Airworthiness Directives; Airbus Airplanes, 11793-11796 [2012-4644]
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Federal Register / Vol. 77, No. 39 / Tuesday, February 28, 2012 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Saab AB, Saab Aerosystems: Docket No.
FAA–2012–0184; Directorate Identifier
2011–NM–118–AD.
(a) Comments Due Date
We must receive comments by April 13,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Saab AB, Saab
Aerosystems Model SAAB 2000 airplanes;
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 92.
(e) Reason
This AD was prompted by reports that
environmentally friendly de-icing agents
used on certain electrical connectors and
braids could cause corrosion damage. We are
issuing this AD to detect and correct
corrosion of critical system wiring, which
could result in arcing and, in combination
with other factors, a fire and consequent
damage to the airplane.
(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.
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(g) Inspection
Within 24 months after the effective date
of this AD, do a detailed inspection for
corrosion of the electrical and electronics
installation, at the locations specified in and
in accordance with the Accomplishment
Instructions of SAAB Service Bulletin 2000–
92–005, Revision 01, dated March 1, 2011;
and SAAB Service Bulletin 2000–92–006,
Revision 01, dated August 18, 2010. These
inspections do not need to be accomplished
concurrently.
(h) Corrective Action
If any corrosion is found during any
inspection required in paragraph (g) of this
AD: Before next flight, repair each affected
harness braid or replace each affected
component and/or wiring harness, as
applicable, in accordance with the
Accomplishment Instructions of SAAB
Service Bulletin 2000–92–005, Revision 01,
dated March 1, 2011; and SAAB Service
Bulletin 2000–92–006, Revision 01, dated
August 18, 2010.
(i) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
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this AD, if those actions were performed
before the effective date of this AD using
according to SAAB Service Bulletin 2000–
92–005, dated May 5, 2010; and SAAB
Service Bulletin 2000–92–006, dated
March 29, 2010.
(j) Reporting Requirement
Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (g) of this AD, using
the Feedback Form in SAAB Service Bulletin
2000–92–005, Revision 01, dated March 1,
2011; and SAAB Service Bulletin 2000–92–
006, Revision 01, dated August 18, 2010.
Send the report to SAAB Aerotech, Support
Services Division, SE–581 88 Linkoping,
Sweden; fax +46 13 18 4874; email
saab2000.techsupport@saabgroup.com; at the
applicable time specified in paragraph (i)(1)
or (i)(2) of this AD. The report must include
the level of corrosion found on each
connector.
(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.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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:
Shahram Daneshmandi, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1112; fax (425)
227–1149. Information may be emailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) 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
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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.
(l) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0079, dated May 5, 2011, and
the service information specified in
paragraphs (l)(1) and (l)(2) of this AD, for
related information.
(1) SAAB Service Bulletin 2000–92–005,
Revision 01, dated March 1, 2011.
(2) SAAB Service Bulletin 2000–92–006,
Revision 01, dated August 18, 2010.
Issued in Renton, Washington, on February
14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–4646 Filed 2–27–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0185; Directorate
Identifier 2011–NM–001–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–103, B4–203,
and B4–2C airplanes, and Model B4–
600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
airplanes (collectively called A300–600
series airplanes). This proposed AD was
prompted by reports of cracking in the
forward lug of the main landing gear
(MLG) rib 5 aft bearing attachment. This
proposed AD would require repetitive
inspections for cracking of the left-hand
(LH) and right-hand (RH) wing MLG rib
5 aft bearing forward lugs and repair if
necessary. We are proposing this AD to
detect and correct cracking of the LH
and RH wing MLG rib 5 aft bearing
forward lugs which, if not corrected,
SUMMARY:
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could affect the structural integrity of
the MLG attachment, which could result
in MLG collapse during landing or
rollout with consequent damage to the
airplane and injury to occupants.
DATES: We must receive comments on
this proposed AD by April 13, 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.
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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,
Washington 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
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this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0185; Directorate Identifier
2011–NM–001–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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2010–0250,
dated November 29, 2010 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During routine visual inspection, a crack
has been found in the wing MLG [main
landing gear] rib 5 aft bearing forward lug on
two A310 in-service aeroplanes. Laboratory
examination of cracked ribs confirmed that
the crack was due to the presence of pitting
corrosion in the forward lug hole. Also on
both aeroplanes medium to heavy corrosion
was found in the forward lugs on the
opposite wing after removal of the bushes.
