Airworthiness Directives; Airbus Airplanes, 70458-70462 [2014-27360]
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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
(2) For all airplanes: As of the effective
date of this AD, no person may install an
NLG having P/N 201071001 or 201071002 on
any airplane.
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(r) Credit for Previous Actions
This paragraph provides credit for the
replacement required by paragraph (l) of this
AD, if those actions were performed before
the effective date of this AD using Fokker
Service Bulletin SBF 100–32–119, dated
January 31, 2000, provided P/N 201071003 or
201071004 nose gear has been installed.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
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 European Aviation Safety Agency
(EASA); or Fokker Services B.V.’s EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
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(t) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0002R1, dated
March 30, 2012, for related information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0062-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (u)(5) and (u)(6) of this AD.
(u) 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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on December 31, 2014.
(i) Fokker Service Bulletin SBF 100–32–
119, Revision 1, dated November 15, 2011,
including Fokker Manual Change
Notification MCNM–F100–043, dated
January 31, 2000.
(ii) Fokker Proforma Service Bulletin SBF
100–32–149, Revision 1, dated October 25,
2007, including Appendix 1, dated December
12, 2006.
(iii) Fokker Service Bulletin SBF 100–53–
074, dated November 1, 1999.
(4) The following service information was
approved for IBR on October 3, 2000 (65 FR
52298, August 17, 2000).
(i) Fokker Service Bulletin SBF100–32–
118, dated October 8, 1999.
(ii) Reserved.
(5) For service information identified in
this AD, contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 1357,
2130 EL Hoofddorp, the Netherlands;
telephone +31 (0)88–6280–350; fax +31
(0)88–6280–111; email technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.com.
(6) You may view this 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.
(7) 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.
Issued in Renton, Washington, on
November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–27361 Filed 11–25–14; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0425; Directorate
Identifier 2013–NM–180–AD; Amendment
39–18024; AD 2014–23–08]
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) 2012–06–
19 for certain Airbus Model A330–201,
–202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and
–343 airplanes; and Model A340–200
and –300 series airplanes. AD 2012–06–
19 required repetitive inspections of the
main fitting and sliding tube of the nose
landing gear (NLG) for defects, damage,
and cracks; and corrective actions if
necessary. This new AD requires an
inspection of the part number and serial
number of the NLG main fitting and
NLG sliding tube; for affected parts, this
new AD requires a magnetic particle
inspection (MPI) for cracks, and flap
peening and replacement if necessary.
This new AD also requires, for certain
parts, additional inspections for damage
and cracking. This new AD also adds
airplanes to the applicability. This AD
was prompted by reports of a cracked
main fitting and sliding tube during
NLG overhaul. We are issuing this AD
to detect and correct cracks, defects, or
damage of the main fitting or sliding
tube, which could result in consequent
NLG collapse.
DATES: This AD becomes effective
December 31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of April 30, 2012 (77 FR
22188, April 13, 2012).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0425; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
SUMMARY:
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For service information identified in
this AD, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–06–19,
Amendment 39–17000 (77 FR 22188,
April 13, 2012). AD 2012–06–19 applied
to certain Airbus Model A330–201,
–202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and
–343 airplanes; and Model A340–200
and –300 series airplanes. The NPRM
published in the Federal Register on
June 30, 2014 (79 FR 36666).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0179,
dated August 7, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301,
–302, –303, –321, –322, –323, –341,
–342, and –343 airplanes; and Model
A340–200 and –300 series airplanes.
The MCAI states:
During the overhaul of two different Nose
Landing Gear (NLG) units, cracks were found
on the main fitting of one and the sliding
tube of the other. Investigations concluded
that the cracks initiated as a result of residual
stress in the parts, following damage due to
impact during towing incidents.
A subsequent review of the reported
incidents identified a specific group of NLG
main fittings and sliding tubes that may have
sustained impact damage as a result of
towing incidents.
This condition, if not detected and
corrected could lead to NLG collapse.
