Airworthiness Directives; Airbus Airplanes, 80239-80242 [2015-31714]
Download as PDF
<![CDATA[
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
conditions specified in both paragraphs (h)(1)
and (h)(2) of this AD are met.
(1) The action was performed before the
effective date of this AD using Bombardier
Service Bulletin 605–24–007, Bombardier
Service Bulletin 604–24–026, or Bombardier
Service Bulletin 601–0625, all dated
September 18, 2012. This service information
is not incorporated by reference in this AD.
(2) The action specified in Service Request
for Product Support Action (SRPSA) 27512,
SRPSA 30806, SRPSA 32727, SRPSA 32864,
or SRPSA 33161 has not been done.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, 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 New York ACO, send it to
ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO,
1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7300; fax
516–794–553. 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, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
tkelley on DSK3SPTVN1PROD with RULES
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–05, dated
January 20, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/#!documentDetail;D=
FAA-2014-0625-0003.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) 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) Bombardier Service Bulletin 605–24–
007, Revision 01, dated January 13, 2014.
(ii) Bombardier Service Bulletin 604–24–
026, Revision 01, dated January 13, 2014.
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
(iii) Bombardier Service Bulletin 601–0625,
Revision 01, dated January 13, 2014.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote
´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.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.
80239
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
combined with failure of the horizontal
beam, could lead to collapse of the
cockpit panel, and reduced
controllability of the airplane.
DATES: This AD becomes effective
January 28, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 28, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0083; 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 final rule, 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–2015–
0083.
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:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200, A330–200
Freighter, and A330–300 series
airplanes; and all Model A340–200 and
A340–300 series airplanes. This AD was
prompted by reports that a bracket that
attaches the cockpit instrument panel to
the airplane structure does not sustain
the fatigue loads of the design service
goal. This AD requires repetitive
inspections of that bracket for cracking
and to determine if both lugs are fully
broken, an inspection for cracking of an
adjacent bracket if necessary, and
corrective actions if necessary. This AD
also provides an optional modification,
which terminates the repetitive
inspections. We are issuing this AD to
detect and correct cracking on a bracket
of the cockpit instrument panel, which,
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A330–
200, A330–200 Freighter, and A330–300
series airplanes; and all Model A340–
200 and A340–300 series airplanes. The
NPRM published in the Federal
Register on February 13, 2015 (80 FR
7989).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0127, dated May 15,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200, A330–200 Freighter,
Issued in Renton, Washington on
December 8, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–31604 Filed 12–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0083; Directorate
Identifier 2014–NM–131–AD; Amendment
39–18347; AD 2015–25–09]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
AGENCY:
SUMMARY:
PO 00000
Frm 00033
Fmt 4700
Sfmt 4700
E:\FR\FM\24DER1.SGM
24DER1
80240
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
and A330–300 series airplanes; and all
Model A340–200, and A340–300 series
airplanes. The MCAI states:
During flight tests, high stress levels have
been measured on the bracket No 6 which
attaches the cockpit instrument panel to the
aeroplane structure, apparently introduced
through the nose landing gear due to bumps
on the runway. Airbus determined that the
bracket does not sustain the fatigue loads
during the Design Service Goal (DSG).
This condition, if not detected and
corrected, combined with failure of the
horizontal beam, could lead to collapse of the
cockpit panel, possibly resulting in reduced
control of the aeroplane.
To address this potential unsafe condition,
Airbus developed a program to inspect the
condition of the affected cockpit instrument
panel bracket No 6, and designed a stronger
(reinforced titanium undrilled) bracket. The
new bracket can be installed in-service
through Airbus Service Bulletin (SB) A330–
25–3548 or SB A340–25–4354, as applicable
to aeroplane type.
For the reasons described above, this
[EASA] AD requires repetitive inspections of
the cockpit instrument panel bracket No 6
and, depending on findings, the
accomplishment of applicable corrective
actions. This [EASA] AD also provides the
installation of the stronger bracket as
optional terminating action for the repetitive
actions required by this [EASA] AD.
