock
Absorber Fluid Level and Charge Pressure
(‘‘Two-Point Check’’—Aircraft on Jacks to
start), Revision August 1, 2012.
(ii) Airbus Mandatory Service Bulletin
A320–32–1310, Revision 01, dated June 23,
2011.
(iii) Airbus Mandatory Service Bulletin
A320–32–1336, Revision 01, dated January
10, 2008.
(iv) Airbus Service Bulletin A320–32–
1350, dated July 31, 2008.
(v) Airbus Service Bulletin A320–32–1360,
dated March 18, 2009.
(vi) Airbus Service Bulletin A320–32–
1369, Revision 01, dated March 31, 2010.
(vii) Airbus Service Bulletin A320–32–
1387, dated April 7, 2011.
(viii) Airbus Technical Note 957.1901/05,
dated October 18, 2005.
(2) For service information identified in
this 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.
Issued in Renton, Washington, on January
31, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–02898 Filed 2–7–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0090; Directorate
Identifier 2012–NM–149–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
SUMMARY:
E:\FR\FM\08FEP1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 27 (Friday, February 8, 2013)]
[Proposed Rules]
[Pages 9341-9346]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-02898]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0088; Directorate Identifier 2011-NM-233-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all Airbus Model A318, A319, A320, and A321 series
airplanes. The existing AD currently requires repetitive inspections of
the upper support of the nose landing gear (NLG), and related
investigative and corrective actions if necessary; and also provides an
optional terminating action for the repetitive inspections. Since we
issued that AD, we have determined that previously allowed terminating
actions no longer address the unsafe condition and that a new
terminating action is necessary. This proposed AD would require
installing a new enhanced manufacturing and maintainability (EMM)
braking and steering control unit (BSCU) standard and adds airplanes to
[[Page 9342]]
the applicability. We are proposing this AD to prevent landings with
the NLG turned 90 degrees from centerline, which could result in
reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by March 25, 2013.
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-2013-0088;
Directorate Identifier 2011-NM-233-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
On August 17, 2007, we issued AD 2007-18-09, Amendment 39-15189 (72
FR 51164, September 6, 2007), which superseded AD 2005-24-06, Amendment
39-14386 (70 FR 70715, November 23, 2005). That AD required actions
intended to address an unsafe condition on the products listed above.
Since we issued AD 2007-18-09, Amendment 39-15189 (72 FR 51164,
September 6, 2007), The European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2011-0201, dated October 13,
2011 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
In 2005, an A320 aeroplane experienced a landing with the Nose
Landing Gear (NLG) wheels rotated at 90 degrees to the aeroplane
centreline.
Investigation showed that the upper support of the NLG shock
absorber was damaged and the anti-rotation lugs were ruptured. This
caused the nose wheels to lose their centred position reference. The
affected Braking and Steering Control Unit (BSCU) had logged a
steering system fault because hydraulic power was not available at
the time of steering system checks, therefore the BSCU was not able
to proceed with the re-centring of the wheels. Failure to centre the
NLG wheels correctly may result in a failure of the NLG to retract.
To prevent further landing incidents with NLG wheels rotated at
90 degrees, DGAC France issued AD F-2005-191 [which corresponds to
FAA AD 2005-24-06, Amendment 39-14386 (70 FR 70715, November 23,
2005)] to require the implementation of an operational procedure and
the accomplishment of certain maintenance actions.
EASA AD 2006-0174, [which corresponds to FAA AD 2007-18-09,
Amendment 39-15189 (72 FR 51164, September 6, 2007)] which
superseded AD F-2005-191, was issued to extend the applicability and
to introduce repetitive boroscope inspections of the NLG upper
support lugs and cylinder lugs which have been driven by EMM BSCU
L4.1 (Part Number (P/N) E21327001) or L4.5 (P/N E21327003) and,
corrective actions, depending on findings.
Since that AD was issued, Airbus has demonstrated the
acceptability of installing EMM BSCU L4.9B (P/N E21327006 or P/N
E21327106) or conventional BSCU std 10 (P/N C202163392E34) or
conventional BSCU std 10.1 (P/N C202163392E35) as terminating action
for the actions required by EASA AD 2006-0174, for aeroplanes fitted
with twin wheel Main Landing Gear (MLG) units.
