Airworthiness Directives; Airbus Airplanes, 13938-13944 [2014-05435]
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Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules
130S, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: (425) 917–6418; fax: (425) 917–
6590; email: marie.hogestad@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA 98057–
3356. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on February
28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–05426 Filed 3–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0142; Directorate
Identifier 2012–NM–161–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2008–17–
02, AD 2012–08–03, and AD 2012–15–
14, for certain Airbus Model A300 B4–
2C, B4–103, and B4–203 airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model C4–
605R Variant F airplanes (collectively
called A300–600 series airplanes); and
Model A310 series airplanes. AD 2008–
17–02, AD 2012–08–03, and AD 2012–
15–14 currently require repetitive
inspections of the forward lugs of the aft
bearing at rib 5 of the main landing gear
(MLG) on the left-hand (LH) and righthand (RH) wings, and repair if
necessary; and installation of new
bushes with increased interference fit in
the forward lug of the aft bearing at rib
5 of the MLG on the LH and RH wings.
Since we issued AD 2008–17–02, AD
2012–08–03, and AD 2012–15–14, we
have received two reports of ruptured
MLG rib 5 forward lugs that had been
modified (bushes with increased
interference fit). This proposed AD
would add airplanes to the
applicability; and would add, for certain
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SUMMARY:
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airplanes, repetitive inspections of the
MLG rib 5 aft bearing forward lugs, and
repair if necessary. We are proposing
this AD to detect and correct cracking of
the forward lugs of the aft bearing at rib
5 of the MLG on the LH and RH wings,
which could affect the structural
integrity of the MLG attachment,
resulting in possible MLG collapse
during landing or rollout.
DATES: We must receive comments on
this proposed AD by April 28, 2014.
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—
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0142; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this 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.
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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–2014–0142; Directorate Identifier
2012–NM–161–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 July 31, 2008, we issued AD 2008–
17–02, Amendment 39–15640 (73 FR
47032, August 13, 2008), for certain
Model A310 airplanes.
On April 5, 2012, we issued AD 2012–
08–03, Amendment 39–17019 (77 FR
24367, April 24, 2012), for certain
Model A300 B4–2C, B4–103, B4–203,
B4–601, B4–603, B4–620, B4–622, B4–
605R, B4–622R, F4–605R, F4–622R, C4–
605R Variant F airplanes; and Model
A310–203, –204, 221, –222, –304, –322,
–324, and –325 airplanes.
On July 23, 2012, we issued AD 2012–
15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012), for certain
Model A300 B4–2C, B4–103, B4–203,
B4–601, B4–603, B4–620, B4–622, B4–
605R, B4–622R, F4–605R, and F4–622R,
and C4–605R Variant F airplanes.
AD 2008–17–02, Amendment 39–
15640 (73 FR 47032, August 13, 2008);
AD 2012–08–03, Amendment 39–17019
(77 FR 24367, April 24, 2012); and AD
2012–15–14, Amendment 39–17143 (77
FR 46937, August 7, 2012); require
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 2008–17–02,
Amendment 39–15640 (73 FR 47032,
August 13, 2008); AD 2012–08–03,
Amendment 39–17019 (77 FR 24367,
April 24, 2012); and AD 2012–15–14,
Amendment 39–17143 (77 FR 46937,
August 7, 2012); the European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community, has issued
EASA Airworthiness Directive 2012–
0176, dated September 7, 2012,
corrected September 20, 2012 (referred
to after this as the Mandatory
Continuing Airworthiness Information,
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or ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Several cases of corrosion of the Main
Landing Gear (MLG) Rib 5 aft fitting forward
lug have been reported on A310 family
aeroplanes. In some instances, corrosion pits
caused the cracking of the forward lug.
This condition, if not detected and
corrected, may lead to the complete failure of
the fitting and thus could affect the structural
integrity of the MLG installation.
