Airworthiness Directives; Airbus Airplanes, 51717-51720 [2012-20966]
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51717
Proposed Rules
Federal Register
Vol. 77, No. 166
Monday, August 27, 2012
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0858; Directorate
Identifier 2011–NM–183–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to 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. The existing 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. Since we issued that
AD, we have received reports that new
cracks were found in the FR 40 forward
fitting. This proposed AD would require
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. We are
proposing 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: We must receive comments on
this proposed AD by October 11, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
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SUMMARY:
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W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
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 this proposed 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. Comments will
be available in the AD docket shortly
after receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0858; Directorate Identifier
2011–NM–183–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
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closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On March 4, 2010, we issued AD
2010–06–05, Amendment 39–16229 (75
FR 11435, March 11, 2010). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2010–06–05,
Amendment 39–16229 (75 FR 11435,
March 11, 2010), we have received
reports that additional cracks have been
found after the modification had been
completed. In addition, new inspections
have been added to address the unsafe
condition. The European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community, has issued
EASA Airworthiness Directive 2011–
0163, dated August 30, 2011 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The 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 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.
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
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(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.
Relevant Service Information
Airbus has issued All Operator Telex
A300–53A0391, dated August 9, 2011
(for Model A300 B4–2C, B4–103, and
B4–203 airplanes); and 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). The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
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Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
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 proposed AD take about 3 workhours 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 would take about
3 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on 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,
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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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[Amended]
2. The FAA amends § 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:
Airbus: Docket No. FAA–2012–0858;
Directorate Identifier 2011–NM–183–AD.
(a) Comments Due Date
We must receive comments by October 11,
2012.
(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, have
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
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Appendices 01 and 02, both dated September
12, 2008.
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.
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.
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.
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.
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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 prior to the accumulation of 6,100 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 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
Aviation Safety Agency (EASA) (or its
delegated agent).
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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).
(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
Visual 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
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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).
(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).
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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.
(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.
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(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.
(o) Related Information
(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, 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;
phone: (425) 227–2125; fax: (425) 227–1149;
email: Dan.Rodina@faa.gov. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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
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(1) Refer to MCAI EASA Airworthiness
Directive 2011–0163, dated August 30, 2011,
and the service information in paragraphs
(o)(1)(i) through (o)(1)(vi) of this AD, for
related information.
(i) Airbus All Operator Telex A300–
53A0391, dated August 9, 2011.
(ii) Airbus All Operator Telex A300–
57A6111, dated August 9, 2011.
(iii) Airbus Mandatory Service Bulletin
A300–57A6108, including Appendices 01
and 02, dated September 12, 2008.
(iv) Airbus Mandatory Service Bulletin
A300–53A0387, including Appendices 01
and 02, dated September 12, 2008.
(v) Airbus Service Bulletin A300–53–0268,
Revision 06, dated January 7, 2002.
(vi) 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.
(2) 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. You may review copies of
the 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.
Issued in Renton, Washington, on August
17, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–20966 Filed 8–24–12; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0860; Directorate
Identifier 2012–NM–123–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –800, and –900ER series
airplanes. This proposed AD was
prompted by incorrect wire support
clamps installed within the left
environmental cooling systems (ECS)
bay, which could allow wiring to come
in contact with the exposed metal of the
improper clamp. This proposed AD
would require inspections to identify
the part number of the wire support
clamp, related investigative actions, and
corrective actions if necessary. We are
proposing this AD to prevent electrical
arcing and a potential ignition source,
which in combination with flammable
fuel vapors could result in a fuel tank
explosion, and consequent loss of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by October 11, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
DATES:
E:\FR\FM\27AUP1.SGM
27AUP1
]]>Agencies
[Federal Register Volume 77, Number 166 (Monday, August 27, 2012)]
[Proposed Rules]
[Pages 51717-51720]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-20966]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 77, No. 166 / Monday, August 27, 2012 /
Proposed Rules
[[Page 51717]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-183-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to 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. The existing 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. Since we issued that AD, we have received reports that new
cracks were found in the FR 40 forward fitting. This proposed AD would
require 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. We are proposing 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: We must receive comments on this proposed AD by October 11,
2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
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 this proposed 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. Comments will be available in the AD docket
shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0858;
Directorate Identifier 2011-NM-183-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 4, 2010, we issued AD 2010-06-05, Amendment 39-16229 (75
FR 11435, March 11, 2010). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010), we have received reports that additional cracks have
been found after the modification had been completed. In addition, new
inspections have been added to address the unsafe condition. The
European Aviation Safety Agency (EASA), which is the Technical Agent
for the Member States of the European Community, has issued EASA
Airworthiness Directive 2011-0163, dated August 30, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The 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 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.