To address this potential unsafe condition,
EASA issued AD 2010–0034 [(https://
ad.easa.europa.eu/blob/easa_ad_2010_0034_
Corrected_superseded.pdf/AD_2010-0034_1)
[which corresponds to FAA AD 2012–06–19,
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Amendment 39–17000 (77 FR 22188, April
13, 2012)] to require accomplishment of a
one-time Magnetic Particles Inspection (MPI),
followed by repetitive Detailed Visual
Inspections (DVI) of the main fittings and
sliding tubes of the affected NLG units
identified by Part Number (P/N) and Serial
Number (S/N) in the Applicability section of
that AD and, depending on findings,
accomplishment of applicable corrective
actions.
Since that [EASA] AD was issued, it has
been found necessary to address the issue at
the level of NLG detail parts and no longer
at NLG assembly level, as some detail parts
have been transferred from an aeroplane to
another. Airbus revised the applicable
Service Bulletins (SB), which now list the
affected NLG main fittings and sliding tubes.
For the reasons described above, this
[EASA] AD retains [certain] requirements of
EASA AD 2010–0034 which is superseded
and requires [an inspection of the part
number and serial number of the NLG main
fitting and NLG sliding tube, and for affected
parts,] a one-time MPI [for cracks], followed
by repetitive DVI [for cracking, damage to
paint, sealant, cadmium, and base metal] of
the affected NLG main fittings and sliding
tubes and, depending on inspection results,
accomplishment of corrective actions [e.g.,
flap peening and replacing cracked parts].
This AD also extends the applicability to
A330 freighters.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-04250002.
Clarification of Service Information
References
We have clarified the service
information references in this AD to
identify the appendices.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM (79 FR 36666,
June 30, 2014) and the FAA’s response
to each comment.
Request to Reference Service
Information Instead of Table
Air France requested that we revise
paragraph (g) of the NPRM (79 FR
36666, June 30, 2014), to replace table
1 to paragraph (g) of the NPRM with
references to Airbus Service Bulletin
A330–32–3233, Revision 02, including
Appendix 01, dated January 27, 2014;
and Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix
01, dated July 5, 2013. Air France
asserted that the main reason for
superseding AD 2012–06–19,
Amendment 39–17000 (77 FR 22188,
April 13, 2012), is to address the issue
at the level of NLG detail parts and no
longer at the NLG assembly level, as
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70459
some detail parts have been transferred
from one airplane to another.
We agree with the commenter that
Airbus Service Bulletin A330–32–3233,
Revision 02, including Appendix 01,
dated January 27, 2014; and Airbus
Service Bulletin A340–32–4275,
Revision 01, including Appendix 01,
dated July 5, 2013, contain the NLG
detail parts (NLG main fitting and NLG
sliding tube). However, paragraph (g) of
this AD is a requirement that is retained
from AD 2012–06–19, Amendment 39–
17000 (77 FR 22188, April 13, 2012) and
only restates the affected parts
identified in that AD. Paragraphs (i) and
(j) of this AD require inspecting for
affected NLG main fittings and NLG
sliding tubes identified in the service
information and inspecting affected
parts for cracks. Accomplishing the new
requirements specified in paragraph (j)
of this AD terminates the actions
specified in paragraph (g) of this AD.
Therefore, no changes were made to this
AD 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 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 European Aviation
Safety Agency (EASA), or Airbus’s
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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
‘‘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.
Conclusion
We reviewed the available data,
including the comment 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 minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
36666, June 30, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 36666,
June 30, 2014).
Costs of Compliance
We estimate that this AD affects 92
airplanes of U.S. registry.
The actions that were required by AD
2012–06–19, Amendment 39–17000 (77
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FR 22188, April 13, 2012), that are
retained in this AD take about 4 workhours per product, at an average labor
rate of $85 per work-hour. Required
parts cost about $0 per product. Based
on these figures, the estimated cost of
the actions that were required by AD
2012–06–19 is $31,280 per product.
We also estimate that it will take
about 10 work-hours per product to
comply with the new basic
requirements of this AD. The average
labor rate is $85 per work-hour.
Required parts will cost about $0 per
product. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $78,200, or $850 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 114 work-hours and require parts
costing $435,000, for a cost of $444,690
per product. We have no way of
determining the number of aircraft 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);
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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-2014-0425; or in
person at the Docket Management
Facility 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–06–19, Amendment 39–17000 (77
FR 22188, April 13, 2012), and adding
the following new AD:
■
2014–23–08 Airbus: Amendment 39–18024.