EASA ADs 2006–0372R1 (https://
ad.easa.europa.eu/blob/easa_ad_2006_0372_
R1_superseeded.pdf/AD_2006-0372R1_1),
2007–0195 (https://ad.easa.europa.eu/blob/
easa_ad_2007_0195_superseded.pdf/AD_
2007-0195_1) [which corresponds with FAA
AD 2008–17–02, Amendment 39–15640 (73
FR 47032, August 13, 2008), 2010–0250
(https://ad.easa.europa.eu/blob/easa_ad_
2010_0250_superseded.pdf/AD_2010-0250_
1) [which corresponds with FAA AD 2012–
15–14, Amendment 39–17143 (77 FR 46937,
August 7, 2012)] and 2010–0251 (https://
ad.easa.europa.eu/blob/easa_ad_2010_0251_
superseded.pdf/AD_2010-0251_1) [which
corresponds with FAA AD 2012–08–03,
Amendment 39–17019 (77 FR 24367, April
24, 2012)] were issued to address this
condition and required a repetitive
inspection programme of the MLG Rib 5
fitting forward lugs and, as terminating
action, the embodiment of mandatory design
change (bushes with increased interference
fit).
MLG Rib 5 forward lug on A320 family
aeroplanes is a similar design to the A300/
A300–600/A310 family. Since those [EASA]
ADs were issued, on two A321 aeroplanes,
post modification (bushes with increased
interference fit) MLG Rib 5 forward lugs were
reportedly found ruptured.
One other case was due to a sealant
discrepancy that led to water ingress and
consequently corrosion initiation, leading to
cracking. Subsequent investigation results
have shown that a remaining defect, not
removed during the repair, had propagated,
resulting in rupture of the lug.
For the reasons stated above, this new
[EASA] AD retains the requirements of EASA
ADs 2006–0372R1, 2007–0195, 2010–0250
and 2010–0251, which are superseded,
expands the applicability to all models and
series of A300, A310, A300–600 and A300–
600ST aeroplanes, and requires:
—for aeroplanes not yet modified or repaired,
implementation of Modification Service
Bulletin (SB) A300–57–0249, A310–57–
2090, A300–57–6106, or A300–57–9019,
all at Revision 3, and
—for aeroplanes which already embody that
modifications, at original issue or revision
01 or 02 of the applicable SB, or have MLG
Ribs already repaired in accordance with
Airbus repair instruction R57240221 or
R57249121, implementation of an
additional inspection programme
[repetitive detailed inspection for cracking
or ultrasonic inspections for any crack
indication] and associated corrective
action(s) [detailed inspection for cracking
if any crack indication found, and repair].
The unsafe condition is cracking of the
forward lugs of the aft bearing at rib 5
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of the MLG on the LH and RH wings,
which could affect the structural
integrity of the MLG attachment,
resulting in possible MLG collapse
during landing or rollout. You may
examine the MCAI in the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2014–0142.
Relevant Service Information
Airbus has issued the following
service information.
• Airbus Alert Service Bulletin A300–
57A0248, dated December 12, 2006;
• Airbus Service Bulletin A300–57–
0255, dated January 13, 2012;
• Airbus Service Bulletin A300–57–
6112, dated January 13, 2012;
• Airbus Service Bulletin A310–57–
2101, dated January 13, 2012.
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.
In many FAA transport ADs, when
the service information specifies to
contact the manufacturer for further
instructions if certain discrepancies are
found, we typically include in the AD
a requirement to accomplish the action
using a method approved by either the
FAA or the State of Design Authority (or
its delegated agent).
We have recently been notified that
certain laws in other countries do not
allow such delegation of authority, but
some countries do recognize design
approval organizations. In addition, we
have become aware that some U.S.
operators have used repair instructions
that were previously approved by a
State of Design Authority or a Design
Approval Holder (DAH) as a method of
compliance with this provision in FAA
ADs. Frequently, in these cases, the
previously approved repair instructions
come from the airplane structural repair
manual or the DAH repair approval
statements that were not specifically
developed to address the unsafe
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13939
condition corrected by the AD. Using
repair instructions that were not
specifically approved for a particular
AD creates the potential for doing
repairs that were not developed to
address the unsafe condition identified
by the MCAI AD, the FAA AD, or the
applicable service information, which
could result in the unsafe condition not
being fully corrected.
To prevent the use of repairs that
were not specifically developed to
correct the unsafe condition, certain
requirements of this proposed AD
specify that the repair approval
specifically refer to the FAA AD. This
change is intended to clarify the method
of compliance and to provide operators
with better visibility of repairs that are
specifically developed and approved to
correct the unsafe condition. In
addition, we use the phrase ‘‘its
delegated agent, or the DAH with State
of Design Authority design organization
approval, as applicable’’ in this
proposed AD to refer to a DAH
authorized to approve certain required
repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD
affects 194 airplanes of U.S. registry.
