Airworthiness Directives; Airbus Airplanes, 75833-75836 [2012-29992]
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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
(2) If the HP/IP turbine bearing support oil
feed tube outer heat shield is not present,
accept the module as compliant. No further
action is required.
DEPARTMENT OF TRANSPORTATION
(h) Mandatory Terminating Action
As mandatory terminating action to the
repetitive inspections required by this AD,
install a revised HP/IP turbine bearing
support structure, at the next 05 Module
overhaul after the effective date of this AD,
in accordance with either:
(1) Sections 3.B (1)(a) through 3.B (1)(f) of
RR Service Bulletin (SB) No. RB.211–72–
F117, Revision 2, dated September 25, 2006;
or
(2) Sections 3.B (1)(a) through 3.B (1)(e)
and 3.B (2)(a) of RR SB No. RB.211–72–F227,
Revision 1, dated October 8, 2007.
(i) Definition
For the purpose of this AD, ‘‘next 05
Module overhaul’’ is any time that the HP/
IP turbine internal oil tubes have been
exposed and the HP/IP turbine bearing
support oil feed tube heat shields are
subjected to visual inspection.
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(k) Related Information
(1) For more information about this AD,
contact Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238 7154; fax: 781–238 7199;
email: robert.c.morlath@faa.gov.
(2) Refer to European Aviation Safety
Agency AD 2012–0201, dated September 26,
2012, for related information.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Rolls-Royce plc Alert Service Bulletin
No. RB.211–72–AG873, dated February 27,
2012, approved for IBR January 10, 2013.
(ii) Reserved.
(3) The following service information was
approved for IBR on December 14, 2007 (72
FR 67568, November 29, 2007).
(i) Rolls-Royce plc Service Bulletin No.
RB.211–72–F117, Revision 2, dated
September 25, 2006.
(ii) Rolls-Royce plc Service Bulletin No.
RB.211–72–F227, Revision 1, dated October
8, 2007.
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Discussion
Issued in Burlington, Massachusetts, on
December 4, 2012.
Colleen M. D’Alessandro,
Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2012–30650 Filed 12–21–12; 8:45 am]
BILLING CODE 4910–13–P
14 CFR Part 39
(j) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make
your request.
04:58 Dec 22, 2012
This AD becomes effective
January 30, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 30, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of April 15, 2010 (75 FR
11435, March 11, 2010).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
(g) Repetitive Inspections
If the HP/IP turbine bearing support oil
feed tube outer heat shield is present,
perform repetitive inspections of the HP/IP
turbine bearing support oil feed tube, in
accordance with paragraphs 3.A (2)(b)
through 3.A (2)(f) of RR ASB No. RB.211–72–
AG873, dated February 27, 2012.
VerDate Mar<15>2010
(4) For service information identified in
this AD, contact Rolls-Royce plc, Corporate
Communications, P.O. Box 31, Derby,
England, DE248BJ, phone: 011–44–1332–
242424; fax: 011–44–1332–245418; or email:
https://www.rolls-royce.com/contact/
civil_team.jsp.
(5) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(6) You may view this service information
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.
75833
[Docket No. FAA–2012–0858; Directorate
Identifier 2011–NM–183–AD; Amendment
39–17287; AD 2012–25–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Airbus Model A300 B4–2C, B4–
103, and B4–203 airplanes; and Model
A300 B4–601, B4–603, B4–620, B4–622,
B4–605R, and B4–622R airplanes. That
AD currently requires performing a onetime detailed visual inspection of the
forward fitting at frame (FR) 40 on both
sides of the airplane for cracks, and
repair if necessary. This new AD
requires repetitive detailed inspections
of the forward fitting at FR 40 without
nut removal, and a one-time eddy
current or liquid penetrant inspection of
the forward fitting at FR 40 with nut
removal, and repair if necessary. This
AD was prompted by reports that new
cracks were found in the FR 40 forward
fitting. We are issuing this AD to detect
and correct cracking of the FR 40
forward fitting, which could result in a
deterioration of the structural integrity
of the frame.
