Airworthiness Directives; Airbus Airplanes, 73960-73963 [2015-29851]
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations
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 Kansas City, Missouri, on
November 16, 2015.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–29855 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0928; Directorate
Identifier 2014–NM–040–AD; Amendment
39–18333; AD 2015–24–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, A340–
300, A340–500, and A340–600 series
airplanes. This AD was prompted by a
report of skin disbonding on a
composite side panel of a rudder
installed on an A310 airplane. This AD
requires a review of the maintenance
records of the rudder to determine if any
composite side shell panel repair has
been done; a thermography inspection
limited to the repair areas or complete
side shells, as applicable, to identify
possible in-service rudder repairs,
damages, or fluid ingress; and
applicable related investigative and
corrective actions. We are issuing this
AD to detect and correct the rudder skin
disbonding, which could affect the
structural integrity of the rudder, and
could result in reduced controllability
of the airplane.
DATES: This AD becomes effective
January 4, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 4, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0928 or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
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SUMMARY:
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30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0928.
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 by adding an AD that would
apply to all Airbus Model A330–200
Freighter, A330–200, A330–300, A340–
200, A340–300, A340–500, and A340–
600 series airplanes. The NPRM
published in the Federal Register on
December 29, 2014 (79 FR 77972).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0033, dated February 4,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200 Freighter, A330–200,
A330–300, A340–200, A340–300, A340–
500, and A340–600 series airplanes. The
MCAI states:
A case of skin disbonding was reported on
a composite side panel of a rudder installed
on an A310 aeroplane.
The investigation results revealed that this
disbonding started from a skin panel area
previously repaired in-service in accordance
with the Structural Repair Manual (SRM).
The initial damage has been identified as
a disbonding between the core and skin of
the repaired area. This damage may not be
visually detectable and likely propagates
during normal operation due to the variation
of pressure during ground-air-ground cycles.
Composite rudder side shell panels are also
installed on A330 and A340 aeroplanes,
which may have been repaired in-service
using a similar method.
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This condition, if not detected and
corrected, could affect the structural integrity
of the rudder, possibly resulting in reduced
control of the aeroplane.
For the reasons described above, this
[EASA] AD requires a one-time
thermography inspection of a repaired rudder
or a rudder whose maintenance records are
incomplete and, depending on findings,
accomplishment of applicable corrective and
follow-up actions [including repetitive
inspections].
The related investigative actions in
this AD include, as applicable, an
ultrasonic inspection, an elasticity
laminate checker inspection, a tap test
inspection, detailed inspections, and
thermography inspections, and
ventilation of the core. The repetitive
inspections include detailed inspections
and thermography inspections. The
corrective actions in this AD include
repairs.
The compliance time for the related
investigative actions is before further
flight after accomplishing the applicable
inspection required by paragraph (g)(1)
or (g)(2)(ii) of this AD.
The intervals for the repetitive
inspections are either 900 flight hours or
1,000 flight cycles, depending on the
applicable conditions identified in the
service information.
The compliance times for the
corrective actions range, depending on
the applicable conditions identified in
the service information, from before
further flight to within 4,500 flight
cycles but not to exceed 24 months after
accomplishing the applicable inspection
required by paragraph (g)(1) or (g)(2)(ii)
of this AD.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-09280002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 77972,
December 29, 2014) and the FAA’s
response to each comment.
Request To Use the Latest Service
Information
American Airlines (AAL) and Delta
Airlines (DAL) requested that we revise
the NPRM (79 FR 77972, December 29,
2014) to cite the latest service
information.
We agree with the commenters’
request. Airbus has issued Airbus
Service Bulletin A330–55–3043,
Revision 1, dated August 20, 2014,
Airbus Service Bulletin A340–55–4039,
Revision 1, dated August 20, 2014, and
Airbus Service Bulletin A340–55–5007,
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Revision 1, dated August 20, 2014. The
new service information requires no
additional work, and there are no new
actions required by this AD. We have
updated the AD with the latest service
information, and we have also added a
credit paragraph for previous actions
done before the effective date of this AD
using the service information cited in
the NPRM (79 FR 77972, December 29,
2014).