Docket No. FAA–2014–0425; Directorate
Identifier 2013–NM–180–AD.
(a) Effective Date
This AD becomes effective December 31,
2014.
(b) Affected ADs
This AD replaces AD 2012–06–19,
Amendment 39–17000 (77 FR 22188, April
13, 2012).
(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –223, –223F, –243, –243F,
–301, –302, –303, –321, –322, –323, –341,
–342, and –343 airplanes; and Model A340–
211, –212, –213, –311, –312, and –313
airplanes; certificated in any category; all
manufacturer serial numbers.
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(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—APPLICABLE NLG AND SERIAL
NUMBERS—Continued
(e) Reason
This AD was prompted by reports of a
cracked nose landing gear (NLG) main fitting
and sliding tube during NLG overhaul. We
are issuing this AD to detect and correct
cracks, defects, or damage of the main fitting
or sliding tube, which could result in
consequent NLG collapse.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Detailed Inspection and
Corrective Actions
This paragraph restates the requirements of
paragraph (g) of AD 2012–06–19,
Amendment 39–17000 (77 FR 22188, April
13, 2012), with revised service information.
For Model A330–201, –202, –203, –223,
–243, –301, –302, –303, –321, –322, –323,
–341, –342, and –343 airplanes; and Model
A340–211, –212, –213, –311, –312, and –313
airplanes; if fitted with the NLG identified in
table 1 to paragraph (g) of this AD: Within
900 flight hours after April 30, 2012 (the
effective date of AD 2012–06–19), do a
detailed inspection of the NLG main fitting
and sliding tube for any cracks, defects, and
damage of the paint or surface protection,
including paint removal and cracking of the
surface treatment. Before further flight after
doing the detailed inspection of the NLG,
remove the labels, paint, surface protection
coatings, and cadmium from the NLG main
fitting; do a detailed inspection for any
damage to the surface that will impair the
magnetic particle inspection (MPI); and, if
any defects are found, before further flight,
remove any defects by polishing. Do all
actions specified in this paragraph in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraph (g)(1) or
(g)(2) of this AD.
(1) For Model A330 airplanes: Airbus
Mandatory Service Bulletin A330–32–3233,
dated October 22, 2009; or Airbus Service
Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014.
(2) For Model A340 airplanes: Airbus
Mandatory Service Bulletin A340–32–4275,
dated October 22, 2009; or Airbus Service
Bulletin A340–32–4275, Revision 01,
including Appendix 01, dated July 5, 2013.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—APPLICABLE NLG AND SERIAL
NUMBERS
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Part No.
D23285200 ...............................
D23285101–7 ...........................
D23285101–10 .........................
D23581100–1 ...........................
D23581100–1 ...........................
D23581100–7 ...........................
D23581100–7 ...........................
D23581100–7 ...........................
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Serial No.
B2
B58
B75
B124
B159
B386
B398
B400
Jkt 235001
Part No.
Serial No.
D23581100–7 ...........................
B403
(h) Retained Magnetic Particle Inspection
This paragraph restates the requirements of
paragraph (h) of AD 2012–06–19,
Amendment 39–17000 (77 FR 22188, April
13, 2012), with revised service information.
Before further flight after doing the actions
required in paragraph (g) of this AD: Do an
MPI for cracking of the NLG main fitting and
sliding tube, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(1) or (g)(2) of this AD.
(1) If no crack is detected during the MPI
required by the introductory text of
paragraph (h) of this AD: Before further
flight, flap peen the inspected area where the
paint and cadmium has been removed, and
replace the protective coatings, in accordance
with the Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(1) or (g)(2) of this AD.
(2) If any crack is detected during the MPI
required by the introductory text of
paragraph (h) of this AD: Before further
flight, replace the damaged part with a new
or serviceable part, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(1) or (g)(2) of this AD.
(i) New Identification of Part and Serial
Numbers
Within 1,000 flight hours after the effective
date of this AD, identify the part number and
serial number of the NLG main fitting and
NLG sliding tube, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014; or Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix 01,
dated July 5, 2013; as applicable. A review
of airplane maintenance records is acceptable
in lieu of this identification if the part
number and the serial number of the NLG
main fitting and NLG sliding tube can be
conclusively determined from that review.