SUMMARY:
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DATES:
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on August 27, 2012 (77 FR
51717), and proposed to supersede AD
2010–06–05, Amendment 39–16229 (75
FR 11435, March 11, 2010). That NPRM
proposed to correct an unsafe condition
for the specified products. The
Mandatory Continuing Airworthiness
Information (MCAI) states:
One A300–600 aeroplane operator reported
that, during a routine inspection, a crack was
found in the right hand frame (FR) 40
forward fitting between stringer 32 and
stringer 33. The subject aeroplane had
previously been modified in accordance with
Airbus SB A300–57–6053 (Mod. 10453).
Therefore and pending completion of the
full analysis using a refined Finite Element
Model, EASA [European Aviation Safety
Agency] issued AD 2009–0094 [which
corresponds with FAA AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March
11, 2010)] to require a one-time Detailed
Visual Inspection (DVI) of the post-SB A300–
57–6053 A300–600 aeroplanes and post-SB
A300–53–0297 A300 aeroplanes in order to
ensure the structural integrity of frame 40.
During a recent maintenance check, on two
aeroplanes (one A300B4 and one A300–600),
cracks were found in the FR 40 forward
fitting.
These new crack findings are considered as
unexpected, since they were found after:
—Application of modification SB A300–57–
6053 or SB A300–53–0297 which cancels
the inspection programme, and
—Accomplishment of EASA AD 2009–0094.
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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
For the reasons described above, this new
[EASA] AD, which supersedes EASA AD
2009–0094, requires repetitive DVI of the FR
40 forward fitting (without nut removal),
accomplishment of a one time Eddy Current
(EC) inspection or liquid penetrant
inspection of this area (with nut removal)
and, depending on findings, the
accomplishment of associated corrective
action [repair if any cracking found]. Passing
the EC or liquid penetrant inspection
constitutes terminating action for the
repetitive DVI.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 51717, August 27, 2012), or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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Costs of Compliance
We estimate that this AD will affect
about 134 products of U.S. registry.
The actions that are required by AD
2010–06–05, Amendment 39–16229 (75
FR 11435, March 11, 2010), and retained
in this AD take about 3 work-hours per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the currently
required actions is $255 per product.
We estimate that it will take about 3
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $34,170, or $255 per
product.
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
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04:58 Dec 22, 2012
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that is likely to exist or develop on
products identified in this rulemaking
action.
2010–06–05, Amendment 39–16229 (75
FR 11435, March 11, 2010), and adding
the following new AD:
Regulatory Findings
2012–25–06 Airbus: Amendment 39–17287.
Docket No. FAA–2012–0858; Directorate
Identifier 2011–NM–183–AD.
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at
https://www.regulations.gov; or in person
at the Docket Operations office between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains the NPRM (77 FR
51717, August 27, 2012), 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. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
■
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(a) Effective Date
This airworthiness directive (AD) becomes
effective January 30, 2013.
(b) Affected ADs
This AD supersedes AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March
11, 2010).
(c) Applicability
This AD applies to Airbus airplanes,
certificated in any category, as identified in
paragraphs (c)(1) and (c)(2) of this AD. For
airplanes on which Airbus Service Bulletin
A300–53–0297 or A300–57–6053 (Airbus
Modification 10453), as applicable, has been
incorporated as a corrective action (repair
following crack finding), no action is
required by this AD.
(1) Model A300 B4–2C, B4–103, and B4–
203 airplanes, all serial numbers, modified
preventively in service (without any
preliminary crack findings), as specified in
Airbus Service Bulletin A300–53–0297
(Airbus Modification 10453).
(2) Model A300 B4–601, B4–603, B4–605R,
B4–620, B4–622, and B4–622R airplanes, all
serial numbers, modified preventively in
service (without any preliminary crack
findings), as specified in Airbus Service
Bulletin A300–57–6053 (Airbus Modification
10453).
(d) Subject
Air Transport Association (ATA) of
America Code 53, 57: Fuselage, Wings.