The actions that are required by AD
2008–17–02, Amendment 39–15640 (73
FR 47032, August 13, 2008), and
retained in this proposed AD take about
5 work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that were required by AD
2008–17–02 is $425 per product.
The actions that are required by AD
2012–08–03, Amendment 39–17019 (77
FR 24367, April 24, 2012), and retained
in this proposed AD take about 38 workhours per product, at an average labor
rate of $85 per work-hour. Required
parts cost about $4,590 per product.
Based on these figures, the estimated
cost of the actions that were required by
AD 2012–08–03 is $7,820 per product.
The actions that are required by AD
2012–15–14, Amendment 39–17143 (77
FR 46937, August 7, 2012), 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
actions that were required by AD 2012–
15–14 is $255 per product.
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
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $49,470, or $255 per product.
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD. We have
no way of determining the number of
products that may need these actions.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to 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 control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is 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.
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Authority for This Rulemaking
17:07 Mar 11, 2014
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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
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.
VerDate Mar<15>2010
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.
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directives
(AD) 2008–17–02, Amendment 39–
15640 (73 FR 47032, August 13, 2008);
AD 2012–08–03, Amendment 39–17019
(77 FR 24367, April 24, 2012); and AD
2012–15–14, Amendment 39–17143 (77
FR 46937, August 7, 2012); and
■ b. Adding the following new AD:
■
■
Airbus: Docket No. FAA–2013–0142;
Directorate Identifier 2012–NM–161–AD.
(a) Comments Due Date
We must receive comments by April 28,
2014.
(b) Affected ADs
(1) This AD supersedes the ADs specified
in paragraphs (b)(1)(i), (b)(1)(ii), and (b)(1)(iii)
of this AD.
(i) AD 2008–17–02, Amendment 39–15640
(73 FR 47032, August 13, 2008).
(ii) AD 2012–08–03, Amendment 39–17019
(77 FR 24367, April 24, 2012).
(iii) AD 2012–15–14, Amendment 39–
17143 (77 FR 46937, August 7, 2012).
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(2) This AD affects AD 2007–03–18,
Amendment 39–14929 (72 FR 5919, February
8, 2007).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, and B2–203 airplanes; Model A300
B4–2C, B4–103, and B4–203 airplanes; Model
A300 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.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(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 main
landing gear (MLG) rib 5 aft bearing
attachment. We are issuing this AD to detect
and correct cracking of the forward lugs of
the aft bearing at rib 5 of the MLG on the lefthand (LH) and right-hand (RH) wings, which
could affect the structural integrity of the
MLG attachment, resulting in possible MLG
collapse during landing or rollout.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Detailed Inspection
and Corrective Actions
This paragraph restates the requirements of
paragraph (f) of AD 2008–17–02, Amendment
39–15640 (73 FR 47032, August 13, 2008).
For Model A310 airplanes, except for those
where LH and RH wing MLG rib 5 forward
lugs have been repaired by installation of
oversized interference fit bushes as per
Airbus A310 Repair Instruction R572–49121,
or which have had Airbus Service Bulletin
A310–57–2090 (Airbus Modification 13329)
embodied in service: Do the actions specified
in paragraphs (g)(1), (g)(2), and (g)(3) of this
AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57A2088, dated November 6, 2006.
(1) Before the accumulation of 12,000 total
flight cycles, or within 14 days after February
6, 2007 (the effective date of AD 2007–02–09,
Amendment 39–14896 (72 FR 2612, January
22, 2007)), whichever occurs later: Perform a
detailed visual inspection of the LH and RH
wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH
aft bearing forward lug, contact Airbus and
proceed with the replacement before next
flight.
(3) Repeat the inspection at intervals not
exceeding 100 flight cycles.
(h) Retained Actions and Compliance
This paragraph restates the requirements of
paragraph (g) of AD 2008–17–02,
Amendment 39–15640 (73 FR 47032, August
13, 2008), with new service information for
paragraphs (h)(2), (h)(3), and (h)(4)(ii) of this
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AD. For Model A310 airplanes, except for
those where LH and RH wing MLG rib 5
forward lugs have been repaired by
installation of oversized interference fit
bushes as per Airbus A310 Repair Instruction
R572–49121, or which have had Airbus
Service Bulletin A310–57–2090 (Airbus
Modification 13329) embodied in service:
Before the accumulation of 12,000 total flight
cycles or before the accumulation of 12,000
flight cycles on MLG rib 5, or within 14 days
after September 17, 2008 (the effective date
of AD 2008–17–02), whichever occurs latest,
perform either a detailed visual inspection
(DVI) or an ultrasonic inspection of the LH
and RH MLG rib 5 aft bearing forward lug for
cracks, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–57–2091, excluding
Appendix 01, dated May 22, 2007. If a MLG
rib 5 has been replaced on one side only,
then the LH and RH must be considered
separately. Doing this inspection ends the
requirements of paragraph (g) for that MLG
rib 5 only.
