Document ID: FAA-2013-0088-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2014-09-12T04:00Z

[Federal Register Volume 79, Number 177 (Friday, September 12, 2014)]
[Rules and Regulations]
[Pages 54579-54588]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-21552]

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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; 
Amendment 39-17703; AD 2013-25-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2007-18-09 for 
all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-
18-09 required repetitive inspections of the upper support of the nose 
landing gear (NLG), and related investigative and corrective actions if 
necessary; and also provided an optional terminating action for the

[[Page 54580]]

repetitive inspections. This new AD adds installation of a new enhanced 
manufacturing and maintainability (EMM) braking and steering control 
unit (BSCU) standard, and adds airplanes to the applicability. This AD 
was prompted by a determination that previously allowed terminating 
actions no longer address the unsafe condition and that a new 
terminating action is necessary. 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.

DATES: This AD becomes effective October 17, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 17, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 11, 2007 (72 FR 51164, September 6, 2007).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 30, 2005 (70 FR 70715, November 23, 2005).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0088; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.
    For service information identified in this AD, contact Airbus, 
Airworthiness Office--EIAS, 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 http://www.airbus.com. You may view this 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.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede 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). AD 2007-18-09 applied to all Airbus 
Model A318, A319, A320, and A321 series airplanes. The NPRM published 
in the Federal Register on February 8, 2013 (78 FR 9341). The NPRM was 
prompted by a determination that previously allowed terminating actions 
no longer address the identified unsafe condition and that a new 
terminating action is necessary. The NPRM proposed to continue to 
require repetitive inspections of the upper support of the NLG, and 
related investigative and corrective actions if necessary; and also 
provided a new optional terminating action for the repetitive 
inspections. The NPRM also proposed to install a new EMM BSCU standard, 
and add airplanes to the applicability. 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.
    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 Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. 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, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
DGAC France issued AD F-2005-191 [(http://ad.easa.europa.eu/blob/
easaad20056411F20051910tb
superseded.pdf/ADF-2005-1911) 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, [(http://ad.easa.europa.eu/blob/
easaad20060174superseded.pdf/
AD2006-01742) 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 [EASA] 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 [EASA] 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 [EASA] 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 [EASA] AD.

The unsafe condition is the NLG turning 90 degrees from centerline, 
which could result in reduced controllability of the airplane. You may 
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0088-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received.

Support for the NPRM (78 FR 9341, February 8, 2013)

    United Airlines (UAL) stated that it concurs with the FAA's 
assertion that terminating action should consist of BSCU standard 
L4.9B, standard 10, or standard 10.1, rather than standard L4.1 or 
L4.5.

Statement of Compliance With the NPRM (78 FR 9341, February 8, 2013)

    UAL stated that it is currently in the process of upgrading its 
BSCU to the enhanced EMM version specified in the NPRM (78 FR 9341, 
February 8, 2013) and is 81 percent complete.

Request for Alternative Actions

    UAL stated that the NPRM (78 FR 9341, February 8, 2013) mandates 
accomplishment of the BSCU replacement within 6 months after the

[[Page 54581]]

effective date of the AD, and that it is concerned the vendor may not 
be able to support this relatively short deadline with sufficient 
numbers of enhanced BSCUs. UAL asserted that a more feasible solution 
with an acceptable level of safety would be:
     Continue repetitive inspections of the upper support of 
the nose landing gear (NLG) until replacement with the EMM BSCU.
     Continue repetitive inspections of the NLG for airplanes 
on which the terminating action per AD 2007-18-09, Amendment 39-15189 
(72 FR 51164, September 6, 2007)--standard L4.1, L4.5, or L5-2 was done 
previously.
     Upgrade to the standard L4.9B, standard 10, or standard 
10.1, could then be accomplished on attrition, as units are available 
from the BSCU manufacturer.
    We disagree with the commenter's request. The compliance time for 
modification of EMM BSCU standard L4.9B was determined after conducting 
a risk assessment and determining the effect of associated risk on the 
worldwide fleet. We have determined that for twin wheel MLG, the 
repetitive inspection of the NLG upper support lugs and missing 
cylinder cannot be relied upon indefinitely until replacement with EMM 
BSCU standard L4.9B or applicable alternatives specified in paragraph 
(w) of this AD by attrition. Modification is not required by paragraph 
(v) of this AD for airplanes installed with bogie MLG. Only airplanes 
fitted with twin wheel MLG must do the modification within 6 months.
    The compliance time was also established taking into consideration 
availability of parts. Operators have multiple options to install EMM 
BSCU standards in accordance with paragraph (w) of this AD. However, 
according to the provisions of paragraph (bb)(1) of this AD, we might 
approve requests to adjust the compliance time or allow alternative 
actions if the requests include substantiation that the new compliance 
time or alternative actions would provide an acceptable level of 
safety. We have not changed this final rule in this regard.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the EASA, or Airbus's EASA Design Organization Approval 
(DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this AD.