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Request To Clarify the Structural
Repair Manual Repairs That Are
Affected
AAL requested that the NPRM (79 FR
77972, December 29, 2014) clarify the
specific structural repair manual (SRM)
repairs that are affected. AAL stated that
paragraph (j) of the proposed AD states
specific serial number ranges that are
not affected by the AD provided that it
is determined that no repair has been
accomplished on the composite side
shell panel of that rudder since first
installation on the airplane. AAL
believes this last sentence is too broad
and not in line with the intent of the
service information requirements. AAL
commented that stating no repair has
been accomplished limits acceptable
repairs covered by an Airbus repair
design approval sheet, designated
engineering representative repairs, and
other SRM repairs not affected by the
improper practices that are the subject
of the NPRM. AAL stated that
paragraphs (g)(1) and paragraph (l) of
the proposed AD list the affected SRM
repairs in the service information
figures.
We agree with the commenter’s
request. We have revised paragraph (j)
of this AD to clarify the specific repairs
accomplished as described in the SRM
procedures identified in Figure
A–GBBAA (Sheet 01 and 02) or Figure
A–GBCAA (Sheet 02) of the service
information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, as
applicable.
Request To Add the Manufacturer Part
Number
DAL requested that the NPRM (79 FR
77972, December 29, 2014) include the
manufacturer part numbers of the
rudder serial numbers specified in
paragraph (j), which provides only a list
of rudder serial numbers not affected by
the requirements of paragraphs (g) and
(h) of the proposed AD. DAL
commented that in the event of future
aircraft acquisitions or rudder
(component only) purchases, operators
will need the manufacturer part
numbers associated with the listed
serial numbers to determine AD
applicability.
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We disagree with the commenter’s
request to add part numbers to
paragraph (j) of this AD. The rudder
serial number, regardless of the part
number, is the key to identifying
whether the rudder is not affected. Only
rudders that have certain serial numbers
that meet the conditions specified in
paragraph (j) of this AD are exempt from
the actions required by paragraphs (g)
and (h) of this AD. Airbus has informed
us that rudders with the same
manufacturer part number might or
might not be affected; it is the serial
number that determines whether it is an
affected rudder. We have not changed
the AD in this regard.
Conclusion
We reviewed the relevant data,
considered 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 minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
77972, December 29, 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 77972,
December 29, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–55–
3043, Revision 1, dated August 20,
2014.
• Airbus Service Bulletin A340–55–
4039, Revision 1, dated August 20,
2014.
• Airbus Service Bulletin A340–55–
5007, Revision 1, dated August 20,
2014.
The service information describes
procedures for a review of the
maintenance records of the rudder to
determine if any composite side shell
panel repair has been done; a
thermography inspection limited to the
repair areas or complete side shells, as
applicable, to identify possible inservice rudder repairs, damages, or fluid
ingress; and applicable related
investigative and corrective actions.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this AD.
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Costs of Compliance
We estimate that this AD affects 55
airplanes of U.S. registry.
We also estimate that it would take
about 45 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts would
cost about $0 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be
$210,375, or $3,825 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.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to 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 control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is 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.
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.
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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-2014-0928; 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 adding
the following new airworthiness
directive (AD):
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■
2015–24–01 Airbus: Amendment 39–18333.
Docket No. FAA–2014–0928; Directorate
Identifier 2014–NM–040–AD.
(a) Effective Date
This AD becomes effective January 4, 2016.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) Airbus Model A330–201, –202, –203,
–223, –223F,–243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes, all manufacturer serial numbers.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a report of skin
disbonding on a composite side panel of a
rudder installed on an A310 airplane. We are
issuing this AD to detect and correct the
rudder skin disbonding, which could affect
the structural integrity of the rudder, and
could result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Review the Maintenance Records
Within 24 months after the effective date
of this AD: Review the maintenance records
of the rudder to determine if any composite
side shell panel repair has been
accomplished on the rudder since first
installation on an airplane.
(1) If, based on the maintenance record
review, any repair identified in Figure A–
GBBAA (Sheet 01 and 02) or Figure A–
GBCAA (Sheet 02) of the service information
specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD is found: Within 24
months after the effective date of this AD, do
a thermography inspection for repair,
damages, and fluid ingress, limited to the
repaired areas, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this
AD:
(i) Airbus Service Bulletin A330–55–3043,
Revision 1, dated August 20, 2014 (for Model
A330–201, –202, –203, –223, –223F, –243,
–243F, –301, –302, –303, –321, –322, –323,
–341, –342, and –343 airplanes).