(j) New Magnetic Particle Inspection
If, during the identification required by
paragraph (i) of this AD, it is determined any
NLG main fitting or NLG sliding tube is
installed and the fitting or tube has a part
number and serial number listed in Airbus
Service Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014; or Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix 01,
dated July 5, 2013; as applicable: Within
1,000 flight hours after the effective date of
this AD, do an MPI for cracks of the affected
parts, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014; or Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix 01,
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Frm 00035
Fmt 4700
Sfmt 4700
70461
dated July 5, 2013; as applicable.
Accomplishing the MPI required by this
paragraph terminates the inspections
required by paragraphs (g) and (h) of this AD.
(1) If any crack is detected during the MPI
required by the introductory text of
paragraph (j) of this AD: Before further flight,
replace any cracked part (NLG main fitting
and NLG sliding tube) with a serviceable
part, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014; or Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix 01,
dated July 5, 2013; as applicable.
(2) If no crack is detected during the MPI
required by the introductory text of
paragraph (j) of this AD: Before further flight,
do a flap peening to introduce compressive
residual stress and corrosion protection, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
32–3233, Revision 02, including Appendix
01, dated January 27, 2014; or Airbus Service
Bulletin A340–32–4275, Revision 01,
including Appendix 01, dated July 5, 2013;
as applicable.
(k) New Detailed Inspection
Within 900 flight hours after doing the flap
peening required by paragraph (j)(2) of this
AD, do a detailed inspection for damage to
paint, damage to the sealant around the
labels, damage to the cadmium or base metal,
and for cracking of the affected parts, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
32–3233, Revision 02, including Appendix
01, dated January 27, 2014; or Airbus Service
Bulletin A340–32–4275, Revision 01,
including Appendix 01, dated July 5, 2013;
as applicable. Repeat the inspection
thereafter at intervals not to exceed 900 flight
hours.
(1) If any damage to the paint, damage to
the sealant around the labels, or damage to
the cadmium or base metal, is detected
during any detailed inspection required by
the introductory text of paragraph (k) of this
AD; Before further flight, do an MPI for
cracking of the affected parts, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–32–3233,
Revision 02, including Appendix 01, dated
January 27, 2014; or Airbus Service Bulletin
A340–32–4275, Revision 01, including
Appendix 01, dated July 5, 2013; as
applicable.
(2) If any cracking is detected during any
inspection required by the introductory text
of paragraph (k) or paragraph (k)(1) of this
AD: Before further flight, replace any cracked
part with a serviceable part, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–32–3233,
Revision 02, including Appendix 01, dated
January 27, 2014; or Airbus Service Bulletin
A340–32–4275, Revision 01, including
Appendix 01, dated July 5, 2013; as
applicable.
(l) Terminating Action
Replacement of a part as required by
paragraph (j)(1) or (k)(2) of this AD is
terminating action for the repetitive detailed
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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
inspections required by paragraph (k) of this
AD for that part, provided that the part
number and serial number of the replacement
part is not listed in Airbus Service Bulletin
A330–32–3233, Revision 02, including
Appendix 01, dated January 27, 2014; or
Airbus Service Bulletin A340–32–4275,
Revision 01, including Appendix 01, dated
July 5, 2013; as applicable.
(m) Parts Installation Limitation
As of the effective date of this AD,
installation of an NLG main fitting or NLG
sliding tube having a part number and serial
number listed in Airbus Service Bulletin
A330–32–3233, Revision 02, including
Appendix 01, dated January 27, 2014; or
Airbus Service Bulletin A340–32–4275,
Revision 01, including Appendix 01, dated
July 5, 2013; as applicable; is allowed,
provided that the NLG main fitting and NLG
sliding tube have not accumulated more than
900 flight hours since the most recent
inspection accomplished in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–32–3233, Revision 02,
including Appendix 01, dated January 27,
2014; or Airbus Service Bulletin A340–32–
4275, Revision 01, including Appendix 01,
dated July 5, 2013; as applicable.
mstockstill on DSK4VPTVN1PROD with RULES
(n) Credit for Previous Actions
This paragraph provides credit for
inspections required by paragraphs (j) and (k)
of this AD and the flap peening required by
paragraph (j)(2) of this AD, if those actions
were performed before the effective date of
this AD using the applicable service
information specified in paragraph (n)(1),
(n)(2), or (n)(3) of this AD.
