Airworthiness Directives; Airbus Airplanes, 54579-54588 [2014-21552]
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
(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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2014–18–03 APEX Aircraft: Amendment
39–17967; Docket No. FAA–2014–0647;
Directorate Identifier 2014–CE–027–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective October 17, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to APEX Aircraft Models
R 3000/160 airplanes, all serial numbers,
certificated in any category.
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(d) Subject
Air Transport Association of America
(ATA) Code 73: Engine Fuel & Control.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as paint
adherence defects inside the engine air intake
box leading to small pieces of paint from the
engine air intake box blocking the engine
carburetor. We are issuing this AD to detect
and correct paint adherence defects inside
the engine air intake box leading to small
pieces of paint from the engine air intake box
blocking the engine carburetor. This
condition, if not detected and corrected,
could lead to an engine failure, possibly
resulting in loss of control.
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(f) Actions and Compliance
Unless already done, do the following
actions, as specified in paragraphs (f)(1)
through (f)(4) of this AD:
(1) Within 110 hours time-in-service (TIS)
after October 17, 2014 (the effective date of
this AD) and repetitively thereafter at
intervals not to exceed 110 hours TIS,
accomplish a visual and tactile inspection of
the engine air intake box (including the
deflection flap) and the engine air ducting
(including the area located downstream of
the filter) following the Accomplishment
Instructions section of CEAPR Mandatory
Service Bulletin Number 161R3, dated
September 6, 2012.
(2) If any paint damage such as bubbling,
blistering, peeled off areas or paint
detachment is found during any inspection
required by paragraph (f)(1) of this AD, before
further flight, replace each damaged part
with an airworthy part following the
Accomplishment Instructions section of
CEAPR Mandatory Service Bulletin Number
161R3, dated September 6, 2012.
(3) Replacement of damaged parts on an
airplane, as required by paragraph (f)(2) of
this AD, does not constitute terminating
action for the repetitive inspections required
by paragraph (f)(1) of this AD for that
airplane.
(4) As of October 17, 2014 (the effective
date of this AD), do not install on any
airplane a painted engine air intake box or
repaired engine air ducting.
(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.
(i) CEAPR Mandatory Service Bulletin
Number 161R3, dated September 6, 2012.
Note 1 to paragraph (i)(2)(i) of this AD:
The service bulletin contains French to
English translation. EASA used the English
translation in referencing the document from
CEAPR. For enforceability purposes, we will
cite references to the CEAPR service
information as it appears on the document.
(ii) Reserved.
(3) For CEAPR service information
identified in this AD, contact CEAPR, Bureau
´
de Navigabilite, 1 route de Troyes, 21121
DAROIS–France, telephone: (33) 380 35 25
22; fax: (33) 380 35 25 25; email: www.info@
ceapr.com; internet: https://ceapr.com/.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090; email: sarjapur.nagarajan@
faa.gov. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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.
Issued in Kansas City, Missouri, on August
29, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2014–0155, dated
July 2, 2014, for related information. You
may examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2014–0647.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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[FR Doc. 2014–21270 Filed 9–11–14; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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
SUMMARY:
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
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 https://
www.regulations.gov/#!docket
Detail;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.airwortheas@airbus.com; Internet https://
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,
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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
´ ´
Generale de l’Aviation Civile] DGAC France
issued AD F–2005–191 [(https://
ad.easa.europa.eu/blob/easa_ad_2005_6411_
F20051910tb_superseded.pdf/AD_F–2005–
191_1) 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, [(https://
ad.easa.europa.eu/blob/easa_ad_2006_0174_
superseded.pdf/AD_2006–0174_2) which
corresponds to FAA AD 2007–18–09,
Amendment 39–15189 (72 FR 51164,
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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 https://
www.regulations.gov/#!document
Detail;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
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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
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to use messages provided by the
manufacturer as approval of deviations
during the accomplishment of an ADmandated 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 FAAapproved. 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
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54581
‘‘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. . . .’’
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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 workhours 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.
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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
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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.
§ 39.13
Regulatory Findings
(a) Effective Date
This airworthiness directive (AD) becomes
effective October 17, 2014.
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 https://
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
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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[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:
■
2013–25–07 Airbus: Amendment 39–17703.
Docket No. FAA–2013–0088; Directorate
Identifier 2011–NM–233–AD.
(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.
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
(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
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This paragraph restates the requirements of
paragraph (h) of AD 2007–18–09,
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18:05 Sep 11, 2014
Jkt 232001
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
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54583
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
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
Figure 1 to Paragraph (i) of this AD -Retained AFM Revision
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.
• Ifthe 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/SKlD&N/W STRG---------------------- OFF THEN ON
Ifthe 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.
• Ifthe WHEEL N/W STRG FAULT ECAM caution appears,
without the LIG SHOCK ABSORBER FAULT ECAM caution:
-No specific crew action is requested by the WHEEL N/W STRG
FAULT ECAM caution procedure.
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
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Jkt 232001
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
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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,
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-Refer to the ECAM STATUS.
Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
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.