(ii) Airbus Service Bulletin A340–55–4039,
Revision 1, dated August 20, 2014 (for Model
A340–211, –212, –213, –311, –312, and –313
airplanes).
(iii) Airbus Service Bulletin A340–55–
5007, Revision 1, dated August 20, 2014 (for
Model A340–541 and –642 airplanes).
(2) For a rudder for which maintenance
records are unavailable or incomplete, do the
actions specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD:
(i) No later than 3 months before
accomplishment of the thermography
inspection, as required by paragraph (g)(2)(ii)
of this AD, contact Airbus to request related
rudder manufacturing data by submitting the
serial number of the rudder to Airbus.
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(ii) Within 24 months after the effective
date of this AD: Do a thermography
inspection for any repair on complete side
shells to identify and mark any repair, in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD.
(h) Related Investigative Actions, Corrective
Actions, and Repetitive Inspections
After the inspection as required by
paragraph (g)(1) or (g)(2) of this AD: At the
applicable compliance times specified in
paragraph 1.E., ‘‘Compliance,’’ of Tables 3,
4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD,
accomplish all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD; except as
provided by paragraphs (i)(1) and (i)(2) of
this AD. Options provided in the service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD for
accomplishing the actions are acceptable for
the corresponding requirements of this
paragraph provided that the related
investigative and corrective actions are done
at the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, including
applicable repetitive inspection intervals,
except as required by paragraphs (i)(1) and
(i)(2) of this AD. Thereafter repeat the
inspections of the restored and repaired areas
at the applicable compliance time specified
in paragraph 1.E., ‘‘Compliance,’’ of Tables 3,
4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD.
(i) Exceptions to the Service Information
(1) Where the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD specifies a
compliance time relative to the date of the
service information, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) If the service information in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD specifies
to contact Airbus: At the applicable
compliance times specified in paragraph 1.E.,
‘‘Compliance,’’ of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, repair 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).
(j) Provisions for Certain Airplanes
Airplanes fitted with a rudder having a
serial number (S/N) that is not in the range
of S/N TS–1001 through S/N TS–1043
inclusive, S/N TS–2001 through S/N TS–
2074 inclusive, S/N TS–3000 through S/N
TS–3525 inclusive, S/N TS–4001 through
S/N TS–4170 inclusive, S/N TS–6001
through S/N TS–6246 inclusive, or S/N TS–
5001 through S/N TS–5138 inclusive, are not
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affected by the requirements of paragraphs (g)
and (h) of this AD provided that it is
determined that no repair has been
accomplished as described in the procedures
identified in Figure A–GBBAA (Sheet 01 and
02) or Figure A–GBCAA (Sheet 02) of the
service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, as
applicable, on the composite side shell panel
of that rudder since first installation on an
airplane.
(k) Parts Installation Limitations
As of the effective date of this AD, no
person may install, on any airplane, a rudder,
unless the record review and thermography
inspection specified in paragraph (g) of this
AD has been done on that rudder and
thereafter all applicable related investigative
actions, repetitive inspections, and corrective
actions are done as required by paragraph (h)
of this AD, except as provided in paragraph
(j) of this AD.
(l) Repair Prohibition
As of the effective date of this AD, no
person may accomplish a side shell repair on
any rudder using a structure repair manual
procedure identified in Figure A–GBBAA
(Sheet 01 and 02) or Figure A–GBCAA (Sheet
02) of the service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this
AD, as applicable, on any airplane.
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(m) Credit for Previous Actions
This paragraph provides credit for the
actions specified in this AD, if those actions
were performed before the effective date of
this AD using the service information in
paragraphs (m)(1), (m)(2), and (m)(3) of this
AD.
(1) Airbus Service Bulletin A330–55–3043,
dated February 7, 2013.
(2) Airbus Service Bulletin A340–55–4039,
dated February 7, 2013.
(3) Airbus Service Bulletin A340–55–5007,
dated February 7, 2013.
(n) 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
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Jkt 238001
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.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0033, dated
February 4, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–0928.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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.
(i) Airbus Service Bulletin A330–55–3043,
Revision 1, dated August 20, 2014.