(e) Reason
This AD was prompted by reports that
cracks were found in the frame (FR) 40
forward fitting. We are issuing this AD to
detect and correct cracking of the FR 40
forward fitting, which could result in a
deterioration of the structural integrity of the
frame.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Detailed Inspection
This paragraph restates the actions
required by paragraphs (f)(1), (f)(2), and (f)(3)
of AD 2010–06–05, Amendment 39–16229
(75 FR 11435, March 11, 2010).
(1) At the applicable time specified in table
1 to paragraph (g)(1) of this AD: Do a onetime detailed visual inspection of the forward
fitting at FR 40 on both sides of the airplane,
in accordance with Airbus Mandatory
Service Bulletin A300–57A6108 (for Model
A300 B4–601, B4–603, B4–605R, B4–620,
B4–622, and B4–622R airplanes) or A300–
53A0387 (for Model A300 B4–2C, B4–103,
and B4–203 airplanes), both including
Appendices 01 and 02, both dated September
12, 2008.
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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
75835
TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—COMPLIANCE TIMES
Airplane models/configuration
Compliance time
A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin
A300–53–0297 was done prior to the accumulation of 9,000 total
flight cycles.
Prior to the accumulation of 18,000 total flight cycles, or within 3
months after April 15, 2010 (the effective date of AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever
occurs later.
Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR
11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–
05), have accumulated 11,000 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months
after April 15, 2010 (the effective date of AD 2010–06–05).
Prior to the accumulation of 15,000 total flight cycles, or within 3
months after April 15, 2010 (the effective date of AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever
occurs later.
Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR
11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–
05), have accumulated 8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months after
April 15, 2010 (the effective date of AD 2010–06–05).
Prior to the accumulation of 11,500 total flight cycles, or within 3
months after April 15, 2010 (the effective date of AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever
occurs later.
Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57–6053, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR
11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–
05), have accumulated 6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300–57–6053, within 3 months after
April 15, 2010 (the effective date of AD 2010–06–05).
A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin
A300–53–0297 was done on or after the accumulation of 9,000 total
flight cycles.
A300 B4–203 airplanes on which Airbus Service Bulletin A300–53–
0297 was done prior to the accumulation of 8,300 total flight cycles.
A300 B4–203 airplanes on which Airbus Service Bulletin A300–53–
0297 was done on or after the accumulation of 8,300 total flight cycles.
A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done
prior to the accumulation of 6,100 total flight cycles.
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A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done on
or after the accumulation of 6,100 total flight cycles.
(2) Except as required by paragraph (g)(3)
of this AD: If any crack is found during the
inspection required by paragraph (g)(1) of
this AD, before further flight, do a temporary
or definitive repair, as applicable, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
53–0268, Revision 06, dated January 7, 2002
(for Model A300 B4–2C, B4–103, and B4–203
airplanes); or A300–57–6052, Revision 03,
dated May 27, 2002, including Airbus
Drawings 15R53810394, Issue A, dated
December 21, 1998, and 21R57110247, Issue
A, dated June 20, 1997 (for Model A300 B4–
601, B4–603, B4–605R, B4–620, B4–622, and
B4–622R airplanes).
(3) If any crack found during the inspection
required by paragraph (g)(1) of this AD
cannot be repaired in accordance with Airbus
Service Bulletin A300–53–0268, Revision 06,
dated January 7, 2002 (for Model A300 B4–
2C, B4–103, and B4–203 airplanes); or A300–
57–6052, Revision 03, dated May 27, 2002,
including Airbus Drawings 15R53810394,
Issue A, dated December 21, 1998, and
21R57110247, Issue A, dated June 20, 1997
(for Model A300 B4–601, B4–603, B4–605R,
B4–620, B4–622, and B4–622R airplanes):
Contact Airbus for repair instructions and,
before further flight, repair the crack using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the European
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04:58 Dec 22, 2012
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Aviation Safety Agency (EASA) (or its
delegated agent).