Additional Changes Made to This Final Rule

    We have removed Note 1 to paragraph (i) of the proposed AD (78 FR 
9341, February 8, 2013) and included that information in paragraph (i) 
of this AD. This change does not affect the intent of paragraph (i) of 
this AD.
    We have also revised paragraph (m) of this AD to remove a reference 
to Chapter 32 of the Airbus A318/A319/A320/A321 Aircraft Maintenance 
Manual (AMM). As of the effective date of this AD, operators must 
contact the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA; as specified in 
paragraph (bb)(1) of this AD for approval to use this document. We also 
added a new Note 1 to paragraph (m) of this AD, which specifies that 
guidance for doing the installation required by paragraph (m) of this 
AD may be found in Chapter 32 of the Airbus A318/A319/A320/A321 AMM.
    In addition, we have clarified paragraph (o) of this AD to indicate 
which part numbers correspond to which EMM units.
    We removed Note 2 to paragraph (p) of the proposed AD (78 FR 9341, 
February 8, 2013) and included that information in new paragraph 
(aa)(3) of this AD. We have redesignated subsequent paragraphs 
accordingly. This change does not affect the intent of paragraph (p) of 
this AD.
    We removed Note 3 to paragraph (r) of the proposed AD (78 FR 9341, 
February 8, 2013) and included that information in paragraph (r) of 
this AD. This change does not affect the intent of paragraph (r) of 
this AD.
    Also, we revised paragraph (x) of the proposed AD (78 FR 9341, 
February 8, 2013) to indicate that accomplishing a modification 
specified in paragraph (w) of this AD is also a terminating action for 
the inspections required by paragraph (t) of this AD.
    Paragraph (y) of the proposed AD (78 FR 9341, February 8, 2013) 
included a typographical error in the exception phrase. We have revised 
this AD to clarify the exception by specifying ``Except for the 
prohibition specified in paragraph (z) of this AD. . . .''

[[Page 54582]]

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 9341, February 8, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 9341, February 8, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects about 755 products of U.S. 
registry.
    The actions that are retained from AD 2007-18-09, Amendment 39-
15189 (72 FR 51164, September 6, 2007), 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 actions that were required by AD 
2007-18-09 is $255 per product.
    We estimate that it will take 35 work-hours per product to comply 
with the new basic requirements of this 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 this AD 
to the 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 AD. We 
have no way of determining the number of products that might 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0088; 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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The 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:

2013-25-07 Airbus: Amendment 39-17703. Docket No. FAA-2013-0088; 
Directorate Identifier 2011-NM-233-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective October 17, 
2014.

(b) Affected ADs

    This AD replaces 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

    Comply with this AD within the compliance times specified, 
unless already 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) having 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 54583]]

(h) Retained Statement of No Further Action Required After Records 
Review

    This paragraph restates a provision from 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 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 AFM to include the following information. 
This may be done by inserting a copy of figure 1 to paragraph (i) of 
this AD into the AFM. 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. When a statement identical to that in figure 1 to 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 figure 1 to paragraph (i) of this AD or AD 2007-18-09, 
Amendment 39-15189 (72 FR 51164, September 6, 2007), may be removed 
from the AFM.
BILLING CODE 4910-13-P

[[Page 54584]]

[GRAPHIC] [TIFF OMITTED] TR12SE14.006

BILLING CODE 4910-13-C

(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), 
with specific delegation approval language. 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,

[[Page 54585]]

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 Airbus's EASA Design 
Organization Approval (DOA). 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 ECAM caution L/G SHOCK 
ABSORBER FAULT associated with at least one of the following 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 and specific delegation approval 
language. 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 the Manager, 
International Branch, ANM-116; or EASA; or Airbus's EASA DOA.

    Note 1 to paragraph (m) of this AD: Guidance for doing the 
installation required by paragraph (m) of this AD may be found in 
Chapter 32 of the Airbus A318/A319/A320/A321 Airplane Maintenance 
Manual.