For the reasons described above, this AD retains some of the
requirements of EASA AD 2006-0174, which is superseded, extends the
applicability to all A318, A319, A320 and A321 aeroplanes, requires
the installation of BSCU L4.9B, or BSCU std 10, or BSCU std 10.1 for
in service aeroplanes fitted with twin wheel MLG, which constitutes
terminating action for the repetitive inspections and checks
required by this AD.
Installation of a NLG with new upper support anti-rotation lugs
and new cylinders lugs, or installation of a NLG for which it can be
demonstrated that it was never driven by EMM BSCU L4.1 or L4.5, is
no longer considered as terminating action for the requirements of
this AD.
The unsafe condition is the NLG turning 90 degrees from centerline,
which could result in reduced controllability of the airplane. You may
obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service bulletins.
Airbus Mandatory Service Bulletin A320-32-1310, Revision
01, dated June 23, 2011.
Airbus Mandatory Service Bulletin A320-32-1336, Revision
01, dated January 10, 2008.
Airbus Service Bulletins A320-32-1350, dated July 31,
2008.
Airbus Service Bulletin A320-32-1360, dated March 18,
2009.
Airbus Service Bulletin A320-32-1369, Revision 01, dated
March 31, 2010.
Airbus Service Bulletin A320-32-1387, dated April 7, 2011.
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
[[Page 9343]]
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.
Differences Between This AD and the MCAI or Service Information
Airbus Mandatory Service Bulletin A320-32-1310, Revision 01, dated
June 23, 2011, specifies to use Airbus recommendations when restoring
the NLG, but this proposed AD would require restoring the NLG 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).
The MCAI permits accomplishment of MCAI paragraph 1.1 by inserting
a copy of certain Airbus airplane flight manual (AFM) temporary
revisions into the AFM. We have not included that provision in this
proposed AD, since the temporary revisions have already been
incorporated into the AFM.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 755 products of U.S. registry.
The actions that are required by FAA AD 2007-18-09, Amendment 39-
15189 (72 FR 51164, September 6, 2007), and retained in this proposed
AD take about 3 work-hours per product, at an average labor rate of $85
per work hour. Based on these figures, the estimated cost of the
currently required actions is $255 per product.
We estimate that it would take about 35 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. 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, we estimate the
cost of the proposed AD on U.S. operators to be $2,246,125, or $2,975
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. We have no way of determining the number of products that may need
these actions.
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007), and
adding the following new AD:
Airbus: Docket No. FAA-2013-0088; Directorate Identifier 2011-NM-
233-AD.
(a) Comments Due Date
We must receive comments by March 25, 2013.
(b) Affected ADs
This AD supersedes AD 2007-18-09, Amendment 39-15189 (72 FR
51164, September 6, 2007).
(c) Applicability
This AD applies to the Airbus airplanes listed in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any
category; all serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-111, -211, -212, -214, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by a report of an airplane landing with the
nose landing gear (NLG) turned 90 degrees from centerline, and from
additional reports of upper support anti-rotation lugs of the NLG
rupturing in service. We are issuing this AD to prevent landings
with the NLG turned 90 degrees from centerline, which could result
in reduced controllability of the airplane.
(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 Records Review
This paragraph restates the requirements of paragraph (f) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007).
Within 5 days after November 30, 2005 (the effective date of AD
2005-24-06, Amendment 39-14386 (70 FR 70715, November 23, 2005)),
perform a records review to determine whether the airplane is
equipped with or has ever been equipped with an enhanced
manufacturing and maintainability (EMM) braking and steering control
unit (BSCU) part number (P/N) E21327001 (standard L4.1, installed by
Airbus Modification 26965, or Airbus Service Bulletin A320-32-1912)
or P/N E21327003 (standard L4.5, installed by Airbus Modification
33376, or Airbus Service Bulletin A320-32-1261). Airbus Service
Bulletin A320-32-1310, dated February 8, 2006, is one approved
method for doing the records review.
[[Page 9344]]
(h) Retained Statement of No Further Action Required
This paragraph restates the requirements of paragraph (g) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007). For
airplanes on which a records review required by paragraph (g) of
this AD conclusively determines that the airplane is not and never
has been equipped with a BSCU P/N E21327001 or P/N E21327003, no
further action is required by paragraphs (i), (j), (k), (l), and (m)
of this AD.