The corrective actions include replacing
bracket No. 6 and bracket No. 7 with
serviceable parts, and repair, as
applicable.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-00830002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
The following presents the comment
received on the NPRM (80 FR 7989,
February 13, 2015) and the FAA’s
response.
tkelley on DSK3SPTVN1PROD with RULES
Request To Identify Part Numbers in
Paragraphs (g) and (h)
Delta Airlines requested that
paragraphs (g) and (h) of the proposed
AD (80 FR 7989, February 13, 2015) be
revised to specify the part numbers of
the affected brackets. Delta suggested
that paragraph (g) of the proposed AD be
revised to include the part number after
the reference to bracket No. 6 (part
number (P/N) F2511012820000, premodification Number 55128S18242; and
P/N F2511373420000, post-modification
Number 55128S18242). Delta also
requested that paragraph (h)(2) of the
proposed AD be revised to include the
part number after bracket No. 6 (P/N
F2511012820000, pre-modification
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
Number 55128S18242; and P/N
F2511373420000, post-modification
Number 55128S18242) and bracket No.
7 (P/N F2511012820000, premodification Number 55128S18242; and
P/N F2511373420000, post-modification
Number 55128S18242). Delta stated that
Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014,
specifies to inspect only P/N
F2511012820000, pre-modification
Number 55128S18242, and P/N
F2511373420000, post-modification
Number 55128S18242, and identifies
only those part numbers as ‘‘affected’’
brackets that are used on both bracket
No. 6 and bracket No. 7.
We agree to include the part numbers
identified by the commenter in
paragraphs (g) and (h)(2) of this AD. We
have also included the part numbers in
paragraphs (h)(1) and (h)(2)(i) of this
AD. The ‘‘Reason/Description/
Operational Consequences’’ section of
Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014,
specifies to inspect P/N
F2511012820000, pre-modification
Number 55128S18242, and P/N
F2511373420000, post-modification
Number 55128S18242. Also, the
Accomplishment Instructions of that
service bulletin specify to replace P/N
F2511012820000 or P/N
F2511373420000, as applicable. We
contacted Airbus for verification that
only those part numbers are considered
to be ‘‘affected’’ brackets and Airbus
confirmed that only those part numbers
are affected. The same affected and
replacement parts are used on both
Airbus Model A330–200, A330–200
Freighter, and A330–300 series
airplanes; and A340–200 and A340–300
series airplanes.
Additional Change to This AD
A typographical error in paragraph
(c)(1) of the proposed AD (80 FR 7989,
February 13, 2015) has been corrected in
this final rule. Paragraph (c)(1) of the
proposed AD inadvertently included
Model A330–313 airplanes instead of
Model A330–343 airplanes. The
SUMMARY section and preamble of the
NPRM stated that the applicability
included Model A330–300 series
airplanes, which include Model A330–
343 airplanes.
Conclusion
We reviewed the relevant data,
considered 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:
PO 00000
Frm 00034
Fmt 4700
Sfmt 4700
• Are consistent with the intent that
was proposed in the NPRM (80 FR 7989,
February 13, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 7989,
February 13, 2015).
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 A330–25–
3538, Revision 02, dated April 24, 2014,
which provides procedures for
inspection of cockpit instrument panel
bracket 6.
• Airbus Service Bulletin A330–25–
3548, dated October 31, 2013, which
provides procedures for replacement of
cockpit instrument panel bracket 6 with
a reinforced titanium bracket.
• Airbus Service Bulletin A340–25–
4351, Revision 01, dated January 31,
2014, which provides procedures for
inspection of cockpit instrument panel
bracket 6.
• Airbus Service Bulletin A340–25–
4354, dated October 31, 2013, which
provides procedures for replacement of
cockpit instrument panel bracket 6 with
a reinforced titanium bracket.
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.
Costs of Compliance
We estimate that this AD affects 76
airplanes of U.S. registry.
We also estimate that it will take
about 8 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $51,680, or $680 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the follow-on repairs
specified in this AD.
In addition, we estimate that any
necessary replacements will take about
23 work-hours and require parts costing
$0, for a cost of $1,955 per product. We
have no way of determining the number
of aircraft that might need these actions.