(i) New Requirement: Repetitive Detailed
Inspections
(h) Retained Reporting Requirement
Within 300 flight cycles after the effective
date of this AD: Perform a detailed inspection
for cracks of the forward fitting at FR 40
without nut removal on both sides of the
airplane, in accordance with Airbus All
Operator Telex A300–53A0391, dated August
9, 2011 (for Model A300 B4–2C, B4–103, and
B4–203 airplanes); or Airbus All Operator
Telex A300–57A6111, dated August 9, 2011
(for Model A300 B4–601, B4–603, B4–605R,
B4–620, B4–622, and B4–622R airplanes).
Thereafter, repeat the inspection at intervals
not to exceed 300 flight cycles.
This paragraph restates the requirements of
paragraph (f)(4) of AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March
11, 2010). Submit an inspection report in
accordance with Appendix 01 of Airbus
Mandatory Service Bulletin A300–53A0387,
including Appendices 01 and 02, dated
September 12, 2008 (for Model A300 B4–2C,
B4–103, and B4–203 airplanes); or Airbus
Mandatory Service Bulletin A300–57A6108,
including Appendices 01 and 02, dated
September 12, 2008 (for Model A300 B4–601,
B4–603, B4–605R, B4–620, B4–622, and B4–
622R airplanes); to the address identified on
the reporting sheet, at the applicable time
specified in paragraph (h)(1) or (h)(2) of this
AD.
(1) If the inspection was done on or after
April 15, 2010 (the effective date of AD
2010–06–05, Amendment 39–16229 (75 FR
11435, March 11, 2010)): Submit the report
within 30 days after the inspection.
(2) If the inspection was done before April
15, 2010 (the effective date of AD 2010–06–
05, Amendment 39–16229 (75 FR 11435,
March 11, 2010)): Submit the report within
30 days after April 15, 2010 (the effective
date of AD 2010–06–05).
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(j) New Requirement: Eddy Current
Inspection or Liquid Penetrant Inspection
Within 36 months after the effective date
of this AD: Perform an eddy current
inspection or a liquid penetrant inspection
for cracks of the forward fitting at FR 40 with
nut removal on both sides of the airplane, in
accordance with Airbus All Operator Telex
A300–53A0391, dated August 9, 2011 (for
Model A300 B4–2C, B4–103, and B4–203
airplanes); or Airbus All Operator Telex
A300–57A6111, dated August 9, 2011 (for
Model A300 B4–601, B4–603, B4–605R, B4–
620, B4–622, and B4–622R airplanes).
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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
(k) New Requirement: Corrective Action
If, during any inspection required by
paragraph (i) or (j) of this AD, any crack is
detected: Before further flight, repair the
crack in accordance with a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA, or
EASA (or its delegated agent).
(l) New Requirement: Reporting
Requirement
Submit a one-time report of the findings
(both positive and negative) of the
inspections required by paragraphs (i) and (j)
of this AD to Airbus, Sebastien Faure, SEES1,
SAS—EAW (Airworthiness Office), 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 31 68;
fax +33 5 61 93 36 14; email
sebastien.s.faure@airbus.com, at the
applicable time specified in paragraph (l)(1)
or (l)(2) of this AD.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
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(m) New Requirement: Terminating Action
Accomplishment of the one-time eddy
current inspection or a liquid penetrant
inspection required by paragraph (j) of this
AD, including doing all applicable repairs,
constitutes terminating action for the
inspections required by paragraph (i) of this
AD.
(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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–2125; fax (425) 227–
1149. Information may be emailed to: 9ANM-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. AMOCs approved previously in
accordance with AD 2010–06–05,
Amendment 39–16229 (75 FR 11435, March
11, 2010), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
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04:58 Dec 22, 2012
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are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(o) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0163, dated August 30, 2011,
and the service information specified in
paragraphs (o)(1) through (o)(6) of this AD,
for related information.
(1) Airbus All Operator Telex A300–
53A0391, dated August 9, 2011.
(2) Airbus All Operator Telex A300–
57A6111, dated August 9, 2011.
(3) Airbus Mandatory Service Bulletin
A300–57A6108, including Appendices 01
and 02, dated September 12, 2008.