(1) Airbus Service Bulletin A330–32–3233,
dated October 22, 2009.
(2) Airbus Service Bulletin A330–32–3233,
Revision 01, dated July 5, 2013. This
document is not incorporated by reference in
this AD.
(3) Airbus Service Bulletin A340–32–4275,
dated October 22, 2009.
(o) 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
Issued in Renton, Washington, on
November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(p) Related Information
U.S. Customs and Border Protection
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2013–0179, dated August 7, 2013,
for related information. You may examine the
MCAI in the AD docket on the Internet at
https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0425-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) 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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on December 31, 2014.
(i) Airbus Service Bulletin A330–32–3233,
Revision 02, including Appendix 01, dated
January 27, 2014.
(ii) Airbus Service Bulletin A340–32–4275,
Revision 01, including Appendix 01, dated
July 5, 2013.
(4) The following service information was
approved for IBR on April 30, 2012, (77 FR
22188, April 13, 2012).
(i) Airbus Service Bulletin A330–32–3233,
dated October 22, 2009.
(ii) Airbus Service Bulletin A340–32–4275,
dated October 22, 2009.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(6) You may view this 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.
(7) 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.
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[FR Doc. 2014–27360 Filed 11–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
19 CFR Part 4
[CBP Dec. 14–11]
Technical Amendment: Boarding of
Vessels at CBP Ports
U.S. Customs and Border
Protection, Department of Homeland
Security.
ACTION: Final rule; technical
amendment.
AGENCY:
This document amends the
U.S. Customs and Border Protection
(CBP) regulations to conform to U.S.
Coast Guard implementing regulations
regarding certain boardings of vessels
under the Maritime Transportation Act
of 2002, as amended (MTSA). Under
MTSA, any person boarding a vessel
arriving at a CBP port after that vessel
is taken in charge by a CBP officer must
comply with Transportation Worker
Identification Credential requirements.
This document also updates
terminology and removes obsolete
language in the relevant regulatory
section.
SUMMARY:
DATES:
Effective November 26, 2014.
FOR FURTHER INFORMATION CONTACT:
Craig Clark, Office of Field Operations,
U.S. Customs and Border Protection,
(202) 344–3052, OFO-ManifestBranch@
cbp.dhs.gov.
SUPPLEMENTARY INFORMATION:
I. Background
It is the policy of U.S. Customs and
Border Protection (CBP) to periodically
review title 19 of the Code of Federal
Regulations (19 CFR) to ensure that it is
accurate and up-to-date so that the
general public is aware of CBP
requirements and procedures. As part of
this review policy, CBP has determined
that certain corrections affecting part 4
of the CBP regulations (19 CFR part 4)
are necessary.
A. Maritime Transportation Act of 2002
The Maritime Transportation Act of
2002 (MTSA), Pub. L. 107–295, 116 Stat.
2064, as amended by the Security and
Accountability for Every Port Act of
E:\FR\FM\26NOR1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70458-70462]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-27360]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-180-AD;
Amendment 39-18024; AD 2014-23-08]
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) 2012-06-19 for
certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-
200 and -300 series airplanes. AD 2012-06-19 required repetitive
inspections of the main fitting and sliding tube of the nose landing
gear (NLG) for defects, damage, and cracks; and corrective actions if
necessary. This new AD requires an inspection of the part number and
serial number of the NLG main fitting and NLG sliding tube; for
affected parts, this new AD requires a magnetic particle inspection
(MPI) for cracks, and flap peening and replacement if necessary. This
new AD also requires, for certain parts, additional inspections for
damage and cracking. This new AD also adds airplanes to the
applicability. This AD was prompted by reports of a cracked main
fitting and sliding tube during NLG overhaul. We are issuing this AD to
detect and correct cracks, defects, or damage of the main fitting or
sliding tube, which could result in consequent NLG collapse.
DATES: This AD becomes effective December 31, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 31,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
30, 2012 (77 FR 22188, April 13, 2012).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0425; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
[[Page 70459]]
For service information identified in this AD, contact Airbus SAS,
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80;
email airworthiness.A330-A340@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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-06-19, Amendment 39-17000 (77 FR 22188,
April 13, 2012). AD 2012-06-19 applied to certain Airbus Model A330-
201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341,
-342, and -343 airplanes; and Model A340-200 and -300 series airplanes.
