[Federal Register Volume 78, Number 27 (Friday, February 8, 2013)]
[Proposed Rules]
[Pages 9341-9346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-02898]


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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).

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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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, 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 [email protected]; Internet http://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 http://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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On 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: [email protected]. 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 [email protected]; Internet http://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