(n) Retained Statement of No Reporting Requirement

    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) New 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 stands for EMM BSCU 
L4.1.
    (2) P/N E21327003 installed by Airbus Modification 33376 or 
Airbus Service Bulletin A320-32-1261 in service stands for 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 stands for EMM BSCU L4.8.
    (4) P/N E213270B1 installed by Airbus Modification 31931 or 
Airbus Service Bulletin A320-32-1206 stands for 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 stands for EMM BSCU L4.9B.
    (6) P/N E21327106 installed by Airbus Modification 151575 or 
Airbus Service Bulletin A320-32-1387 stands for EMM BSCU L4.9B.
    (7) P/N C202163392E34 installed by Airbus Service Bulletin A320-
32-1336 or Airbus Service Bulletin A320-32-1360 stands for 
conventional BSCU standard 10.
    (8) P/N C202163392E35 installed by Airbus Service Bulletin A320-
32-1369 stands for conventional BSCU standard 10.1.

(p) New 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).

(q) New Statement of No Further Action Required After Records Review

    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, P/N 
E21327003, P/N E21327004, or P/N E213270B1, no further action is 
required by paragraphs (r) and (s) of this AD.

(r) New AFM 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 figure 2 to 
paragraph (r) of this AD into the AFM. 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. When a statement identical to that in 
figure 2 to 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 figure 2 to paragraph (r) of this AD 
may be removed from the AFM.
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(s) New 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 specified 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-wheels, 
and weight-on-wheels, in accordance with the Accomplishment 
Instructions of Airbus 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 Airplane Maintenance Manual Task 12-12-32-610-001-A, 
Check NLG Shock Absorber Fluid Level and Charge Pressure

[[Page 54587]]

(``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 Service Bulletin A320-32-1310, Revision 01, 
dated June 23, 2011. Where Airbus 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 EASA; or Airbus's EASA DOA.

(t) New 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 Service Bulletin A320-32-1310, Revision 01, 
dated June 23, 2011. Where Airbus 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 EASA; or Airbus's EASA DOA. 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, or 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) New Repetitive Boroscopic Inspections

    After accomplishing the inspection specified in paragraph (t) of 
this AD: Repeat 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) New 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 31, 
2008.

(w) New 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 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) New Terminating Action

    In-service modification of an airplane fitted with twin wheel 
MLG, as required by paragraph (v) or as specified in paragraph (w) 
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) New Exception From Certain Actions

    Except for the prohibition specified in paragraph (z) 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 standard L4.1, 
L4.5, or L4.8 has been performed since the first flight of the 
airplane.

(z) New Parts Installation Prohibition

    For airplanes on which EMM BSCU L4.1, or EMM BSCU L4.5, or EMM 
BSCU L4.8 is not installed: As of the effective date of this AD, no 
person may modify any airplane by installing EMM BSCU standard L4.1, 
L4.5, or L4.8.

(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), 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, which is not incorporated by reference 
in this AD.
    (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 records review 
required by paragraph (p) of this AD, if the review was performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-32-1310, Revision 01, dated June 23, 2011.
    (4) 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 
Service Bulletin A320-32-1336, dated September 19, 2007, which is 
not incorporated by reference in this AD.
    (5) 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, which is not 
incorporated by reference in this AD.

(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.
    (i) 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.
    (ii) AMOCs approved previously for AD 2007-18-09, Amendment 39-
15189 (72 FR 51164, September 6, 2007), are not approved as AMOCs 
with this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement

[[Page 54588]]

in this AD to obtain corrective actions from a manufacturer, the 
action must be accomplished using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA. If approved by the DOA, the 
approval must include the DOA-authorized signature.

(cc) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2011-0201, dated October 13, 
2011, for related information. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0088-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (dd)(6) and (dd)(7) of this AD.

(dd) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR 
October 17, 2014.
    (i) Airbus A318/A319/A320/A321 Airplane Maintenance Manual 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 Service Bulletin A320-32-1310, Revision 01, dated 
June 23, 2011.
    (iii) Airbus 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.
    (4) The following service information was approved for IBR on 
October 11, 2007 (72 FR 51164, September 6, 2007).
    (i) Airbus Service Bulletin A320-32-1310, dated February 8, 
2006.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
November 30, 2005 (70 FR 70715, November 23, 2005).
    (i) Airbus Technical Note 957.1901/05, dated October 18, 2005.
    (ii) Reserved.
    (6) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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 http://www.airbus.com.
    (7) You may review copies of the 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.
    (8) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 29, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-21552 Filed 9-11-14; 8:45 am]
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