(i) Retained Airplane Flight Manual (AFM) Revision
This paragraph restates the requirements of paragraph (h) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007). For
airplanes that are not specified in paragraph (h) of this AD and on
which Airbus Modification 31152 has not been incorporated in
production (i.e., applicable only to aircraft with steering powered
by the green hydraulic system): Within 10 days after November 30,
2005 (the effective date of AD 2005-24-06, Amendment 39-14386 (70 FR
70715, November 23, 2005)), revise the Limitation Section of the
Airbus A318/319/320/321 Aircraft Flight Manual (AFM) to include the
following information. This may be done by inserting a copy of this
AD into the AFM:
The ECAM message, in case of a nose wheel steering failure, will
be worded as follows:
--``WHEEL N/W STRG FAULT'' for aircraft with the FWC E3 and
subsequent standards
--``WHEEL N.W. STEER FAULT'' for aircraft with the FWC E2 Standard.
[dec221] If the L/G SHOCK ABSORBER FAULT ECAM caution is
triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM
caution is triggered after the landing gear extension:
When all landing gear doors are indicated closed on ECAM WHEEL
page, reset the BSCU:
--A/SKID&N/W STRG----------------------------OFF THEN ON
If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed,
this indicates a successful nose wheel re-centering and steering
recovery.
--Rearm the AUTO BRAKE, if necessary.
If the WHEEL N/W STRG FAULT ECAM caution remains displayed, this
indicates that the nose wheel steering remains lost, and that the
nose wheels are not centered.
--During landing, delay nose wheel touchdown for as long as
possible.
--Refer to the ECAM STATUS.
[dec221] If the WHEEL N/W STRG FAULT ECAM caution appears,
without the L/G SHOCK ABSORBER FAULT ECAM caution:
--No specific crew action is requested by the WHEEL N/W STRG FAULT
ECAM caution procedure.
--Refer to the ECAM STATUS.
Accomplishment of the actions required by paragraph (r) of this
AD terminates the requirements of this paragraph, and the AFM
limitation required by this paragraph must be removed.
Note 1 to paragraph (i) of this AD: When a statement identical
to that in paragraph (i) of this AD has been included in the general
revisions of the AFM, the general revisions may be inserted into the
AFM, and the copy of this AD or AD 2007-18-09, Amendment 39-15189
(72 FR 51164, September 6, 2007), may be removed from the AFM.
(j) Retained Inspection Thresholds
This paragraph restates the requirements of paragraph (i) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007). For
airplanes that are not specified in paragraph (h) of this AD, at the
earlier of the times specified in paragraphs (j)(1) and (j)(2) of
this AD: Do a special detailed inspection (boroscopic) for broken or
cracked NLG upper support lugs and missing cylinder lugs, and do all
applicable related investigative/corrective actions before further
flight. Do all actions in accordance with Airbus Technical Note
957.1901/05, dated October 18, 2005; or the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1310, dated February
8, 2006. After October 11, 2007 (the effective date of AD 2007-18-
09), only Airbus Service Bulletin A320-32-1310, dated February 8,
2006, may be used. Where Airbus Service Bulletin A320-32-1310, dated
February 8, 2006, specifies that restoring the NLG is necessary in
accordance with Airbus recommendations, this AD requires restoring
the NLG 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 the applicable interval
specified in paragraph (k) or (l) of this AD until the inspection
required by paragraph (t) of this AD is accomplished.
(1) Within 100 flight cycles following an electronic centralized
aircraft monitoring (ECAM) caution ``L/G SHOCK ABSORBER FAULT''
associated with at least one of the following centralized fault
display system (CFDS) messages specified in paragraph (j)(1)(i),
(j)(1)(ii), or (j)(1)(iii) of this AD. As of the effective date of
this AD, for the conditions specified in paragraph (j)(1) of this
AD, do the actions required by paragraph (r) of this AD.
(i) ``N L/G EXT PROX SNSR 24GA TGT POS.''
(ii) ``N L/G EXT PROX SNSR 25GA TGT POS.''
(iii) ``N L/G SHOCK ABSORBER FAULT 2526GM.''