We estimate that the optional
modification will take about 9 work
hours and require parts costing $1,770,
for a cost of $2,535.
E:\FR\FM\24DER1.SGM
24DER1
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
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.
tkelley on DSK3SPTVN1PROD with RULES
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0083; 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.
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
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):
■
2015–25–09 Airbus: Amendment 39–18347.
Docket No. FAA–2015–0083; Directorate
Identifier 2014–NM–131–AD.
(a) Effective Date
This AD becomes effective January 28,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330–201, –202, –203, –223,
–243, –223F, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes,
all manufacturer serial numbers except those
on which Airbus Modification 203287 has
been embodied in production.
(2) Model A340–211, –212, –213, –311,
–312, and –313 airplanes, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Reason
This AD was prompted by reports that a
bracket that attaches the cockpit instrument
panel to the airplane structure does not
sustain the fatigue loads of the design service
goal. We are issuing this AD to detect and
correct cracking on a bracket of the cockpit
instrument panel, which, combined with
failure of the horizontal beam, could lead to
collapse of the cockpit panel, and reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection of Bracket No. 6 of the Cockpit
Instrument Panel
At the latest of the times specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD:
Do a detailed inspection of bracket No. 6
(part number (P/N) F2511012820000, pre-
PO 00000
Frm 00035
Fmt 4700
Sfmt 4700
80241
modification Number 55128S18242; or P/N
F2511373420000, post-modification Number
55128S18242) of the cockpit instrument
panel for cracking and to determine if both
bracket lugs are fully broken, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; or Airbus
Service Bulletin A340–25–4351, Revision 01,
dated January 31, 2014; as applicable. Repeat
the inspection thereafter at intervals not to
exceed 2,600 flight cycles.
(1) Prior to accumulating 17,200 total flight
cycles since the airplane’s first flight.
(2) Prior to bracket No. 6 of the cockpit
instrument panel accumulating 17,200 total
flight cycles since installation on an airplane.
(3) Within 500 flight cycles after the
effective date of this AD.
(h) Inspection and Corrective Actions
(1) If, during any inspection required by
paragraph (g) of this AD, any cracking of
bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N
F2511373420000, Post-modification Number
55128S18242) of the cockpit instrument
panel is found, and both bracket lugs are not
fully broken: Within 2,600 flight cycles after
that inspection, replace bracket No. 6 of the
cockpit instrument panel with a serviceable
part, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–25–3538, Revision 02,
dated April 24, 2014; or Airbus Service
Bulletin A340–25–4351, Revision 01, dated
January 31, 2014; as applicable. Replacement
of bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N
F2511373420000, post-modification Number
55128S18242) of the cockpit instrument
panel does not constitute terminating action
for the repetitive inspections required by
paragraph (g) of this AD.
(2) If, during any inspection required by
paragraph (g) of this AD, any cracking of
bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N
F2511373420000, Post-modification Number
55128S18242) of the cockpit instrument
panel is found and both bracket lugs are fully
broken: Before further flight, do a detailed
inspection of bracket No. 7 (P/N
F2511012820000, pre-modification Number
55128S18242; or P/N F2511373420000, Postmodification Number 55128S18242) of the
cockpit instrument panel for cracking, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
25–3538, Revision 02, dated April 24, 2014;
or Airbus Service Bulletin A340–25–4351,
Revision 01, dated January 31, 2014; as
applicable.
(i) If, during the inspection required by
paragraph (h)(2) of this AD, no cracking is
found in bracket No. 7 of the cockpit
instrument panel: Before further flight,
replace bracket No. 6 and bracket No. 7 of the
cockpit instrument panel with serviceable
parts, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–25–3538, Revision 02,
dated April 24, 2014; or Airbus Service
Bulletin A340–25–4351, Revision 01, dated
January 31, 2014; as applicable. Replacement
of bracket No. 6 (P/N F2511012820000, pre-
E:\FR\FM\24DER1.SGM
24DER1
80242
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
modification Number 55128S18242; or P/N
F2511373420000, post-modification Number
55128S18242) of the cockpit instrument
panel does not constitute terminating action
for the repetitive inspections required by
paragraph (g) of this AD.