(ii) Airbus Service Bulletin A340–55–4039,
Revision 1, dated August 20, 2014.
(iii) Airbus Service Bulletin A340–55–
5007, Revision 1, dated August 20, 2014.
(3) 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.
(4) 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.
(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.
Issued in Renton, Washington, on
November 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–29851 Filed 11–25–15; 8:45 am]
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73963
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1048; Directorate
Identifier 2014–NM–055–AD; Amendment
39–18332; AD 2015–23–14]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F.28 Mark
0070 and 0100 airplanes. This AD was
prompted by reports that cracks can
occur in a frame of the tail section on
certain airplanes. This AD requires a
one-time detailed inspection of the
oblique frame 67–2 for any cracking,
and repair if necessary. We are issuing
this AD to detect and correct such
cracking, which could lead to failure of
the oblique frame 67–2, and consequent
loss of the structural integrity of the tail
section.
DATES: This AD becomes effective
January 4, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 4, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-1048 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.
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. 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
1048.
SUMMARY:
E:\FR\FM\27NOR1.SGM
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[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Rules and Regulations]
[Pages 73960-73963]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29851]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-AD;
Amendment 39-18333; AD 2015-24-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. This AD was prompted by a
report of skin disbonding on a composite side panel of a rudder
installed on an A310 airplane. This AD requires a review of the
maintenance records of the rudder to determine if any composite side
shell panel repair has been done; a thermography inspection limited to
the repair areas or complete side shells, as applicable, to identify
possible in-service rudder repairs, damages, or fluid ingress; and
applicable related investigative and corrective actions. We are issuing
this AD to detect and correct the rudder skin disbonding, which could
affect the structural integrity of the rudder, and could result in
reduced controllability of the airplane.
DATES: This AD becomes effective January 4, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 4,
2016.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0928 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.
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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0928.
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 by adding an AD that would apply to all Airbus Model A330-200
Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-
600 series airplanes. The NPRM published in the Federal Register on
December 29, 2014 (79 FR 77972).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0033, dated February 4, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500,
and A340-600 series airplanes. The MCAI states:
A case of skin disbonding was reported on a composite side panel
of a rudder installed on an A310 aeroplane.
The investigation results revealed that this disbonding started
from a skin panel area previously repaired in-service in accordance
with the Structural Repair Manual (SRM).
The initial damage has been identified as a disbonding between
the core and skin of the repaired area. This damage may not be
visually detectable and likely propagates during normal operation
due to the variation of pressure during ground-air-ground cycles.
Composite rudder side shell panels are also installed on A330
and A340 aeroplanes, which may have been repaired in-service using a
similar method.
This condition, if not detected and corrected, could affect the
structural integrity of the rudder, possibly resulting in reduced
control of the aeroplane.
For the reasons described above, this [EASA] AD requires a one-
time thermography inspection of a repaired rudder or a rudder whose
maintenance records are incomplete and, depending on findings,
accomplishment of applicable corrective and follow-up actions
[including repetitive inspections].
The related investigative actions in this AD include, as
applicable, an ultrasonic inspection, an elasticity laminate checker
inspection, a tap test inspection, detailed inspections, and
thermography inspections, and ventilation of the core. The repetitive
inspections include detailed inspections and thermography inspections.
The corrective actions in this AD include repairs.
The compliance time for the related investigative actions is before
further flight after accomplishing the applicable inspection required
by paragraph (g)(1) or (g)(2)(ii) of this AD.
The intervals for the repetitive inspections are either 900 flight
hours or 1,000 flight cycles, depending on the applicable conditions
identified in the service information.
The compliance times for the corrective actions range, depending on
the applicable conditions identified in the service information, from
before further flight to within 4,500 flight cycles but not to exceed
24 months after accomplishing the applicable inspection required by
paragraph (g)(1) or (g)(2)(ii) of this AD.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0928-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 77972, December 29, 2014) and the FAA's response to each comment.
Request To Use the Latest Service Information
American Airlines (AAL) and Delta Airlines (DAL) requested that we
revise the NPRM (79 FR 77972, December 29, 2014) to cite the latest
service information.