(2) At the later of the times specified in paragraphs (j)(2)(i)
and (j)(2)(ii) of this AD.
(i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles
since the date of issuance of the original French standard
airworthiness certificate, or the original French export certificate
of airworthiness, whichever occurs first.
(ii) Within 6 months, 1,800 flight hours, or 1,350 flight cycles
after October 11, 2007 (the effective date of AD 2007-18-09,
Amendment 39-15189 (72 FR 51164, September 6, 2007)), whichever
occurs first.
(k) Retained Repetitive Inspection Intervals for BSCU Standard L4.1 or
L4.5
This paragraph restates the requirements of paragraph (j) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007). For
airplanes not specified in paragraph (h) of this AD that are
equipped with EMM BSCU standard L4.1 or L4.5: Repeat the inspection
specified in paragraph (j) of this AD thereafter at intervals not to
exceed the earliest of 6 months; 1,800 flight hours; 1,350 flight
cycles; or 100 flight cycles following certain ECAM cautions and
CFDS messages, as specified in paragraph (j)(1) of this AD.
(l) Retained Repetitive Inspection Intervals for BSCU Standard L4.8 or
Non-EMM BSCU
This paragraph restates the requirements of paragraph (k) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007). For
airplanes not specified in paragraph (h) of this AD that are
equipped with EMM BSCU standard L4.8 or a non-EMM BSCU: Repeat the
inspection specified in paragraph (j) of this AD thereafter at
intervals not to exceed the earliest of 20 months; 6,000 flight
hours; 4,500 flight cycles; or 100 flight cycles following certain
ECAM cautions and CFDS messages, as specified in paragraph (j)(1) of
this AD.
(m) Retained Optional Terminating Action With Limiting Date Restriction
This paragraph restates the requirements of paragraph (l) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007) with
a limiting date restriction. For airplanes that are not specified in
paragraph (h) of this AD: Installation of an NLG with new upper
support anti-rotation lugs and new cylinder lugs, or installation of
an NLG that was never driven by EMM BSCU standard L4.1 or L4.5;
combined with installation of EMM BSCU standard L4.8 or a non-EMM
BSCU; before the effective date of this AD; constitutes terminating
action for the requirements of paragraphs (g), (h), (i), (j), (k),
and (l) of this AD. Do the installations in accordance with a method
approved by either the Manager, International Branch, ANM-116; or
the EASA (or its delegated agent). Chapter 32 of the Airbus A318/
A319/A320/A321 Aircraft Maintenance Manual (AMM) is one approved
method for doing the installations before the effective date of this
AD.
(n) Retained Statement of No Reporting Required
This paragraph restates the requirements of paragraph (m) of AD
2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007).
Although Airbus Service Bulletin A320-32-1310, dated February 8,
2006, specifies sending certain inspection results to Airbus, this
AD does not include that requirement.
(o) Part Number Identification
For the purpose of this AD, the following part numbers are
identified.
(1) P/N E21327001: installed by Airbus Modification 26965 or by
Airbus Service Bulletin A320-32-1912 in service: EMM BSCU L4.1.
(2) P/N E21327003: installed by Airbus Modification 33376 or
Airbus Service
[[Page 9345]]
Bulletin A320-32-1261 in service: EMM BSCU L4.5.
(3) P/N E21327004: installed by Airbus modification 35216 or
Airbus Service Bulletin A320-32-1305 or Airbus Service Bulletin
A320-32-1343/AOT A320-32A1343 in service: EMM BSCU L4.8.
(4) P/N E213270B1: installed by Airbus modification 31931 or
Airbus Service Bulletin A320-32-1206: EMM BSCU L5-2.
(5) P/N E21327006: installed by Airbus modification 38973 or
Airbus Service Bulletin A320-32-1350 or Airbus Service Bulletin
A320-32-1361: EMM BSCU L4.9B.
(6) P/N E21327106: installed by Airbus modification 151575 or
Airbus Service Bulletin A320-32-1387: EMM BSCU L4.9B.
(7) P/N C202163392E34: installed by Airbus Service Bulletin
A320-32-1336 or Airbus Service Bulletin A320-32-1360: conventional
BSCU standard (std) 10.
(8) P/N C202163392E35: installed by Airbus Service Bulletin
A320-32-1369: conventional BSCU std 10.1.