(ii) If, during the inspection required by
paragraph (h)(2) of this AD, any cracking is
found in bracket No. 7 of the cockpit
instrument panel: Although Airbus Service
Bulletin A330–25–3538, Revision 02, dated
April 24, 2014; and Airbus Service Bulletin
A340–25–4351, Revision 01, dated January
31, 2014; specify to contact Airbus for repair
instructions, and specify that action as ‘‘RC’’
(Required for Compliance), repair the
cracking before further flight using a repair
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).
(i) Optional Terminating Modification for
Paragraph (g) of This AD
Modifying an airplane by replacing bracket
No. 6 of the cockpit instrument panel with
a new, reinforced bracket, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–25–3548, dated
October 31, 2013; or Airbus Service Bulletin
A340–25–4354, dated October 31, 2013; as
applicable; terminates the repetitive
inspections required by paragraph (g) of this
AD.
tkelley on DSK3SPTVN1PROD with RULES
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraph (j)(1),
(j)(2), or (j)(3) of this AD, which is not
incorporated by reference in this AD.
(1) Airbus Service Bulletin A330–25–3538,
dated September 10, 2013.
(2) Airbus Service Bulletin A330–25–3538,
Revision 01, dated April 24, 2014.
(3) Airbus Service Bulletin A340–25–4351,
dated September 10, 2014.
(k) 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
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
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.
(3) Required for Compliance (RC): Except
as required by paragraph (h)(2)(ii) of this AD,
if Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; or Airbus
Service Bulletin A340–25–4351, Revision 01,
dated January 31, 2014; contain procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures and tests that
are not identified as RC are recommended.
Those procedures and tests that are not
identified as RC may be deviated from, using
accepted methods in accordance with the
operators maintenance or inspection program
without obtaining approval of an AMOC,
provided the procedures and tests identified
as RC can be done and the airplane can be
put back in an airworthy condition. Any
substitutions or changes to procedures or
tests identified as RC require approval of an
AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0127, dated
May 15, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2015-0083-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 A330–25–3538,
Revision 02, dated April 24, 2014.
(ii) Airbus Service Bulletin A330–25–3548,
dated October 31, 2013.
(iii) Airbus Service Bulletin A340–25–
4351, Revision 01, dated January 31, 2014.
(iv) Airbus Service Bulletin A340–25–
4354, dated October 31, 2013.
(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
PO 00000
Frm 00036
Fmt 4700
Sfmt 4700
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
December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–31714 Filed 12–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0828; Directorate
Identifier 2014–NM–146–AD; Amendment
39–18341; AD 2015–25–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–23–
03, which applies to certain The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, and 747SR series
airplanes. AD 2013–23–03 required a
detailed inspection of certain attach
fittings for a cylindrical defect, and
replacement if necessary. For certain
airplanes, this new AD requires new
inspections of the inboard actuator
attach fittings for machining defects,
and overhaul or replacement if
necessary. This new AD also limits the
compliance time for doing the
replacement for certain other airplanes.
This AD was prompted by a report that
a machining defect was also found on
some of the actuator assemblies
inspected during manufacture. This
defect could lead to fatigue cracking and
subsequent fracture. We are issuing this
AD to detect and correct defective
inboard actuator attach fittings which,
combined with loss of the outboard
actuator load path, could result in
uncontrolled retraction of the outboard
flap, damage to flight control systems,
and consequent reduced controllability
of the airplane.