Similarly to A310 aeroplanes, A300 and
A300–600 aeroplanes are concerned by this
situation which, if not detected, could affect
the structural integrity of the MLG
attachment.
The aim of the [EASA] Emergency
Airworthiness Directive (EAD) 2006–0372–E
[which corresponds to FAA AD 2007–03–18,
Amendment 39–14929 (72 FR 5919, February
8, 2007)] was to mandate, for A300 and
A300–600 aeroplanes, repetitive detailed
visual inspections (DVI) of wing MLG rib 5
aft bearing forward lugs for detection of
through cracks.
Since then, in order to ensure the detection
of any crack in the forward lug of the RH
[right-hand] and LH [left-hand] MLG rib 5 aft
bearing attachment at an early stage, Airbus
has developed a new inspection by means of
ultrasonic method. Due to the early crack
detection possibility, this new means of
inspection also enables extension of the
inspection interval.
For technical reasons, this new means of
inspection is only applicable to A300B4, C4,
and F4 and A300–600 aeroplane series (not
to A300B2 aeroplane series).
For these reasons, this new [EASA] AD
* * * adds new inspection program
requirements [a revised detailed inspection,
optional ultrasonic inspections, and repair if
necessary].
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As an option, a modification which
includes installing bushings with an
increased interference fit in the aft
bearing forward lugs terminates the
repetitive inspections. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
service bulletins:
• Mandatory Service Bulletin A300–
57–0249, Revision 02, dated June 18,
2010 (for Model A300–B4–103, B4–2C,
and B4–203 airplanes).
• Mandatory Service Bulletin A300–
57–0251, including Appendix 01, dated
August 8, 2007 (for Model A300 B4–
103, B4–203 and B4–2C airplanes).
• Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010 (for
Model A300 B4–601, B4–603, B4–605R,
B4–620, B4–622, B4–622R, F4–605R,
F4–622R, and C4–605R airplanes).
• Mandatory Service Bulletin A300–
57–6107, including Appendix 01, dated
August 8, 2007 (for Model A300 B4–
601, B4–603, B4–605R, B4–620, B4–622,
B4–622R, C4–605R, F4–605R, and F4–
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.
Differences Between This AD and the
MCAI or Service Information
Although the MCAI allows further
flight after cracks are found during
compliance with the required action,
paragraph (i) of this AD requires that
you repair the cracks before further
flight.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 165 products of U.S.
registry. We also estimate that it would
take about 3 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
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rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$42,075, or $255 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 52 work-hours and require parts
costing $4,590, for a cost of $9,010 per
product. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Regulatory Findings
We determined that this 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.
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2012–0185;
Directorate Identifier 2011–NM–001–AD.
(a) Comments Due Date
We must receive comments by April 13,
2012.
(b) Affected ADs
This AD affects AD 2007–03–18,
Amendment 39–14929 (72 FR 5919, February
8, 2007).
(c) Applicability
This AD applies to Airbus Model A300 B4–
2C, B4–103, B4–203 airplanes; Model B4–
601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, F4–605R and F4–622R airplanes; and
Model A300 C4–605R Variant F airplanes;
certificated in any category; all serial
numbers except for airplanes identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Airplanes on which LH (left-hand) and
RH (right-hand) wing main landing gear
(MLG) rib 5 forward lugs have oversized
interference fit bushings installed per
drawing R57240221.
(2) Model A300 B4–103, B4–203, and B4–
2C airplanes on which Airbus Mandatory
Service Bulletin A300–57–0249 has been
done in service on the LH and RH wing.
(3) Model A300–600 series airplanes on
which Airbus Service Bulletin A300–57–
6106 has been done in service on the LH and
RH wing.
(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(e) Reason
This AD was prompted by reports of
cracking in the forward lug of the MLG rib
5 aft bearing attachment. We are issuing this
AD to detect and correct cracking of the LH
and RH wing MLG rib 5 aft bearing forward
lugs which, if not corrected, could affect the
structural integrity of the MLG attachment,
which could result in MLG collapse during
landing or rollout with consequent damage to
the airplane and injury to occupants.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
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11795
compliance times specified, unless the
actions have already been done.