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(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
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18:08 Sep 11, 2014
Jkt 232001
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
54585
(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
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.
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.
(o) New Part Number Identification
(r) New AFM Revision
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.
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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BILLING CODE 4910–13–P
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
Figure 2 to Paragraph (r) of this AD -New AFM Revision
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.
• 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.
•
Ifthe 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.
BILLING CODE 4910–13–C
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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
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18:08 Sep 11, 2014
Jkt 232001
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.
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(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
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Note: For airplanes fitted with pre FWC E3P standard, read N.W STEER
instead ofN/W STRG.
Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
(‘‘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.
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(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
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16:18 Sep 11, 2014
Jkt 232001
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.
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54587
(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: 9ANM-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
E:\FR\FM\12SER1.SGM
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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(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 https://
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.
mstockstill on DSK4VPTVN1PROD with RULES
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.
Issued in Renton, Washington, on
November 29, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(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 https://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.
15 CFR Part 30
VerDate Mar<15>2010
16:18 Sep 11, 2014
Jkt 232001
[FR Doc. 2014–21552 Filed 9–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of the Census
[Docket Number: 140821699–4699–01]
RIN 0607–AA53
Foreign Trade Regulations (FTR):
Reinstatement of Exemptions Related
to Temporary Exports, Carnets, and
Shipments Under a Temporary Import
Bond
Bureau of the Census,
Commerce Department.
ACTION: Interim final rule.
AGENCY:
The Bureau of the Census
(Census Bureau) issues this interim final
rule to amend its regulations to
eliminate the reporting requirement for
temporary exports, which includes
carnets, and goods previously imported
on a Temporary Importation Under
Bond (TIB). In the Final Rule published
in the Federal Register on March 14,
2013, the Census Bureau removed the
exemptions for temporary exports,
which includes carnets and goods
imported under a TIB. This amendment
reinstates exemptions for temporary
exports/carnets and for goods that were
imported under a TIB for return in the
same condition as when imported. As a
result, these types of shipments are
exempt from filing, except as noted in
the Foreign Trade Regulations (FTR).
DATES: Effective date: This interim final
rule is effective September 12, 2014.
Comment date: To be assured
consideration, written comments must
be received on our before October 14,
2014.
SUMMARY:
Please direct all written
comments on this interim final rule to
the Chief, Foreign Trade Division, U.S.
Census Bureau, Room 6K032,
Washington, DC 20233–6010. You may
also submit comments, identified by
RIN 0607–AA53 or by the eRulemaking
ADDRESSES:
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
docket number USBC–2014–0003, to the
Federal e-Rulemaking Portal: https://
www.regulations.gov. All comments
received are part of the public record.
No comments will be posted to https://
www.regulations.gov for public viewing
until after the comment period has
closed. Comments will generally be
posted without change. All Personally
Identifiable Information (for example,
name and address) voluntarily
submitted by the commenter may be
publicly accessible. Do not submit
confidential business information or
otherwise sensitive or protected
information. The Census Bureau will
accept anonymous comments (enter
N/A in the required fields, if you wish
to remain anonymous). You may submit
attachments to electronic comments in
Microsoft Word, Excel, WordPerfect, or
Adobe PDF file formats only.
FOR FURTHER INFORMATION CONTACT: Dale
C. Kelly, Chief, Foreign Trade Division,
U.S. Census Bureau, Room 6K032,
Washington, DC 20233–6010, by phone
(301) 763–6937, by fax (301) 763–8835,
or by email <dale.c.kelly@census.gov>.
SUPPLEMENTARY INFORMATION:
Background
The Census Bureau is responsible for
collecting, compiling, and publishing
export trade statistics for the United
States under the provisions of Title 13,
United States Code (U.S.C.), Chapter 9,
Section 301. The Automated Export
System (AES) is the primary instrument
used for collecting export trade data,
which are used by the Census Bureau
for statistical purposes. Through the
AES, the Census Bureau collects
Electronic Export Information (EEI), the
electronic equivalent of the export data
formerly collected on the Shipper’s
Export Declaration, pursuant to the
Foreign Trade Regulations (FTR), Title
15, Code of Federal Regulations (CFR),
part 30. Filing in the AES is not
required for shipments excluded in
Section 30.2(d) and shipments
exempted in Subpart D that are not
subject to Section 30.2(a)(1)(iv).
The Census Bureau published a Final
Rule in the Federal Register on March
14, 2013 (78 FR 16366) that removed the
exemptions for carnets and other
temporary exports and goods previously
imported under a Temporary Import
Bond (TIB) exported in the same
condition; it became effective April 5,
2014. In other words, this rule created
an AES filing requirement for
previously exempted items, such as
carnets. With respect to eliminating
these exemptions, the Department of the
Treasury raised concerns and members
of the trade community submitted
E:\FR\FM\12SER1.SGM
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]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 https://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 [(https://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, [(https://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 https://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 https://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.
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[[Page 54584]]
[GRAPHIC] [TIFF OMITTED] TR12SE14.006
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(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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[[Page 54586]]
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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 https://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 https://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: https://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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