(p) Records Review
Within 5 days after the effective date of this AD: Perform a
records review to determine whether the airplane is equipped with or
has ever been equipped with an EMM BSCU having P/N E21327001
(standard L4.1, installed by Airbus modification 26965, or Airbus
Service Bulletin A320-32-1912) or P/N E21327003 (standard L4.5,
installed by Airbus modification 33376, or Airbus Service Bulletin
A320-32-1261), or P/N E21327004 (standard L4.8, installed by Airbus
modification 35216, or Airbus Service Bulletin A320-32-1305, or
Airbus Service Bulletin A320-32-1343/AOT A320-32A1343), or P/N
E213270B1 (standard L5-2, installed by Airbus modification 31931, or
Airbus Service Bulletin A320-32-1206).
Note 2 to paragraph (p) of this AD: Accomplishment of the
actions specified in Airbus Mandatory Service Bulletin A320-32-1310,
Revision 01, dated June 23, 2011, before the effective date of this
AD, provides a method for doing the records review.
(q) No Further Action Required for Certain Paragraphs
For airplanes on which a records review required by paragraph
(p) of this AD conclusively determines that the airplane is not and
never has been equipped with an EMM BSCU having P/N E21327001, or P/
N E21327003, or P/N E21327004, or P/N E213270B1, no further action
is required by paragraphs (r) and (s) of this AD.
(r) Airplane Flight Manual Revision
For airplanes that are not identified in paragraph (q) of this
AD and on which Airbus Modification 31152 has not been incorporated
in production (i.e., applicable only to aircraft with steering
powered by the green hydraulic system): Within 10 days after the
effective date of this AD, revise the Limitation Section of the
Airbus A318/319/320/321 AFM to include the following information.
This revision may be done by inserting a copy of this AD into the
AFM.
The ECAM message, in case of a nose wheel steering failure, will
be worded as follows:
--``WHEEL N/W STRG FAULT'' for airplanes with Flight Warning
Computer (FWC) software post E3P.
--``WHEEL N.W. STEER FAULT'' for airplanes with FWC software pre
E3P.
[dec221] If the L/G SHOCK ABSORBER FAULT ECAM caution is
triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM
caution is triggered after the landing gear extension:
When all landing gear doors are indicated closed on
ECAM WHEEL page, reset the BSCU:
--A/SKID&N/W STRG----------------------------OFF THEN ON
If the WHEEL N/W STRG FAULT ECAM caution is no longer
displayed, this indicates a successful nose wheel re-centering and
steering recovery.
--Rearm the AUTO BRAKE, if necessary.
If the WHEEL N/W STRG FAULT ECAM caution remains
displayed, this indicates that the nose wheel steering remains lost,
and that the nose wheels are not centered.
--During landing, delay nose wheel touchdown for as long as
possible.
--Refer to the ECAM STATUS.
[dec221] If the WHEEL N/W STRG FAULT ECAM caution appears,
without the L/G SHOCK ABSORBER FAULT ECAM caution:
--No specific crew action is requested by the WHEEL N/W STRG FAULT
ECAM caution procedure.
--Refer to the ECAM STATUS.
Note: For airplanes fitted with pre FWC E3P standard, read N.W
STEER instead of N/W STRG.
Accomplishment of the actions required by this paragraph terminates
the requirements of paragraph (i) of this AD and the AFM revision
required by paragraph (i) of this AD must be removed.
Note 3 to paragraph (r) of this AD: When a statement identical
to that in paragraph (r) of this AD has been included in the general
revisions of the AFM, the general revisions may be inserted into the
AFM, and the copy of this AD may be removed from the AFM.
(s) Inspection Following Certain Centralized Fault Display System
Messages
(1) For airplanes other than those identified in paragraph (q)
of this AD: Within 100 flight cycles following an ECAM caution ``L/G
SHOCK ABSORBER FAULT'' associated with at least one of the following
CFDS messages specified in paragraph (s)(1)(i), (s)(1)(ii), or
(s)(1)(iii) of this AD, do the actions in paragraph (s)(2) of this
AD.
(i) ``N L/G EXT PROX SNSR 24GA TGT POS.''
(ii) ``N L/G EXT PROX SNSR 25GA TGT POS.''