The NPRM published in the Federal Register on June 30, 2014 (79 FR
36666).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0179, dated August 7, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321,
-322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300
series airplanes. The MCAI states:
During the overhaul of two different Nose Landing Gear (NLG)
units, cracks were found on the main fitting of one and the sliding
tube of the other. Investigations concluded that the cracks
initiated as a result of residual stress in the parts, following
damage due to impact during towing incidents.
A subsequent review of the reported incidents identified a
specific group of NLG main fittings and sliding tubes that may have
sustained impact damage as a result of towing incidents.
This condition, if not detected and corrected could lead to NLG
collapse.
To address this potential unsafe condition, EASA issued AD 2010-
0034 [(https://ad.easa.europa.eu/blob/easa_ad_2010_0034_Corrected_superseded.pdf/AD_2010-0034_1) [which
corresponds to FAA AD 2012-06-19, Amendment 39-17000 (77 FR 22188,
April 13, 2012)] to require accomplishment of a one-time Magnetic
Particles Inspection (MPI), followed by repetitive Detailed Visual
Inspections (DVI) of the main fittings and sliding tubes of the
affected NLG units identified by Part Number (P/N) and Serial Number
(S/N) in the Applicability section of that AD and, depending on
findings, accomplishment of applicable corrective actions.
Since that [EASA] AD was issued, it has been found necessary to
address the issue at the level of NLG detail parts and no longer at
NLG assembly level, as some detail parts have been transferred from
an aeroplane to another. Airbus revised the applicable Service
Bulletins (SB), which now list the affected NLG main fittings and
sliding tubes.
For the reasons described above, this [EASA] AD retains
[certain] requirements of EASA AD 2010-0034 which is superseded and
requires [an inspection of the part number and serial number of the
NLG main fitting and NLG sliding tube, and for affected parts,] a
one-time MPI [for cracks], followed by repetitive DVI [for cracking,
damage to paint, sealant, cadmium, and base metal] of the affected
NLG main fittings and sliding tubes and, depending on inspection
results, accomplishment of corrective actions [e.g., flap peening
and replacing cracked parts]. This AD also extends the applicability
to A330 freighters.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0425-0002.
Clarification of Service Information References
We have clarified the service information references in this AD to
identify the appendices.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (79 FR
36666, June 30, 2014) and the FAA's response to each comment.
Request to Reference Service Information Instead of Table
Air France requested that we revise paragraph (g) of the NPRM (79
FR 36666, June 30, 2014), to replace table 1 to paragraph (g) of the
NPRM with references to Airbus Service Bulletin A330-32-3233, Revision
02, including Appendix 01, dated January 27, 2014; and Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July
5, 2013. Air France asserted that the main reason for superseding AD
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), is to
address the issue at the level of NLG detail parts and no longer at the
NLG assembly level, as some detail parts have been transferred from one
airplane to another.
We agree with the commenter that Airbus Service Bulletin A330-32-
3233, Revision 02, including Appendix 01, dated January 27, 2014; and
Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix
01, dated July 5, 2013, contain the NLG detail parts (NLG main fitting
and NLG sliding tube). However, paragraph (g) of this AD is a
requirement that is retained from AD 2012-06-19, Amendment 39-17000 (77
FR 22188, April 13, 2012) and only restates the affected parts
identified in that AD. Paragraphs (i) and (j) of this AD require
inspecting for affected NLG main fittings and NLG sliding tubes
identified in the service information and inspecting affected parts for
cracks. Accomplishing the new requirements specified in paragraph (j)
of this AD terminates the actions specified in paragraph (g) of this
AD. Therefore, no changes were made to this AD 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 European Aviation Safety Agency (EASA), or Airbus's
[[Page 70460]]
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.
Conclusion
We reviewed the available data, including the comment 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 minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 36666, June 30, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 36666, June 30, 2014).
Costs of Compliance
We estimate that this AD affects 92 airplanes of U.S. registry.
The actions that were required by AD 2012-06-19, Amendment 39-17000
(77 FR 22188, April 13, 2012), that are retained in this AD take about
4 work-hours per product, at an average labor rate of $85 per work-
hour. Required parts cost about $0 per product. Based on these figures,
the estimated cost of the actions that were required by AD 2012-06-19
is $31,280 per product.