(4) Airbus Mandatory Service Bulletin
A300–53A0387, including Appendices 01
and 02, dated September 12, 2008.
(5) Airbus Service Bulletin A300–53–0268,
Revision 06, dated January 7, 2002.
(6) Airbus Service Bulletin A300–57–6052,
Revision 03, dated May 27, 2002, including
Airbus Drawings 15R53810394, Issue A,
dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997.
(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 the AD specifies otherwise.
(3) The following service information was
approved for IBR on January 30, 2013.
(i) Airbus All Operator Telex A300–
53A0391, dated August 9, 2011. (The issue
date and document number of this document
are specified on only the first page of the
document.)
(ii) Airbus All Operator Telex A300–
57A6111, dated August 9, 2011. (The issue
date and document number of this document
are specified on only the first page of the
document.)
(4) The following service information was
approved for IBR on April 15, 2010 (75 FR
11435, March 11, 2010).
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
(i) Airbus Mandatory Service Bulletin
A300–57A6108, including Appendices 01
and 02, dated September 12, 2008.
(ii) Airbus Mandatory Service Bulletin
A300–53A0387, including Appendices 01
and 02, dated September 12, 2008.
(iii) Airbus Service Bulletin A300–53–
0268, Revision 06, dated January 7, 2002.
(Pages 1–6, 9, 10, and 25–27 of this document
are identified as Revision 06, dated January
7, 2002. Pages 7, 8, 11–24, and 28–84 of this
AD document are identified as Revision 05,
dated June 9, 2000).
(iv) Airbus Service Bulletin A300–57–
6052, Revision 03, dated May 27, 2002,
which includes Airbus Drawing
15R53810394, Issue A, dated December 21,
1998 and Airbus Drawing 21R57110247,
Issue A, dated June 20, 1997. Airbus Drawing
21R57110247, Issue A, dated June 20, 1997
has effective pages 1 and 2, dated May 28,
1997 and pages 3 and 4, dated June 20, 1997.
(5) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(6) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 4, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–29992 Filed 12–21–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2012–0660; Airspace
Docket No. 12–ANM–20]
Establishment of Class E Airspace;
Walsenburg, CO
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action establishes Class
E airspace at Spanish Peaks Airfield,
Walsenburg, CO, to accommodate
aircraft using new Area Navigation
(RNAV) Global Positioning System
(GPS) standard instrument approach
SUMMARY:
E:\FR\FM\26DER1.SGM
26DER1
]]>Agencies
[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Rules and Regulations]
[Pages 75833-75836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-29992]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-183-AD;
Amendment 39-17287; AD 2012-25-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R
airplanes. That AD currently requires performing a one-time detailed
visual inspection of the forward fitting at frame (FR) 40 on both sides
of the airplane for cracks, and repair if necessary. This new AD
requires repetitive detailed inspections of the forward fitting at FR
40 without nut removal, and a one-time eddy current or liquid penetrant
inspection of the forward fitting at FR 40 with nut removal, and repair
if necessary. This AD was prompted by reports that new cracks were
found in the FR 40 forward fitting. We are issuing this AD to detect
and correct cracking of the FR 40 forward fitting, which could result
in a deterioration of the structural integrity of the frame.
DATES: This AD becomes effective January 30, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 30,
2013.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
15, 2010 (75 FR 11435, March 11, 2010).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on August 27, 2012 (77
FR 51717), and proposed to supersede AD 2010-06-05, Amendment 39-16229
(75 FR 11435, March 11, 2010). That NPRM proposed to correct an unsafe
condition for the specified products. The Mandatory Continuing
Airworthiness Information (MCAI) states:
One A300-600 aeroplane operator reported that, during a routine
inspection, a crack was found in the right hand frame (FR) 40
forward fitting between stringer 32 and stringer 33. The subject
aeroplane had previously been modified in accordance with Airbus SB
A300-57-6053 (Mod. 10453).