DATES: This AD is effective January 28,
2016.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
E:\FR\FM\24DER1.SGM
24DER1
]]>Agencies
[Federal Register Volume 80, Number 247 (Thursday, December 24, 2015)]
[Rules and Regulations]
[Pages 80239-80242]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31714]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0083; Directorate Identifier 2014-NM-131-AD;
Amendment 39-18347; AD 2015-25-09]
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 certain
Airbus Model A330-200, A330-200 Freighter, and A330-300 series
airplanes; and all Model A340-200 and A340-300 series airplanes. This
AD was prompted by reports that a bracket that attaches the cockpit
instrument panel to the airplane structure does not sustain the fatigue
loads of the design service goal. This AD requires repetitive
inspections of that bracket for cracking and to determine if both lugs
are fully broken, an inspection for cracking of an adjacent bracket if
necessary, and corrective actions if necessary. This AD also provides
an optional modification, which terminates the repetitive inspections.
We are issuing this AD to detect and correct cracking on a bracket of
the cockpit instrument panel, which, combined with failure of the
horizontal beam, could lead to collapse of the cockpit panel, and
reduced controllability of the airplane.
DATES: This AD becomes effective January 28, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 28,
2016.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-0083; 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 final rule, 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-2015-
0083.
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 certain Airbus Model A330-
200, A330-200 Freighter, and A330-300 series airplanes; and all Model
A340-200 and A340-300 series airplanes. The NPRM published in the
Federal Register on February 13, 2015 (80 FR 7989).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0127, dated May 15, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200, A330-200 Freighter,
[[Page 80240]]
and A330-300 series airplanes; and all Model A340-200, and A340-300
series airplanes. The MCAI states:
During flight tests, high stress levels have been measured on
the bracket No 6 which attaches the cockpit instrument panel to the
aeroplane structure, apparently introduced through the nose landing
gear due to bumps on the runway. Airbus determined that the bracket
does not sustain the fatigue loads during the Design Service Goal
(DSG).
This condition, if not detected and corrected, combined with
failure of the horizontal beam, could lead to collapse of the
cockpit panel, possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition, Airbus developed a
program to inspect the condition of the affected cockpit instrument
panel bracket No 6, and designed a stronger (reinforced titanium
undrilled) bracket. The new bracket can be installed in-service
through Airbus Service Bulletin (SB) A330-25-3548 or SB A340-25-
4354, as applicable to aeroplane type.
For the reasons described above, this [EASA] AD requires
repetitive inspections of the cockpit instrument panel bracket No 6
and, depending on findings, the accomplishment of applicable
corrective actions. This [EASA] AD also provides the installation of
the stronger bracket as optional terminating action for the
repetitive actions required by this [EASA] AD.
The corrective actions include replacing bracket No. 6 and bracket No.
7 with serviceable parts, and repair, as applicable.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0083-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. The following
presents the comment received on the NPRM (80 FR 7989, February 13,
2015) and the FAA's response.
Request To Identify Part Numbers in Paragraphs (g) and (h)
Delta Airlines requested that paragraphs (g) and (h) of the
proposed AD (80 FR 7989, February 13, 2015) be revised to specify the
part numbers of the affected brackets. Delta suggested that paragraph
(g) of the proposed AD be revised to include the part number after the
reference to bracket No. 6 (part number (P/N) F2511012820000, pre-
modification Number 55128S18242; and P/N F2511373420000, post-
modification Number 55128S18242). Delta also requested that paragraph
(h)(2) of the proposed AD be revised to include the part number after
bracket No. 6 (P/N F2511012820000, pre-modification Number 55128S18242;
and P/N F2511373420000, post-modification Number 55128S18242) and
bracket No. 7 (P/N F2511012820000, pre-modification Number 55128S18242;
and P/N F2511373420000, post-modification Number 55128S18242). Delta
stated that Airbus Service Bulletin A330-25-3538, Revision 02, dated
April 24, 2014, specifies to inspect only P/N F2511012820000, pre-
modification Number 55128S18242, and P/N F2511373420000, post-
modification Number 55128S18242, and identifies only those part numbers
as ``affected'' brackets that are used on both bracket No. 6 and
bracket No. 7.