We agree with the commenters' request. Airbus has issued Airbus
Service Bulletin A330-55-3043, Revision 1, dated August 20, 2014,
Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20,
2014, and Airbus Service Bulletin A340-55-5007,
[[Page 73961]]
Revision 1, dated August 20, 2014. The new service information requires
no additional work, and there are no new actions required by this AD.
We have updated the AD with the latest service information, and we have
also added a credit paragraph for previous actions done before the
effective date of this AD using the service information cited in the
NPRM (79 FR 77972, December 29, 2014).
Request To Clarify the Structural Repair Manual Repairs That Are
Affected
AAL requested that the NPRM (79 FR 77972, December 29, 2014)
clarify the specific structural repair manual (SRM) repairs that are
affected. AAL stated that paragraph (j) of the proposed AD states
specific serial number ranges that are not affected by the AD provided
that it is determined that no repair has been accomplished on the
composite side shell panel of that rudder since first installation on
the airplane. AAL believes this last sentence is too broad and not in
line with the intent of the service information requirements. AAL
commented that stating no repair has been accomplished limits
acceptable repairs covered by an Airbus repair design approval sheet,
designated engineering representative repairs, and other SRM repairs
not affected by the improper practices that are the subject of the
NPRM. AAL stated that paragraphs (g)(1) and paragraph (l) of the
proposed AD list the affected SRM repairs in the service information
figures.
We agree with the commenter's request. We have revised paragraph
(j) of this AD to clarify the specific repairs accomplished as
described in the SRM procedures identified in Figure A-GBBAA (Sheet 01
and 02) or Figure A-GBCAA (Sheet 02) of the service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as
applicable.
Request To Add the Manufacturer Part Number
DAL requested that the NPRM (79 FR 77972, December 29, 2014)
include the manufacturer part numbers of the rudder serial numbers
specified in paragraph (j), which provides only a list of rudder serial
numbers not affected by the requirements of paragraphs (g) and (h) of
the proposed AD. DAL commented that in the event of future aircraft
acquisitions or rudder (component only) purchases, operators will need
the manufacturer part numbers associated with the listed serial numbers
to determine AD applicability.
We disagree with the commenter's request to add part numbers to
paragraph (j) of this AD. The rudder serial number, regardless of the
part number, is the key to identifying whether the rudder is not
affected. Only rudders that have certain serial numbers that meet the
conditions specified in paragraph (j) of this AD are exempt from the
actions required by paragraphs (g) and (h) of this AD. Airbus has
informed us that rudders with the same manufacturer part number might
or might not be affected; it is the serial number that determines
whether it is an affected rudder. We have not changed the AD in this
regard.
Conclusion
We reviewed the relevant data, considered 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 minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 77972, December 29, 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 77972, December 29, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus Service Bulletin A330-55-3043, Revision 1, dated
August 20, 2014.
Airbus Service Bulletin A340-55-4039, Revision 1, dated
August 20, 2014.
Airbus Service Bulletin A340-55-5007, Revision 1, dated
August 20, 2014.
The service information describes procedures for a review of the
maintenance records of the rudder to determine if any composite side
shell panel repair has been done; a thermography inspection limited to
the repair areas or complete side shells, as applicable, to identify
possible in-service rudder repairs, damages, or fluid ingress; and
applicable related investigative and corrective actions. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this AD.
Costs of Compliance
We estimate that this AD affects 55 airplanes of U.S. registry.
We also estimate that it would take about 45 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $210,375, or $3,825 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.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is 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.
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.
[[Page 73962]]
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-2014-0928; 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 adding the following new airworthiness
directive (AD):
2015-24-01 Airbus: Amendment 39-18333. Docket No. FAA-2014-0928;
Directorate Identifier 2014-NM-040-AD.
(a) Effective Date
This AD becomes effective January 4, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F,-243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
all manufacturer serial numbers.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a report of skin disbonding on a
composite side panel of a rudder installed on an A310 airplane. We
are issuing this AD to detect and correct the rudder skin
disbonding, which could affect the structural integrity of the
rudder, and could result in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Review the Maintenance Records
Within 24 months after the effective date of this AD: Review the
maintenance records of the rudder to determine if any composite side
shell panel repair has been accomplished on the rudder since first
installation on an airplane.