(g) Inspections
Except as provided by paragraph (h) of this
AD, before the accumulation of 12,000 total
flight cycles since new, or within 12,000
flight cycles since the most recent MLG rib
5 replacement, if applicable, or within 10
days after the effective date of this AD,
whichever occurs latest, do a detailed
inspection or an ultrasonic inspection for
cracking of the LH and RH MLG rib 5 aft
bearing forward lugs, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–0251,
including Appendix 01, dated August 8, 2007
(for Model A300 B4–103, B4–203, and B4–2C
airplanes); or Airbus Mandatory Service
Bulletin A300–57–6107, including Appendix
01, dated August 8, 2007 (for Model A300–
600 series airplanes). Repeat the applicable
inspections thereafter at the applicable
interval specified in paragraph (g)(1) or (g)(2)
of this AD, until the modification specified
in paragraph (j) of this AD is accomplished.
(1) Repeat the detailed inspections at
intervals not to exceed 100 flight cycles.
(2) Repeat the ultrasonic inspections at
intervals not to exceed 675 flight cycles.
(h) Exception
For airplanes on which an inspection
required by AD 2007–03–18, Amendment
39–14929 (72 FR 5919, February 8, 2007), has
been done as of the effective date of this AD:
Within 100 flight cycles after doing the most
recent inspection required by AD 2007–03–
18, or within 10 days after the effective date
of this AD, whichever occurs later, do a
detailed or ultrasonic inspection as specified
in paragraph (g) of this AD. Repeat the
applicable inspection thereafter at the times
specified in paragraph (g) of this AD.
(i) Repair
If any cracking is detected during any
detailed or ultrasonic inspection of the LH
and RH MLG rib 5 aft bearing forward lugs
required by paragraph (g) of this AD, before
further flight, repair using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent).
(j) Optional Terminating Modification
Performing the applicable actions specified
in paragraphs (j)(1), (j)(2), (j)(3) and (j)(4) of
this AD, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–0249,
Revision 02, dated June 18, 2010 (for Model
A300 B4–103, B4–203, and B4–2C airplanes);
or Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010 (for Model
A300–600 series airplanes); terminates the
repetitive inspections required by this AD.
(1) Perform a general visual inspection and
dye penetrant flaw detection inspection for
corrosion and damage of the bore and
spotfaces of the lug.
(2) Determine that the diameter of the bore
of the lug (dimension Y) is within the
tolerance specified in the Accomplishment
Instructions of Airbus Mandatory Service
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Bulletin A300–57–0249, Revision 02, dated
June 18, 2010 (for Model A300 B4–103, B4–
203, and B4–2C airplanes); or Airbus Service
Bulletin A300–57–6106, Revision 02, dated
June 18, 2010 (for Model A300–600 series
airplanes).
(3) If damage or corrosion is detected
during any inspection specified in paragraph
(j)(1) of this AD, or if dimension Y is outside
the tolerance specified in the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–0249,
Revision 02, dated June 18, 2010 (for Model
A300 B4–103, B4–203, and B4–2C airplanes);
or Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010 (for Model
A300–600 series airplanes); repair using a
method approved by either the Manager,
International Branch, ANM 116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent).
(4) Install bushings with an increased
interference fit in the aft bearing forward
lugs, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–0249,
Revision 02, dated June 18, 2010 (for Model
A300 B4–103, B4–203, and B4–2C airplanes);
or Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010 (for Model
A300–600 series airplanes).
(k) Terminating Action for AD 2007–03–18,
Amendment 39–14929 (72 FR 5919,
February 8, 2007)
Doing the inspection required by paragraph
(g) of this AD terminates the requirements of
AD 2007–03–18, Amendment 39–14929 (72
FR 5919, February 8, 2007), for that airplane.
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(l) Reporting
Submit a report (including both positive
and negative findings), using the applicable
report sheet attached to Airbus Mandatory
Service Bulletin A300–57–0251, including
Appendix 01, dated August 8, 2007 (for
Model A300 B4–103, B4–203, and B4–2C
airplanes); or Airbus Mandatory Service
Bulletin A300–57–6107, including Appendix
01, August 8, 2007 (for Model A300–600
series airplanes); of the first inspection
required by paragraph (g) of this AD. Submit
the report to Airbus, Customer Services
Directorate, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex France, Attn: SEDCC1
Technical Data and Documentation Services;
fax: (+33) 5 61 93 28 06; email: sb.reporting@
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) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service bulletins specified in paragraphs
(m)(1), (m)(2), (m)(3), and (m)(4) of this AD.
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(1) Airbus Service Bulletin A300–57–0249,
dated May 22, 2007 (for Model A300 B4–2C,
B4–103, and B4–203 airplanes).