Therefore and pending completion of the full analysis using a
refined Finite Element Model, EASA [European Aviation Safety Agency]
issued AD 2009-0094 [which corresponds with FAA AD 2010-06-05,
Amendment 39-16229 (75 FR 11435, March 11, 2010)] to require a one-
time Detailed Visual Inspection (DVI) of the post-SB A300-57-6053
A300-600 aeroplanes and post-SB A300-53-0297 A300 aeroplanes in
order to ensure the structural integrity of frame 40.
During a recent maintenance check, on two aeroplanes (one A300B4
and one A300-600), cracks were found in the FR 40 forward fitting.
These new crack findings are considered as unexpected, since
they were found after:
--Application of modification SB A300-57-6053 or SB A300-53-0297
which cancels the inspection programme, and
--Accomplishment of EASA AD 2009-0094.
[[Page 75834]]
For the reasons described above, this new [EASA] AD, which
supersedes EASA AD 2009-0094, requires repetitive DVI of the FR 40
forward fitting (without nut removal), accomplishment of a one time
Eddy Current (EC) inspection or liquid penetrant inspection of this
area (with nut removal) and, depending on findings, the
accomplishment of associated corrective action [repair if any
cracking found]. Passing the EC or liquid penetrant inspection
constitutes terminating action for the repetitive DVI.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (77 FR 51717, August 27,
2012), or on the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD will affect about 134 products of U.S.
registry.
The actions that are required by AD 2010-06-05, Amendment 39-16229
(75 FR 11435, March 11, 2010), and retained in this AD take about 3
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the currently required
actions is $255 per product.
We estimate that it will take about 3 work-hours per product to
comply with the new 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 to the U.S. operators to be $34,170, or $255 per product.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (77 FR 51717, August 27,
2012), 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. Comments will
be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010), and
adding the following new AD:
2012-25-06 Airbus: Amendment 39-17287. Docket No. FAA-2012-0858;
Directorate Identifier 2011-NM-183-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective January 30,
2013.
(b) Affected ADs
This AD supersedes AD 2010-06-05, Amendment 39-16229 (75 FR
11435, March 11, 2010).
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, as identified in paragraphs (c)(1) and (c)(2) of this AD.
For airplanes on which Airbus Service Bulletin A300-53-0297 or A300-
57-6053 (Airbus Modification 10453), as applicable, has been
incorporated as a corrective action (repair following crack
finding), no action is required by this AD.
(1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial
numbers, modified preventively in service (without any preliminary
crack findings), as specified in Airbus Service Bulletin A300-53-
0297 (Airbus Modification 10453).
(2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-
622R airplanes, all serial numbers, modified preventively in service
(without any preliminary crack findings), as specified in Airbus
Service Bulletin A300-57-6053 (Airbus Modification 10453).
(d) Subject
Air Transport Association (ATA) of America Code 53, 57:
Fuselage, Wings.
(e) Reason
This AD was prompted by reports that cracks were found in the
frame (FR) 40 forward fitting. We are issuing this AD to detect and
correct cracking of the FR 40 forward fitting, which could result in
a deterioration of the structural integrity of the frame.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Detailed Inspection
This paragraph restates the actions required by paragraphs
(f)(1), (f)(2), and (f)(3) of AD 2010-06-05, Amendment 39-16229 (75
FR 11435, March 11, 2010).
(1) At the applicable time specified in table 1 to paragraph
(g)(1) of this AD: Do a one-time detailed visual inspection of the
forward fitting at FR 40 on both sides of the airplane, in
accordance with Airbus Mandatory Service Bulletin A300-57A6108 (for
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes) or A300-53A0387 (for Model A300 B4-2C, B4-103, and B4-203
airplanes), both including Appendices 01 and 02, both dated
September 12, 2008.
[[Page 75835]]
Table 1 to Paragraph (g)(1) of this AD--Compliance Times
------------------------------------------------------------------------
Airplane models/configuration Compliance time
------------------------------------------------------------------------
A300 B4-2C and B4-103 airplanes on Prior to the accumulation of
which Airbus Service Bulletin A300-53- 18,000 total flight cycles, or
0297 was done prior to the within 3 months after April
accumulation of 9,000 total flight 15, 2010 (the effective date
cycles. of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later.