We also estimate that it will take about 10 work-hours per product
to comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $78,200, or $850 per product.
In addition, we estimate that any necessary follow-on actions will
take about 114 work-hours and require parts costing $435,000, for a
cost of $444,690 per product. We have no way of determining the number
of aircraft 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-2014-0425; or in person at the
Docket Management Facility 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)
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), and
adding the following new AD:
2014-23-08 Airbus: Amendment 39-18024. Docket No. FAA-2014-0425;
Directorate Identifier 2013-NM-180-AD.
(a) Effective Date
This AD becomes effective December 31, 2014.
(b) Affected ADs
This AD replaces AD 2012-06-19, Amendment 39-17000 (77 FR 22188,
April 13, 2012).
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and
-313 airplanes; certificated in any category; all manufacturer
serial numbers.
[[Page 70461]]
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of a cracked nose landing gear
(NLG) main fitting and sliding tube during NLG overhaul. We are
issuing this AD to detect and correct cracks, defects, or damage of
the main fitting or sliding tube, which could result in consequent
NLG collapse.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed Inspection and Corrective Actions
This paragraph restates the requirements of paragraph (g) of AD
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with
revised service information. For Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-211, -212, -213, -311, -312, and -313
airplanes; if fitted with the NLG identified in table 1 to paragraph
(g) of this AD: Within 900 flight hours after April 30, 2012 (the
effective date of AD 2012-06-19), do a detailed inspection of the
NLG main fitting and sliding tube for any cracks, defects, and
damage of the paint or surface protection, including paint removal
and cracking of the surface treatment. Before further flight after
doing the detailed inspection of the NLG, remove the labels, paint,
surface protection coatings, and cadmium from the NLG main fitting;
do a detailed inspection for any damage to the surface that will
impair the magnetic particle inspection (MPI); and, if any defects
are found, before further flight, remove any defects by polishing.
Do all actions specified in this paragraph in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For Model A330 airplanes: Airbus Mandatory Service Bulletin
A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin
A330-32-3233, Revision 02, including Appendix 01, dated January 27,
2014.
(2) For Model A340 airplanes: Airbus Mandatory Service Bulletin
A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin
A340-32-4275, Revision 01, including Appendix 01, dated July 5,
2013.
Table 1 to Paragraph (g) of This AD--Applicable NLG and Serial Numbers
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
D23285200.................................................. B2
D23285101-7................................................ B58
D23285101-10............................................... B75
D23581100-1................................................ B124
D23581100-1................................................ B159
D23581100-7................................................ B386
D23581100-7................................................ B398
D23581100-7................................................ B400
D23581100-7................................................ B403
------------------------------------------------------------------------
(h) Retained Magnetic Particle Inspection
This paragraph restates the requirements of paragraph (h) of AD
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with
revised service information. Before further flight after doing the
actions required in paragraph (g) of this AD: Do an MPI for cracking
of the NLG main fitting and sliding tube, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(1) or (g)(2) of this AD.
(1) If no crack is detected during the MPI required by the
introductory text of paragraph (h) of this AD: Before further
flight, flap peen the inspected area where the paint and cadmium has
been removed, and replace the protective coatings, in accordance
with the Accomplishment Instructions of the applicable service
information specified in paragraph (g)(1) or (g)(2) of this AD.
(2) If any crack is detected during the MPI required by the
introductory text of paragraph (h) of this AD: Before further
flight, replace the damaged part with a new or serviceable part, in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (g)(1) or (g)(2) of this
AD.
(i) New Identification of Part and Serial Numbers
Within 1,000 flight hours after the effective date of this AD,
identify the part number and serial number of the NLG main fitting
and NLG sliding tube, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02,
including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable. A review of airplane maintenance
records is acceptable in lieu of this identification if the part
number and the serial number of the NLG main fitting and NLG sliding
tube can be conclusively determined from that review.