(2) Airbus Service Bulletin A300–57–0249,
Revision 01, dated December 19, 2007 (for
Model A300 B4–2C, B4–103, and B4–203
airplanes).
(3) Airbus Service Bulletin A300–57–6106,
dated May 22, 2007 (Model A300 B4–601,
B4–603, B4–605R, B4–620, B4–622, B4–
622R, F4–605R, F4–622R, and Model A300
C4–605R Variant F airplanes).
(4) Airbus Service Bulletin A300–57–6106,
Revision 01, dated January 28, 2008 (Model
A300 B4–601, B4–603, B4–605R, B4–620,
B4–622, B4–622R, F4–605R, F4–622R, and
Model A300 C4–605R Variant F airplanes).
(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, Washington 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.
(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:
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
Information Collection Clearance Officer,
AES–200.
(o) Related Information
Refer to MCAI EASA Airworthiness
Directive 2010–0250, dated November 29,
2010, and the service information in
paragraphs (o)(1), (o)(2), (o)(3), and (o)(4) of
this AD, for related information.
(1) Airbus Mandatory Service Bulletin
A300–57–0249, Revision 02, dated June 18,
2010.
(2) Airbus Mandatory Service Bulletin
A300–57–0251, including Appendix 01,
dated August 8, 2007.
(3) Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010.
(4) Airbus Mandatory Service Bulletin
A300–57–6107, including Appendix 01,
August 8, 2007.
Issued in Renton, Washington, on February
13, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–4644 Filed 2–27–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
Docket No. FAA–2012–0131; Airspace
Docket No. 12–ANM–2
Proposed Amendment of Class E
Airspace; Rock Springs, WY
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Class E airspace at Rock SpringsSweetwater County Airport, Rock
Springs, WY. Decommissioning of the
Rock Springs Tactical Air Navigation
System (TACAN) has made this action
necessary for the safety and
management of Instrument Flight Rules
(IFR) operations at the airport. This
action also would adjust the geographic
coordinates of the airport.
DATES: Comments must be received on
or before April 13, 2012.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590; telephone (202)
366–9826. You must identify FAA
Docket No. FAA–2012–0131; Airspace
Docket No. 12–ANM–2, at the beginning
of your comments. You may also submit
comments through the Internet at
https://www.regulations.gov.
SUMMARY:
E:\FR\FM\28FEP1.SGM
28FEP1
]]>Agencies
[Federal Register Volume 77, Number 39 (Tuesday, February 28, 2012)]
[Proposed Rules]
[Pages 11793-11796]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-4644]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0185; Directorate Identifier 2011-NM-001-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 B4-103, B4-203, and B4-2C airplanes, and
Model B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R
Variant F airplanes (collectively called A300-600 series airplanes).
This proposed AD was prompted by reports of cracking in the forward lug
of the main landing gear (MLG) rib 5 aft bearing attachment. This
proposed AD would require repetitive inspections for cracking of the
left-hand (LH) and right-hand (RH) wing MLG rib 5 aft bearing forward
lugs and repair if necessary. We are proposing this AD to detect and
correct cracking of the LH and RH wing MLG rib 5 aft bearing forward
lugs which, if not corrected,
[[Page 11794]]
could affect the structural integrity of the MLG attachment, which
could result in MLG collapse during landing or rollout with consequent
damage to the airplane and injury to occupants.
DATES: We must receive comments on this proposed AD by April 13, 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, Washington 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-2012-0185;
Directorate Identifier 2011-NM-001-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0250, dated November 29, 2010 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During routine visual inspection, a crack has been found in the
wing MLG [main landing gear] rib 5 aft bearing forward lug on two
A310 in-service aeroplanes. Laboratory examination of cracked ribs
confirmed that the crack was due to the presence of pitting
corrosion in the forward lug hole. Also on both aeroplanes medium to
heavy corrosion was found in the forward lugs on the opposite wing
after removal of the bushes. Similarly to A310 aeroplanes, A300 and
A300-600 aeroplanes are concerned by this situation which, if not
detected, could affect the structural integrity of the MLG
attachment.
The aim of the [EASA] Emergency Airworthiness Directive (EAD)
2006-0372-E [which corresponds to FAA AD 2007-03-18, Amendment 39-
14929 (72 FR 5919, February 8, 2007)] was to mandate, for A300 and
A300-600 aeroplanes, repetitive detailed visual inspections (DVI) of
wing MLG rib 5 aft bearing forward lugs for detection of through
cracks.