(iii) ``N L/G SHOCK ABSORBER FAULT 2526GM.''
(2) For airplanes identified in paragraph (s)(1) of this AD: Do
the actions specified in paragraphs (s)(2)(i) and (s)(2)(ii) of this
AD.
(i) Check the NLG strut inflation pressure, weight-off- and
weight-on-wheels, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A320-32-1310, Revision 01,
dated June 23, 2011, and before further flight, do all applicable
corrective actions and adjustments, in accordance with Airbus A318/
A319/A320/A321, Task 12-12-32-610-001-A Check NLG Shock Absorber
Fluid Level and Charge Pressure (``Two-Point Check''--Aircraft on
Jacks to start), Revision August 1, 2012.
(ii) Do a boroscopic inspection for broken or cracked NLG upper
support lugs and missing or cracked cylinder lugs, and do all
applicable related investigative and corrective actions before
further flight. Do all actions in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-32-1310,
Revision 01, dated June 23, 2011. Where Airbus Mandatory Service
Bulletin A320-32-1310, Revision 01, dated June 23, 2011, specifies
restoring the NLG in accordance with Airbus recommendations, this AD
requires restoring the NLG before further flight, in accordance with
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the EASA (or its delegated
agent).
(t) Initial Boroscopic Inspection
At the applicable times specified in paragraphs (t)(1) and
(t)(2) of this AD: Do a boroscopic inspection for broken or cracked
NLG upper support lugs and missing or cracked cylinder lugs, and do
all applicable related investigative and corrective actions before
further flight. Do all actions in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-32-1310,
Revision 01, dated June 23, 2011. Where Airbus Mandatory Service
Bulletins A320-32-1310, Revision 01, dated June 23, 2011, specifies
restoring the NLG in accordance with Airbus recommendations, this AD
requires restoring the NLG before further flight, in accordance with
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the EASA (or its delegated
agent). Accomplishment of the actions required by this paragraph
terminate the requirements of paragraphs (j), (k), and (l) of this
AD.
(1) For airplanes fitted with twin wheel main landing gear (MLG)
that have been equipped with EMM BSCU standard L4.1, L4.5, or L4.8:
At the later of the times specified in paragraphs (t)(1)(i) and
(t)(1)(ii) of this AD.
(i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles
since first flight of the airplane, whichever occurs first.
(ii) Within 6 months, or 1,800 flight hours, or 1,350 flight
cycles after the effective date of this AD, whichever occurs first.
(2) For airplanes fitted with bogie MLG: At the later of the
times specified in paragraphs (t)(2)(i) and (t)(2)(ii) of this AD.
(i) Within 20 months, or 6,000 flight hours, or 4,500 flight
cycles after the installation of EMM BSCU standard L5-2, whichever
occurs first.
(ii) Within 6 months, or 1,800 flight hours, or 1,350 flight
cycles after the effective date of this AD, whichever occurs first.
(u) Repetitive Boroscopic Inspections
After accomplishing the inspection specified in paragraph (t) of
this AD: Repeat
[[Page 9346]]
the inspection required by paragraph (t) of this AD thereafter at
the applicable interval specified in paragraphs (u)(1), (u)(2), and
(u)(3) of this AD.
(1) For airplanes fitted with twin wheel MLG that have been
equipped with EMM BSCU standard L4.8: At intervals not to exceed 20
months, or 6,000 flight hours, or 4,500 flight cycles, whichever
occurs first.
(2) For airplanes fitted with twin wheel MLG that have been
equipped with EMM BSCU standard L4.1 or L4.5: At intervals not to
exceed 6 months, or 1,800 flight hours, or 1,350 flight cycles,
whichever occurs first.
(3) For airplanes fitted with bogie MLG: At intervals not to
exceed 20 months, or 6,000 flight hours, or 4,500 flight cycles,
whichever occurs first.
(v) Modification
For airplanes fitted with twin wheel MLG: Within 6 months after
the effective date of this AD, modify the airplane by installing EMM
BSCU standard L4.9B, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1350, dated July 3,
2008.
(w) Optional Method of Modification
Doing a modification specified in paragraph (w)(1), (w)(2), or
(w)(3) of this AD, is acceptable for compliance with the
requirements of paragraph (v) of this AD.