(j) New Magnetic Particle Inspection
If, during the identification required by paragraph (i) of this
AD, it is determined any NLG main fitting or NLG sliding tube is
installed and the fitting or tube has a part number and serial
number listed in Airbus Service Bulletin A330-32-3233, Revision 02,
including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable: Within 1,000 flight hours after the
effective date of this AD, do an MPI for cracks of the affected
parts, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-32-3233, Revision 02, including Appendix 01,
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275,
Revision 01, including Appendix 01, dated July 5, 2013; as
applicable. Accomplishing the MPI required by this paragraph
terminates the inspections required by paragraphs (g) and (h) of
this AD.
(1) If any crack is detected during the MPI required by the
introductory text of paragraph (j) of this AD: Before further
flight, replace any cracked part (NLG main fitting and NLG sliding
tube) with a serviceable part, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02,
including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable.
(2) If no crack is detected during the MPI required by the
introductory text of paragraph (j) of this AD: Before further
flight, do a flap peening to introduce compressive residual stress
and corrosion protection, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02,
including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable.
(k) New Detailed Inspection
Within 900 flight hours after doing the flap peening required by
paragraph (j)(2) of this AD, do a detailed inspection for damage to
paint, damage to the sealant around the labels, damage to the
cadmium or base metal, and for cracking of the affected parts, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, including Appendix 01, dated
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision
01, including Appendix 01, dated July 5, 2013; as applicable. Repeat
the inspection thereafter at intervals not to exceed 900 flight
hours.
(1) If any damage to the paint, damage to the sealant around the
labels, or damage to the cadmium or base metal, is detected during
any detailed inspection required by the introductory text of
paragraph (k) of this AD; Before further flight, do an MPI for
cracking of the affected parts, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-32-3233,
Revision 02, including Appendix 01, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, including
Appendix 01, dated July 5, 2013; as applicable.
(2) If any cracking is detected during any inspection required
by the introductory text of paragraph (k) or paragraph (k)(1) of
this AD: Before further flight, replace any cracked part with a
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-32-3233, Revision 02, including
Appendix 01, dated January 27, 2014; or Airbus Service Bulletin
A340-32-4275, Revision 01, including Appendix 01, dated July 5,
2013; as applicable.
(l) Terminating Action
Replacement of a part as required by paragraph (j)(1) or (k)(2)
of this AD is terminating action for the repetitive detailed
[[Page 70462]]
inspections required by paragraph (k) of this AD for that part,
provided that the part number and serial number of the replacement
part is not listed in Airbus Service Bulletin A330-32-3233, Revision
02, including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable.
(m) Parts Installation Limitation
As of the effective date of this AD, installation of an NLG main
fitting or NLG sliding tube having a part number and serial number
listed in Airbus Service Bulletin A330-32-3233, Revision 02,
including Appendix 01, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated
July 5, 2013; as applicable; is allowed, provided that the NLG main
fitting and NLG sliding tube have not accumulated more than 900
flight hours since the most recent inspection accomplished in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, including Appendix 01, dated
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision
01, including Appendix 01, dated July 5, 2013; as applicable.
(n) Credit for Previous Actions
This paragraph provides credit for inspections required by
paragraphs (j) and (k) of this AD and the flap peening required by
paragraph (j)(2) of this AD, if those actions were performed before
the effective date of this AD using the applicable service
information specified in paragraph (n)(1), (n)(2), or (n)(3) of this
AD.
(1) Airbus Service Bulletin A330-32-3233, dated October 22,
2009.
(2) Airbus Service Bulletin A330-32-3233, Revision 01, dated
July 5, 2013. This document is not incorporated by reference in this
AD.
(3) Airbus Service Bulletin A340-32-4275, dated October 22,
2009.
(o) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement 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 European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0179, dated August 7, 2013, for related information. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0425-0002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) 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 this AD specifies otherwise.
(3) The following service information was approved for IBR on
December 31, 2014.
(i) Airbus Service Bulletin A330-32-3233, Revision 02, including
Appendix 01, dated January 27, 2014.
(ii) Airbus Service Bulletin A340-32-4275, Revision 01,
including Appendix 01, dated July 5, 2013.
(4) The following service information was approved for IBR on
April 30, 2012, (77 FR 22188, April 13, 2012).
(i) Airbus Service Bulletin A330-32-3233, dated October 22,
2009.
(ii) Airbus Service Bulletin A340-32-4275, dated October 22,
2009.
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(6) You may view this 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.
(7) 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 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-27360 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P