We agree to include the part numbers identified by the commenter in
paragraphs (g) and (h)(2) of this AD. We have also included the part
numbers in paragraphs (h)(1) and (h)(2)(i) of this AD. The ``Reason/
Description/Operational Consequences'' section of Airbus Service
Bulletin A330-25-3538, Revision 02, dated April 24, 2014, specifies to
inspect P/N F2511012820000, pre-modification Number 55128S18242, and P/
N F2511373420000, post-modification Number 55128S18242. Also, the
Accomplishment Instructions of that service bulletin specify to replace
P/N F2511012820000 or P/N F2511373420000, as applicable. We contacted
Airbus for verification that only those part numbers are considered to
be ``affected'' brackets and Airbus confirmed that only those part
numbers are affected. The same affected and replacement parts are used
on both Airbus Model A330-200, A330-200 Freighter, and A330-300 series
airplanes; and A340-200 and A340-300 series airplanes.
Additional Change to This AD
A typographical error in paragraph (c)(1) of the proposed AD (80 FR
7989, February 13, 2015) has been corrected in this final rule.
Paragraph (c)(1) of the proposed AD inadvertently included Model A330-
313 airplanes instead of Model A330-343 airplanes. The SUMMARY section
and preamble of the NPRM stated that the applicability included Model
A330-300 series airplanes, which include Model A330-343 airplanes.
Conclusion
We reviewed the relevant data, considered 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 (80 FR 7989, February 13, 2015) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 7989, February 13, 2015).
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 A330-25-3538, Revision 02, dated
April 24, 2014, which provides procedures for inspection of cockpit
instrument panel bracket 6.
Airbus Service Bulletin A330-25-3548, dated October 31,
2013, which provides procedures for replacement of cockpit instrument
panel bracket 6 with a reinforced titanium bracket.
Airbus Service Bulletin A340-25-4351, Revision 01, dated
January 31, 2014, which provides procedures for inspection of cockpit
instrument panel bracket 6.
Airbus Service Bulletin A340-25-4354, dated October 31,
2013, which provides procedures for replacement of cockpit instrument
panel bracket 6 with a reinforced titanium bracket.
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.
Costs of Compliance
We estimate that this AD affects 76 airplanes of U.S. registry.
We also estimate that it will take about 8 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $51,680, or $680 per product.
We have received no definitive data that would enable us to provide
cost estimates for the follow-on repairs specified in this AD.
In addition, we estimate that any necessary replacements will take
about 23 work-hours and require parts costing $0, for a cost of $1,955
per product. We have no way of determining the number of aircraft that
might need these actions.
We estimate that the optional modification will take about 9 work
hours and require parts costing $1,770, for a cost of $2,535.
[[Page 80241]]
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-2015-0083; 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):
2015-25-09 Airbus: Amendment 39-18347. Docket No. FAA-2015-0083;
Directorate Identifier 2014-NM-131-AD.
(a) Effective Date
This AD becomes effective January 28, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330-201, -202, -203, -223, -243, -223F, -243F, -301,
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all
manufacturer serial numbers except those on which Airbus
Modification 203287 has been embodied in production.
(2) Model A340-211, -212, -213, -311, -312, and -313 airplanes,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.
(e) Reason
This AD was prompted by reports that a bracket that attaches the
cockpit instrument panel to the airplane structure does not sustain
the fatigue loads of the design service goal. We are issuing this AD
to detect and correct cracking on a bracket of the cockpit
instrument panel, which, combined with failure of the horizontal
beam, could lead to collapse of the cockpit panel, and reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of Bracket No. 6 of the Cockpit Instrument Panel
At the latest of the times specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD: Do a detailed inspection of bracket
No. 6 (part number (P/N) F2511012820000, pre-modification Number
55128S18242; or P/N F2511373420000, post-modification Number
55128S18242) of the cockpit instrument panel for cracking and to
determine if both bracket lugs are fully broken, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-25-
3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin
A340-25-4351, Revision 01, dated January 31, 2014; as applicable.
Repeat the inspection thereafter at intervals not to exceed 2,600
flight cycles.
(1) Prior to accumulating 17,200 total flight cycles since the
airplane's first flight.
(2) Prior to bracket No. 6 of the cockpit instrument panel
accumulating 17,200 total flight cycles since installation on an
airplane.
(3) Within 500 flight cycles after the effective date of this
AD.