Note 1 to paragraph (h) of this AD: The
ultrasonic inspection will detect any crack at
an early stage and will limit the risk of
extensive repairs. This earlier crack detection
is not possible with the DVI.
(1) If no crack is detected during any
inspection required by paragraph (h) of this
AD: Repeat the applicable inspection at the
time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not
to exceed 100 flight cycles.
(ii) Repeat the ultrasonic inspection
thereafter at intervals not to exceed 825 flight
cycles.
(2) Replacement of the MLG rib 5 bushes
with new bushes with high interference fit in
the aft bearing forward lugs of MLG rib 5, in
accordance with the Accomplishment
Instructions of a service bulletin specified in
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of
this AD, ends the repetitive inspections
required by paragraph (h)(1) of this AD for
that MLG rib 5 only. As of the effective date
of this AD, use only Airbus Service Bulletin
A310–57–2090, Revision 03, dated January
23, 2012, for the actions specified in this
paragraph.
(i) Airbus Service Bulletin A310–57–2090,
Revision 01, dated December 19, 2007.
(ii) Airbus Service Bulletin A310–57–2090,
Revision 02, dated June 18, 2010.
(iii) Airbus Service Bulletin A310–57–
2090, Revision 03, dated January 23, 2012.
(3) If any crack is detected during the DVI
required by paragraph (h) of this AD: Before
further flight, contact Airbus for replacement
instructions and replace the MLG rib 5
bushes before further flight. Repeat the
applicable inspection in paragraph (h) of this
AD at the time specified in paragraph (h)(1)(i)
or (h)(1)(ii) of this AD. Accomplishing the
replacement of the MLG rib 5 bushes with
new bushes with high interference fit in the
aft bearing forward lugs of MLG rib 5, in
accordance with the Accomplishment
Instructions of a service bulletin specified in
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of
this AD, ends the repetitive inspections
required by paragraph (h)(1) of this AD for
that MLG rib 5 only. As of the effective date
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of this AD, use only Airbus Service Bulletin
A310–57–2090, Revision 03, dated January
23, 2012, for the actions specified in this
paragraph.
(4) If any crack is detected during the
ultrasonic inspection required by paragraph
(h) of this AD, before further flight,
accomplish the actions specified in
paragraph (h)(4)(i) or (h)(4)(ii) of this AD, as
applicable.
(i) If any crack is not visible on MLG rib
5: Before further flight, repair MLG rib 5
using Airbus A310 Repair Instruction R572–
49121, Issue C, dated May 2007. After
embodiment of the repair instruction, no
further actions are necessary as required by
paragraph (g) and (h) of this AD and specified
in Airbus Service Bulletin A310–57–2091,
excluding Appendix 01, dated May 22, 2007,
for that MLG rib 5 only.
(ii) If any crack is visible on MLG rib 5:
Before further flight, contact Airbus for rib
replacement instructions, and replace before
further flight. Repeat the applicable
inspection in paragraph (h) of this AD at the
time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD. Accomplishing the
replacement of the MLG rib 5 bushes with
new bushes with high interference fit in the
aft bearing forward lugs of MLG rib 5, in
accordance with the Accomplishment
Instructions of a service bulletin specified in
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of
this AD, ends the repetitive inspections
required by paragraph (h) of this AD for that
MLG rib 5 only.
(i) Retained Installation
This paragraph restates the requirements of
paragraph (g) of AD 2012–08–03,
Amendment 39–17019 (77 FR 24367, April
24, 2012), and applies to the airplanes
identified in paragraph (j) of this AD. Within
30 months after May 29, 2012 (the effective
date of AD 2012–08–03), install new bushes
with increased interference fit in the gear rib
5 aft bearing forward lug on the LH and RH
wings, in accordance with the
Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (i)(1), (i)(2), or (i)(3) of this AD;
except as specified in paragraph (k) of this
AD.