Since then, in order to ensure the detection of any crack in the
forward lug of the RH [right-hand] and LH [left-hand] MLG rib 5 aft
bearing attachment at an early stage, Airbus has developed a new
inspection by means of ultrasonic method. Due to the early crack
detection possibility, this new means of inspection also enables
extension of the inspection interval.
For technical reasons, this new means of inspection is only
applicable to A300B4, C4, and F4 and A300-600 aeroplane series (not
to A300B2 aeroplane series).
For these reasons, this new [EASA] AD * * * adds new inspection
program requirements [a revised detailed inspection, optional
ultrasonic inspections, and repair if necessary].
As an option, a modification which includes installing bushings with an
increased interference fit in the aft bearing forward lugs terminates
the repetitive inspections. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service bulletins:
Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010 (for Model A300-B4-103, B4-2C, and B4-203
airplanes).
Mandatory Service Bulletin A300-57-0251, including
Appendix 01, dated August 8, 2007 (for Model A300 B4-103, B4-203 and
B4-2C airplanes).
Service Bulletin A300-57-6106, Revision 02, dated June 18,
2010 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R,
F4-605R, F4-622R, and C4-605R airplanes).
Mandatory Service Bulletin A300-57-6107, including
Appendix 01, dated August 8, 2007 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, B4-622R, C4-605R, F4-605R, and F4-622R
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.
Differences Between This AD and the MCAI or Service Information
Although the MCAI allows further flight after cracks are found
during compliance with the required action, paragraph (i) of this AD
requires that you repair the cracks before further flight.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 165 products of U.S. registry. We also estimate that
it would take about 3 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor
[[Page 11795]]
rate is $85 per work-hour. Based on these figures, we estimate the cost
of the proposed AD on U.S. operators to be $42,075, or $255 per
product.
In addition, we estimate that any necessary follow-on actions would
take about 52 work-hours and require parts costing $4,590, for a cost
of $9,010 per product. We have no way of determining the number of
products that may need these actions.
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 adding the following new AD:
Airbus: Docket No. FAA-2012-0185; Directorate Identifier 2011-NM-
001-AD.
(a) Comments Due Date
We must receive comments by April 13, 2012.
(b) Affected ADs
This AD affects AD 2007-03-18, Amendment 39-14929 (72 FR 5919,
February 8, 2007).
(c) Applicability
This AD applies to Airbus Model A300 B4-2C, B4-103, B4-203
airplanes; Model B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F
airplanes; certificated in any category; all serial numbers except
for airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD.
(1) Airplanes on which LH (left-hand) and RH (right-hand) wing
main landing gear (MLG) rib 5 forward lugs have oversized
interference fit bushings installed per drawing R57240221.
(2) Model A300 B4-103, B4-203, and B4-2C airplanes on which
Airbus Mandatory Service Bulletin A300-57-0249 has been done in
service on the LH and RH wing.
(3) Model A300-600 series airplanes on which Airbus Service
Bulletin A300-57-6106 has been done in service on the LH and RH
wing.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by reports of cracking in the forward lug
of the MLG rib 5 aft bearing attachment. We are issuing this AD to
detect and correct cracking of the LH and RH wing MLG rib 5 aft
bearing forward lugs which, if not corrected, could affect the
structural integrity of the MLG attachment, which could result in
MLG collapse during landing or rollout with consequent damage to the
airplane and injury to occupants.
(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) Inspections
Except as provided by paragraph (h) of this AD, before the
accumulation of 12,000 total flight cycles since new, or within
12,000 flight cycles since the most recent MLG rib 5 replacement, if
applicable, or within 10 days after the effective date of this AD,
whichever occurs latest, do a detailed inspection or an ultrasonic
inspection for cracking of the LH and RH MLG rib 5 aft bearing
forward lugs, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-57-0251, including Appendix
01, dated August 8, 2007 (for Model A300 B4-103, B4-203, and B4-2C
airplanes); or Airbus Mandatory Service Bulletin A300-57-6107,
including Appendix 01, dated August 8, 2007 (for Model A300-600
series airplanes). Repeat the applicable inspections thereafter at
the applicable interval specified in paragraph (g)(1) or (g)(2) of
this AD, until the modification specified in paragraph (j) of this
AD is accomplished.
(1) Repeat the detailed inspections at intervals not to exceed
100 flight cycles.
(2) Repeat the ultrasonic inspections at intervals not to exceed
675 flight cycles.