(h) Inspection and Corrective Actions
(1) If, during any inspection required by paragraph (g) of this
AD, any cracking of bracket No. 6 (P/N F2511012820000, pre-
modification Number 55128S18242; or P/N F2511373420000, Post-
modification Number 55128S18242) of the cockpit instrument panel is
found, and both bracket lugs are not fully broken: Within 2,600
flight cycles after that inspection, replace bracket No. 6 of the
cockpit instrument panel with a serviceable part, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-25-
3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin
A340-25-4351, Revision 01, dated January 31, 2014; as applicable.
Replacement of bracket No. 6 (P/N F2511012820000, pre-modification
Number 55128S18242; or P/N F2511373420000, post-modification Number
55128S18242) of the cockpit instrument panel does not constitute
terminating action for the repetitive inspections required by
paragraph (g) of this AD.
(2) If, during any inspection required by paragraph (g) of this
AD, any cracking of bracket No. 6 (P/N F2511012820000, pre-
modification Number 55128S18242; or P/N F2511373420000, Post-
modification Number 55128S18242) of the cockpit instrument panel is
found and both bracket lugs are fully broken: Before further flight,
do a detailed inspection of bracket No. 7 (P/N F2511012820000, pre-
modification Number 55128S18242; or P/N F2511373420000, Post-
modification Number 55128S18242) of the cockpit instrument panel for
cracking, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24,
2014; or Airbus Service Bulletin A340-25-4351, Revision 01, dated
January 31, 2014; as applicable.
(i) If, during the inspection required by paragraph (h)(2) of
this AD, no cracking is found in bracket No. 7 of the cockpit
instrument panel: Before further flight, replace bracket No. 6 and
bracket No. 7 of the cockpit instrument panel with serviceable
parts, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; or
Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31,
2014; as applicable. Replacement of bracket No. 6 (P/N
F2511012820000, pre-
[[Page 80242]]
modification Number 55128S18242; or P/N F2511373420000, post-
modification Number 55128S18242) of the cockpit instrument panel
does not constitute terminating action for the repetitive
inspections required by paragraph (g) of this AD.
(ii) If, during the inspection required by paragraph (h)(2) of
this AD, any cracking is found in bracket No. 7 of the cockpit
instrument panel: Although Airbus Service Bulletin A330-25-3538,
Revision 02, dated April 24, 2014; and Airbus Service Bulletin A340-
25-4351, Revision 01, dated January 31, 2014; specify to contact
Airbus for repair instructions, and specify that action as ``RC''
(Required for Compliance), repair the cracking before further flight
using a repair 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).
(i) Optional Terminating Modification for Paragraph (g) of This AD
Modifying an airplane by replacing bracket No. 6 of the cockpit
instrument panel with a new, reinforced bracket, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-25-
3548, dated October 31, 2013; or Airbus Service Bulletin A340-25-
4354, dated October 31, 2013; as applicable; terminates the
repetitive inspections required by paragraph (g) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using the service information
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, which
is not incorporated by reference in this AD.
(1) Airbus Service Bulletin A330-25-3538, dated September 10,
2013.
(2) Airbus Service Bulletin A330-25-3538, Revision 01, dated
April 24, 2014.
(3) Airbus Service Bulletin A340-25-4351, dated September 10,
2014.
(k) 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.
(3) Required for Compliance (RC): Except as required by
paragraph (h)(2)(ii) of this AD, if Airbus Service Bulletin A330-25-
3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin
A340-25-4351, Revision 01, dated January 31, 2014; contain
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures and tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from, using
accepted methods in accordance with the operators maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0127, dated May 15, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-
2015-0083-0002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 A330-25-3538, Revision 02, dated
April 24, 2014.
(ii) Airbus Service Bulletin A330-25-3548, dated October 31,
2013.
(iii) Airbus Service Bulletin A340-25-4351, Revision 01, dated
January 31, 2014.
(iv) Airbus Service Bulletin A340-25-4354, dated October 31,
2013.
(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 December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-31714 Filed 12-23-15; 8:45 am]
BILLING CODE 4910-13-P