A300 B4-2C and B4-103 airplanes on Within 5,500 flight cycles
which Airbus Service Bulletin A300-53- after accomplishment of Airbus
0297 was done on or after the Service Bulletin A300-53-0297,
accumulation of 9,000 total flight or within 6 months after April
cycles. 15, 2010 (the effective date
of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later; except, for airplanes
that, as of April 15, 2010
(the effective date of AD 2010-
06-05), have accumulated
11,000 flight cycles or more
since accomplishment of Airbus
Service Bulletin A300-53-0297,
within 3 months after April
15, 2010 (the effective date
of AD 2010-06-05).
A300 B4-203 airplanes on which Airbus Prior to the accumulation of
Service Bulletin A300-53-0297 was done 15,000 total flight cycles, or
prior to the accumulation of 8,300 within 3 months after April
total flight cycles. 15, 2010 (the effective date
of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later.
A300 B4-203 airplanes on which Airbus Within 4,100 flight cycles
Service Bulletin A300-53-0297 was done after accomplishment of Airbus
on or after the accumulation of 8,300 Service Bulletin A300-53-0297,
total flight cycles. or within 6 months after April
15, 2010 (the effective date
of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later; except, for airplanes
that, as of April 15, 2010
(the effective date of AD 2010-
06-05), have accumulated 8,200
flight cycles or more since
accomplishment of Airbus
Service Bulletin A300-53-0297,
within 3 months after April
15, 2010 (the effective date
of AD 2010-06-05).
A300 B4-601, B4-603, B4-605R, B4-620, Prior to the accumulation of
B4-622, and B4-622R airplanes on which 11,500 total flight cycles, or
Airbus Service Bulletin A300-57-6053 within 3 months after April
was done prior to the accumulation of 15, 2010 (the effective date
6,100 total flight cycles. of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later.
A300 B4-601, B4-603, B4-605R, B4-620, Within 3,300 flight cycles
B4-622, and B4-622R airplanes on which after accomplishment of Airbus
Airbus Service Bulletin A300-57-6053 Service Bulletin A300-57-6053,
was done on or after the accumulation or within 6 months after April
of 6,100 total flight cycles. 15, 2010 (the effective date
of AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11,
2010)), whichever occurs
later; except, for airplanes
that, as of April 15, 2010
(the effective date of AD 2010-
06-05), have accumulated 6,600
flight cycles or more since
accomplishment of Airbus
Service Bulletin A300-57-6053,
within 3 months after April
15, 2010 (the effective date
of AD 2010-06-05).
------------------------------------------------------------------------
(2) Except as required by paragraph (g)(3) of this AD: If any
crack is found during the inspection required by paragraph (g)(1) of
this AD, before further flight, do a temporary or definitive repair,
as applicable, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings
15R53810394, Issue A, dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes).
(3) If any crack found during the inspection required by
paragraph (g)(1) of this AD cannot be repaired in accordance with
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings
15R53810394, Issue A, dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes): Contact Airbus for
repair instructions and, before further flight, repair the crack
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the European Aviation
Safety Agency (EASA) (or its delegated agent).
(h) Retained Reporting Requirement
This paragraph restates the requirements of paragraph (f)(4) of
AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010).
Submit an inspection report in accordance with Appendix 01 of Airbus
Mandatory Service Bulletin A300-53A0387, including Appendices 01 and
02, dated September 12, 2008 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57A6108,
including Appendices 01 and 02, dated September 12, 2008 (for Model
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes); to the address identified on the reporting sheet, at the
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after April 15, 2010 (the
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010)): Submit the report within 30 days after the
inspection.
(2) If the inspection was done before April 15, 2010 (the
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010)): Submit the report within 30 days after April 15,
2010 (the effective date of AD 2010-06-05).