(h) Exception
For airplanes on which an inspection required by AD 2007-03-18,
Amendment 39-14929 (72 FR 5919, February 8, 2007), has been done as
of the effective date of this AD: Within 100 flight cycles after
doing the most recent inspection required by AD 2007-03-18, or
within 10 days after the effective date of this AD, whichever occurs
later, do a detailed or ultrasonic inspection as specified in
paragraph (g) of this AD. Repeat the applicable inspection
thereafter at the times specified in paragraph (g) of this AD.
(i) Repair
If any cracking is detected during any detailed or ultrasonic
inspection of the LH and RH MLG rib 5 aft bearing forward lugs
required by paragraph (g) of this AD, before further flight, repair
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its delegated agent).
(j) Optional Terminating Modification
Performing the applicable actions specified in paragraphs
(j)(1), (j)(2), (j)(3) and (j)(4) of this AD, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Service Bulletin A300-
57-6106, Revision 02, dated June 18, 2010 (for Model A300-600 series
airplanes); terminates the repetitive inspections required by this
AD.
(1) Perform a general visual inspection and dye penetrant flaw
detection inspection for corrosion and damage of the bore and
spotfaces of the lug.
(2) Determine that the diameter of the bore of the lug
(dimension Y) is within the tolerance specified in the
Accomplishment Instructions of Airbus Mandatory Service
[[Page 11796]]
Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model
A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Service
Bulletin A300-57-6106, Revision 02, dated June 18, 2010 (for Model
A300-600 series airplanes).
(3) If damage or corrosion is detected during any inspection
specified in paragraph (j)(1) of this AD, or if dimension Y is
outside the tolerance specified in the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C
airplanes); or Airbus Service Bulletin A300-57-6106, Revision 02,
dated June 18, 2010 (for Model A300-600 series airplanes); repair
using a method approved by either the Manager, International Branch,
ANM 116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its delegated agent).
(4) Install bushings with an increased interference fit in the
aft bearing forward lugs, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-57-0249,
Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and
B4-2C airplanes); or Airbus Service Bulletin A300-57-6106, Revision
02, dated June 18, 2010 (for Model A300-600 series airplanes).
(k) Terminating Action for AD 2007-03-18, Amendment 39-14929 (72 FR
5919, February 8, 2007)
Doing the inspection required by paragraph (g) of this AD
terminates the requirements of AD 2007-03-18, Amendment 39-14929 (72
FR 5919, February 8, 2007), for that airplane.
(l) Reporting
Submit a report (including both positive and negative findings),
using the applicable report sheet attached to Airbus Mandatory
Service Bulletin A300-57-0251, including Appendix 01, dated August
8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or
Airbus Mandatory Service Bulletin A300-57-6107, including Appendix
01, August 8, 2007 (for Model A300-600 series airplanes); of the
first inspection required by paragraph (g) of this AD. Submit the
report to Airbus, Customer Services Directorate, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical
Data and Documentation Services; fax: (+33) 5 61 93 28 06; email:
sb.reporting@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) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the applicable service bulletins
specified in paragraphs (m)(1), (m)(2), (m)(3), and (m)(4) of this
AD.
(1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007
(for Model A300 B4-2C, B4-103, and B4-203 airplanes).
(2) Airbus Service Bulletin A300-57-0249, Revision 01, dated
December 19, 2007 (for Model A300 B4-2C, B4-103, and B4-203
airplanes).
(3) Airbus Service Bulletin A300-57-6106, dated May 22, 2007
(Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-
605R, F4-622R, and Model A300 C4-605R Variant F airplanes).
(4) Airbus Service Bulletin A300-57-6106, Revision 01, dated
January 28, 2008 (Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, B4-622R, F4-605R, F4-622R, and Model A300 C4-605R Variant F
airplanes).
(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, Washington
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.
(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 2010-0250, dated
November 29, 2010, and the service information in paragraphs (o)(1),
(o)(2), (o)(3), and (o)(4) of this AD, for related information.
(1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010.
(2) Airbus Mandatory Service Bulletin A300-57-0251, including
Appendix 01, dated August 8, 2007.
(3) Airbus Service Bulletin A300-57-6106, Revision 02, dated
June 18, 2010.
(4) Airbus Mandatory Service Bulletin A300-57-6107, including
Appendix 01, August 8, 2007.
Issued in Renton, Washington, on February 13, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-4644 Filed 2-27-12; 8:45 am]
BILLING CODE 4910-13-P