(1) Airbus Mandatory Service Bulletin
A300–57–0249, Revision 03, dated January
18, 2012 (for Model A300 B4–2C, B4–103,
and B4–203 airplanes).
(2) Airbus Mandatory Service Bulletin
A300–57–6106, Revision 03, dated January
26, 2012 (for Model A300–600 series
airplanes).
(3) Airbus Mandatory Service Bulletin
A310–57–2090, Revision 03, dated January
23, 2012 (for Model A310 series airplanes).
(j) Affected Airplanes for the Actions
Required by Paragraph (i) of This AD
For airplanes identified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD: Do the
actions required by paragraph (i) of this AD.
(1) Airbus Model A300 B4–2C, B4–103,
and B4–203 airplanes; all serial numbers;
except airplanes on which the MLG rib 5
forward lugs of the LH and RH wings have
been repaired by installation of oversized
interference fit bushes specified in Airbus
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13941
Repair Instruction R57240221, or those on
which the LH and RH wings have had Airbus
Mandatory Service Bulletin A300–57–0249
embodied in service.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes; Airbus Model
A300 B4–605R and B4–622R airplanes;
Airbus Model A300 F4–605R and F4–622R
airplanes; and Airbus Model A300 C4–605R
Variant F airplanes; all serial numbers;
except airplanes on which the MLG rib 5
forward lugs of the LH and RH wings have
been repaired by installation of oversized
interference fit bushes specified in Airbus
Repair Instruction R57240221, or those on
which the LH and RH wings have had Airbus
Service Bulletin A300–57–6106 embodied in
service.
(3) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes;
all serial numbers; except airplanes on which
the MLG rib 5 forward lugs of the LH and RH
wings have been repaired by installation of
oversized interference fit bushes specified in
Airbus Repair Instruction R57249121, or
those on which the LH and RH wings have
had Airbus Mandatory Service Bulletin
A310–57–2090 embodied in service.
(k) Retained Exception
This paragraph restates the requirements of
paragraph (h) of AD 2012–08–03,
Amendment 39–17019 (77 FR 24367, April
24, 2012), and applies to the airplanes
identified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD. If one wing had rib 5 forward lugs
of the MLG repaired by installing oversized
interference fit bushes, as specified in Airbus
Repair Instruction R57240221 or Airbus
Repair Instruction R57249121, as applicable
to the airplane model, then installing new
bushes with increased interference fit in the
aft bearing forward lug of the gear rib, as
specified in paragraph (i) of this AD, is
required for the opposite wing only.
(l) Retained Terminating Action for Certain
Inspections
This paragraph restates the requirements of
paragraph (i) of AD 2012–08–03, Amendment
39–17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
Installation of new bushes, as specified in
paragraph (i) of this AD, is terminating action
for the repetitive inspections required by AD
2007–03–18, Amendment 39–14929 (72 FR
5919, February 8, 2007); and by paragraphs
(g) and (h) of this AD.
(m) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (g) of AD 2012–15–14,
Amendment 39–17143 (77 FR 46937, August
7, 2012), and applies to the airplanes
identified in paragraph (n) of this AD. Except
as provided by paragraph (o) 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 September 11, 2012 (the effective date
of AD 2012–15–14, Amendment 39–17143
(77 FR 46937, August 7, 2012)), 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,
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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 (m)(1) or (m)(2) of this AD, until
the modification specified in paragraph (q) 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.
Holder with EASA’s design organization
approval, as applicable).
(o) Retained Exception
This paragraph restates the requirements of
paragraph (h) of AD 2012–15–14,
Amendment 39–17143 (77 FR 46937, August
7, 2012), and applies to the airplanes
identified in paragraph (n) of this AD on
which an inspection required by AD 2007–
03–18, Amendment 39–14929 (72 FR 5919,
February 8, 2007), has been done as of
September 11, 2012 (the effective date of AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012)): Within 100 flight
cycles after doing the most recent inspection
required by AD 2007–03–18, or within 10
days after September 11, 2012, whichever
occurs later, do a detailed or ultrasonic
inspection as specified in paragraph (m) of
this AD. Repeat the applicable inspection
thereafter at the times specified in paragraph
(m) of this AD.