(i) New Requirement: Repetitive Detailed Inspections
Within 300 flight cycles after the effective date of this AD:
Perform a detailed inspection for cracks of the forward fitting at
FR 40 without nut removal on both sides of the airplane, in
accordance with Airbus All Operator Telex A300-53A0391, dated August
9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or
Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes). Thereafter, repeat the inspection at intervals not to
exceed 300 flight cycles.
(j) New Requirement: Eddy Current Inspection or Liquid Penetrant
Inspection
Within 36 months after the effective date of this AD: Perform an
eddy current inspection or a liquid penetrant inspection for cracks
of the forward fitting at FR 40 with nut removal on both sides of
the airplane, in accordance with Airbus All Operator Telex A300-
53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus All Operator Telex A300-57A6111, dated
August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, and B4-622R airplanes).
[[Page 75836]]
(k) New Requirement: Corrective Action
If, during any inspection required by paragraph (i) or (j) of
this AD, any crack is detected: Before further flight, repair the
crack in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
or EASA (or its delegated agent).
(l) New Requirement: Reporting Requirement
Submit a one-time report of the findings (both positive and
negative) of the inspections required by paragraphs (i) and (j) of
this AD to Airbus, Sebastien Faure, SEES1, SAS--EAW (Airworthiness
Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email
sebastien.s.faure@airbus.com, at the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(m) New Requirement: Terminating Action
Accomplishment of the one-time eddy current inspection or a
liquid penetrant inspection required by paragraph (j) of this AD,
including doing all applicable repairs, constitutes terminating
action for the inspections required by paragraph (i) of this AD.
(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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; 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. AMOCs
approved previously in accordance with AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11, 2010), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(o) Related Information
Refer to MCAI EASA Airworthiness Directive 2011-0163, dated
August 30, 2011, and the service information specified in paragraphs
(o)(1) through (o)(6) of this AD, for related information.
(1) Airbus All Operator Telex A300-53A0391, dated August 9,
2011.
(2) Airbus All Operator Telex A300-57A6111, dated August 9,
2011.
(3) Airbus Mandatory Service Bulletin A300-57A6108, including
Appendices 01 and 02, dated September 12, 2008.
(4) Airbus Mandatory Service Bulletin A300-53A0387, including
Appendices 01 and 02, dated September 12, 2008.
(5) Airbus Service Bulletin A300-53-0268, Revision 06, dated
January 7, 2002.
(6) Airbus Service Bulletin A300-57-6052, Revision 03, dated May
27, 2002, including Airbus Drawings 15R53810394, Issue A, dated
December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.
(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 the AD specifies otherwise.
(3) The following service information was approved for IBR on
January 30, 2013.
(i) Airbus All Operator Telex A300-53A0391, dated August 9,
2011. (The issue date and document number of this document are
specified on only the first page of the document.)
(ii) Airbus All Operator Telex A300-57A6111, dated August 9,
2011. (The issue date and document number of this document are
specified on only the first page of the document.)
(4) The following service information was approved for IBR on
April 15, 2010 (75 FR 11435, March 11, 2010).
(i) Airbus Mandatory Service Bulletin A300-57A6108, including
Appendices 01 and 02, dated September 12, 2008.
(ii) Airbus Mandatory Service Bulletin A300-53A0387, including
Appendices 01 and 02, dated September 12, 2008.
(iii) Airbus Service Bulletin A300-53-0268, Revision 06, dated
January 7, 2002. (Pages 1-6, 9, 10, and 25-27 of this document are
identified as Revision 06, dated January 7, 2002. Pages 7, 8, 11-24,
and 28-84 of this AD document are identified as Revision 05, dated
June 9, 2000).
(iv) Airbus Service Bulletin A300-57-6052, Revision 03, dated
May 27, 2002, which includes Airbus Drawing 15R53810394, Issue A,
dated December 21, 1998 and Airbus Drawing 21R57110247, Issue A,
dated June 20, 1997. Airbus Drawing 21R57110247, Issue A, dated June
20, 1997 has effective pages 1 and 2, dated May 28, 1997 and pages 3
and 4, dated June 20, 1997.
(5) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(6) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 4, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-29992 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P