(1) If, based on the maintenance record review, any repair
identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA
(Sheet 02) of the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months
after the effective date of this AD, do a thermography inspection
for repair, damages, and fluid ingress, limited to the repaired
areas, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD:
(i) Airbus Service Bulletin A330-55-3043, Revision 1, dated
August 20, 2014 (for Model A330-201, -202, -203, -223, -223F, -243,
-243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes).
(ii) Airbus Service Bulletin A340-55-4039, Revision 1, dated
August 20, 2014 (for Model A340-211, -212, -213, -311, -312, and -
313 airplanes).
(iii) Airbus Service Bulletin A340-55-5007, Revision 1, dated
August 20, 2014 (for Model A340-541 and -642 airplanes).
(2) For a rudder for which maintenance records are unavailable
or incomplete, do the actions specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD:
(i) No later than 3 months before accomplishment of the
thermography inspection, as required by paragraph (g)(2)(ii) of this
AD, contact Airbus to request related rudder manufacturing data by
submitting the serial number of the rudder to Airbus.
(ii) Within 24 months after the effective date of this AD: Do a
thermography inspection for any repair on complete side shells to
identify and mark any repair, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.
(h) Related Investigative Actions, Corrective Actions, and Repetitive
Inspections
After the inspection as required by paragraph (g)(1) or (g)(2)
of this AD: At the applicable compliance times specified in
paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5
of the applicable service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD;
except as provided by paragraphs (i)(1) and (i)(2) of this AD.
Options provided in the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the
actions are acceptable for the corresponding requirements of this
paragraph provided that the related investigative and corrective
actions are done at the applicable times specified in paragraph
1.E., ``Compliance,'' of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD,
including applicable repetitive inspection intervals, except as
required by paragraphs (i)(1) and (i)(2) of this AD. Thereafter
repeat the inspections of the restored and repaired areas at the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD.
(i) Exceptions to the Service Information
(1) Where the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a
compliance time relative to the date of the service information,
this AD requires compliance within the specified compliance time
after the effective date of this AD.
(2) If the service information in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD specifies to contact Airbus: At the
applicable compliance times specified in paragraph 1.E.,
``Compliance,'' of the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, repair 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).
(j) Provisions for Certain Airplanes
Airplanes fitted with a rudder having a serial number (S/N) that
is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/
N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS-
3525 inclusive, S/N TS-4001 through S/N TS-4170 inclusive, S/N TS-
6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS-
5138 inclusive, are not
[[Page 73963]]
affected by the requirements of paragraphs (g) and (h) of this AD
provided that it is determined that no repair has been accomplished
as described in the procedures identified in Figure A-GBBAA (Sheet
01 and 02) or Figure A-GBCAA (Sheet 02) of the service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as
applicable, on the composite side shell panel of that rudder since
first installation on an airplane.
(k) Parts Installation Limitations
As of the effective date of this AD, no person may install, on
any airplane, a rudder, unless the record review and thermography
inspection specified in paragraph (g) of this AD has been done on
that rudder and thereafter all applicable related investigative
actions, repetitive inspections, and corrective actions are done as
required by paragraph (h) of this AD, except as provided in
paragraph (j) of this AD.
(l) Repair Prohibition
As of the effective date of this AD, no person may accomplish a
side shell repair on any rudder using a structure repair manual
procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure
A-GBCAA (Sheet 02) of the service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable,
on any airplane.
(m) Credit for Previous Actions
This paragraph provides credit for the actions specified in this
AD, if those actions were performed before the effective date of
this AD using the service information in paragraphs (m)(1), (m)(2),
and (m)(3) of this AD.
(1) Airbus Service Bulletin A330-55-3043, dated February 7,
2013.
(2) Airbus Service Bulletin A340-55-4039, dated February 7,
2013.
(3) Airbus Service Bulletin A340-55-5007, dated February 7,
2013.
(n) 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: 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 EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0033, dated February 4,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0928.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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.
(i) Airbus Service Bulletin A330-55-3043, Revision 1, dated
August 20, 2014.
(ii) Airbus Service Bulletin A340-55-4039, Revision 1, dated
August 20, 2014.
(iii) Airbus Service Bulletin A340-55-5007, Revision 1, dated
August 20, 2014.
(3) 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.
(4) 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.
(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/ibr-locations.html.
Issued in Renton, Washington, on November 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-29851 Filed 11-25-15; 8:45 am]
BILLING CODE 4910-13-P