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
[[Page 51718]]
(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.
Relevant Service Information
Airbus has issued All Operator Telex A300-53A0391, dated August 9,
2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); and 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). The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would 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 proposed 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 would take about 3 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
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:
Airbus: Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-
183-AD.
(a) Comments Due Date
We must receive comments by October 11, 2012.
(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, have 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
[[Page 51719]]
Appendices 01 and 02, both dated September 12, 2008.
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 Prior to the accumulation of 18,000 total flight cycles, or
Airbus Service Bulletin A300-53-0297 was within 3 months after April 15, 2010 (the effective date of AD
done prior to the accumulation of 9,000 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
total flight cycles. whichever occurs later.
A300 B4-2C and B4-103 airplanes on which Within 5,500 flight cycles after accomplishment of Airbus Service
Airbus Service Bulletin A300-53-0297 was Bulletin A300-53-0297, or within 6 months after April 15, 2010
done on or after the accumulation of 9,000 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
total flight cycles. 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 Service Prior to the accumulation of 15,000 total flight cycles, or
Bulletin A300-53-0297 was done prior to the within 3 months after April 15, 2010 (the effective date of AD
accumulation of 8,300 total flight cycles. 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
whichever occurs later.
A300 B4-203 airplanes on which Airbus Service Within 4,100 flight cycles after accomplishment of Airbus Service
Bulletin A300-53-0297 was done on or after Bulletin A300-53-0297, or within 6 months after April 15, 2010
the accumulation of 8,300 total flight (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
cycles. 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, B4-622, Prior to the accumulation of 11,500 total flight cycles, or
and B4-622R airplanes on which Airbus within 3 months after April 15, 2010 (the effective date of AD
Service Bulletin A300-57-6053 was done prior 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
to the accumulation of 6,100 total flight whichever occurs later.
cycles.
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, Within 3,300 flight cycles after accomplishment of Airbus Service
and B4-622R airplanes on which Airbus Bulletin A300-57-6053, or within 6 months after April 15, 2010
Service Bulletin A300-57-6053 was done on or (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
after the accumulation of 6,100 total flight 11435, March 11, 2010)), whichever occurs later; except, for
cycles. 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 Visual 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).
(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).
[[Page 51720]]
(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, 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; phone: (425) 227-2125;
fax: (425) 227-1149; email: Dan.Rodina@faa.gov. 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
(1) Refer to MCAI EASA Airworthiness Directive 2011-0163, dated
August 30, 2011, and the service information in paragraphs (o)(1)(i)
through (o)(1)(vi) of this AD, for related information.
(i) Airbus All Operator Telex A300-53A0391, dated August 9,
2011.
(ii) Airbus All Operator Telex A300-57A6111, dated August 9,
2011.
(iii) Airbus Mandatory Service Bulletin A300-57A6108, including
Appendices 01 and 02, dated September 12, 2008.
(iv) Airbus Mandatory Service Bulletin A300-53A0387, including
Appendices 01 and 02, dated September 12, 2008.
(v) Airbus Service Bulletin A300-53-0268, Revision 06, dated
January 7, 2002.
(vi) 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.
(2) 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. You may review copies of the
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.
Issued in Renton, Washington, on August 17, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-20966 Filed 8-24-12; 8:45 am]
BILLING CODE 4910-13-P
