[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Rules and Regulations]
[Pages 75833-75836]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-29992]
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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.
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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 http://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 http://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
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Airplane models/configuration Compliance time
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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
[email protected], 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: [email protected]. 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 [email protected];
Internet http://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: http://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]
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