(1) Modification of the airplane by installing EMM BSCU standard
L4.9B, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1387, dated April 7, 2011.
(2) Modification of the airplane by installing conventional EMM
BSCU standard 10, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-32-1360, dated March 18, 2009; or
Airbus Mandatory Service Bulletin A320-32-1336, Revision 01, dated
January 10, 2008.
(3) Modification of the airplane by installing conventional EMM
BSCU standard 10.1 in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1369, Revision 01,
dated March 31, 2010.
(x) Terminating Action
In-service modification of an airplane fitted with twin wheel
MLG as required by paragraph (v) of this AD constitutes terminating
action for the initial and repetitive inspections required by
paragraph (t) of this AD. In addition, the AFM changes required by
paragraph (r) of this AD may be removed from the AFM; and the
requirements of paragraph (s) of this AD are no longer required.
(y) Exemption From Certain Actions
Except for paragraph (y) of this AD, airplanes that have been
delivered with Airbus modification 38973 and/or Airbus modification
151575 that install EMM BSCU standard L4.9B are not affected by the
requirements of this AD, provided that no installation of previous
EMM BSCU standards L4.1, L4.5, or L4.8 has been performed since the
airplane first flight.
(z) Parts Installation
For airplanes that do not have EMM BSCU L4.1, or EMM BSCU L4.5,
or EMM BSCU L4.8 installed: As of the effective date of this AD, no
person may modify an airplane by installing EMM BSCU standards L4.1,
L4.5, or L4.8 on any airplane.
(aa) Credit for Previous Actions
(1) This paragraph restates the requirements of paragraph (n) of
AD 2007-18-09, Amendment 39-15189 (72 FR 51164, September 6, 2007).
This paragraph provides credit for the inspections required by
paragraph (j) of this AD, if those inspections were performed before
October 11, 2007 (the effective date of AD 2007-18-09, Amendment 39-
15189 (72 FR 51164, September 6, 2007)) using Chapter 12, Subject
12-14-32 of the Airbus A318/A319/A320/A321 AMM, as revised by Airbus
A318/A319/A320/A321 AMM Temporary Revision 12-001, dated November
13, 2005.
(2) This paragraph provides credit for the inspections and
related investigative/corrective actions required by paragraphs (j),
(k), and (l) of this AD, if those inspections were performed before
the effective date of this AD using Airbus Service Bulletin A320-32-
1310, dated February 8, 2006.
(3) This paragraph provides credit for the modifications
specified in paragraph (w)(2) of this AD, if those modifications
were performed before the effective date of this AD using Airbus
Mandatory Service Bulletin A320-32-1336, dated September 19, 2007.
(4) This paragraph provides credit for the modifications
required by paragraph (w)(3) of this AD, if those modifications were
performed before the effective date of this AD using Airbus Service
Bulletin A320-32-1369, dated March 22, 2009.
(bb) 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: 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 2007-18-09, Amendment 39-
15189 (72 FR 51164, September 6, 2007), are not approved as AMOCs
with 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.
(cc) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0201, dated
October 13, 2011, and the service information service information
identified in paragraphs (cc)(1)(i) through (cc)(1)(viii) for
related information.
(i) Airbus A318/A319/A320/A321, Task 12-12-32-610-001-A Check
NLG Shock Absorber Fluid Level and Charge Pressure (``Two-Point
Check''--Aircraft on Jacks to start), Revision August 1, 2012.
(ii) Airbus Mandatory Service Bulletin A320-32-1310, Revision
01, dated June 23, 2011.
(iii) Airbus Mandatory Service Bulletin A320-32-1336, Revision
01, dated January 10, 2008.
(iv) Airbus Service Bulletin A320-32-1350, dated July 31, 2008.
(v) Airbus Service Bulletin A320-32-1360, dated March 18, 2009.
(vi) Airbus Service Bulletin A320-32-1369, Revision 01, dated
March 31, 2010.
(vii) Airbus Service Bulletin A320-32-1387, dated April 7, 2011.
(viii) Airbus Technical Note 957.1901/05, dated October 18,
2005.
(2) For service information identified in this 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.
Issued in Renton, Washington, on January 31, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-02898 Filed 2-7-13; 8:45 am]
BILLING CODE 4910-13-P