(q) Retained Optional Terminating
Modification
This paragraph restates the optional
terminating modification of paragraph (j) of
AD 2012–15–14, Amendment 39–17143 (77
FR 46937, August 7, 2012), and applies to the
airplanes identified in paragraph (n) of this
AD. Performing the applicable actions
specified in paragraphs (q)(1), (q)(2), (q)(3),
and (q)(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 Mandatory Service Bulletin A300–
57–6106, Revision 03, dated January 26, 2012
(for Model A300–600 series airplanes);
terminates the repetitive inspections required
by paragraph (m) of 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
Bulletin A300–57–0249, Revision 02, dated
June 18, 2010 (for Model A300 B4–103, B4–
203, and B4–2C airplanes); or Airbus
Mandatory Service Bulletin A300–57–6106,
Revision 03, dated January 26, 2012 (for
Model A300–600 series airplanes).
(3) If damage or corrosion is detected
during any inspection specified in paragraph
(q)(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 Mandatory Service Bulletin A300–
57–6106, Revision 03, dated January 26, 2012
(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
EASA (or its delegated agent, or the Design
Approval Holder with EASA’s design
organization approval, as applicable).
(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 Mandatory Service Bulletin A300–
57–6106, Revision 03, dated January 26, 2012
(for Model A300–600 series airplanes).
(p) Retained Repair
This paragraph restates the requirements of
paragraph (i) of AD 2012–15–14, Amendment
39–17143 (77 FR 46937, August 7, 2012). 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 (m) of this AD, before further
flight, repair using a method approved by
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or
its delegated agent, or the Design Approval
(r) Retained Terminating Action for AD
2007–03–18, Amendment 39–14929 (72 FR
5919, February 8, 2007)
This paragraph restates the terminating
action statement of paragraph (k) of AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012), and applies to the
airplanes identified in paragraph (n) of this
AD. Doing the actions required by paragraph
(q) of this AD terminates the inspections
required by AD 2007–03–18, Amendment
39–14929 (72 FR 5919, February 8, 2007), for
that airplane.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(n) Affected Airplanes for the Actions
Required by Paragraph (m) of This AD
For Airbus Model A300 B4–2C, B4–103,
and B4–203 airplanes; Model A300 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; all
serial numbers; except for airplanes
identified in paragraphs (n)(1), (n)(2), and
(n)(3) of this AD: Do the actions required by
paragraph (m) of this AD, except as provided
by paragraph (o) of this AD.
(1) Airplanes on which LH and RH wing
MLG rib 5 forward lugs have oversized
interference fit bushings installed per Airbus
Repair Instruction 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 wings.
(3) Model A300–600 series airplanes on
which Airbus Mandatory Service Bulletin
A300–57–6106 has been done in service on
the LH and RH wings.
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(s) Retained Reporting
This paragraph restates the requirements of
paragraph (l) of AD 2012–15–14, Amendment
39–17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in
paragraph (n) of this AD. 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 (m) 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 (s)(1)
or (s)(2) of this AD.
(1) If the inspection was done on or after
September 11, 2012 (the effective date of AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012)): Submit the report
within 30 days after the inspection.
(2) If the inspection was done before
September 11, 2012 (the effective date of AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012)): Submit the report
within 30 days after September 11, 2012.
(t) New Repetitive Inspections
For airplanes identified in paragraph (u) of
this AD: At the applicable time specified in
paragraph (v)(1) or (v)(2) of this AD, do a
detailed inspection for cracking, or an
ultrasonic inspection for any crack
indications of the LH and RH MLG rib 5 aft
bearing forward lugs, in accordance with the
Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (t)(1), (t)(2), or (t)(3) of this AD.
Repeat the inspection thereafter at intervals
not to exceed the applicable time specified in
paragraph (v)(3) or (v)(4) of this AD.
(1) Airbus Mandatory Service Bulletin
A300–57–0255, dated January 13, 2012 (for
Model A300 B2–1A, B2–1C, B2K–3C, and
B2–203 airplanes).
(2) Airbus Mandatory Service Bulletin
A300–57–6112, dated January 13, 2012 (for
Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R, F4–605R, and F4–
622R airplanes).
(3) Airbus Mandatory Service Bulletin
A310–57–2101, dated January 13, 2012 (for
Model A310–203, –204, –221, –222, –304,
–322, –324, and –325 airplanes).
(u) Affected Airplanes for the Actions
Required by Paragraph (t) of This AD
For airplanes on which any modification or
repair described in the service bulletins
identified in paragraph (u)(1), (u)(2), or (u)(3)
of this AD, as applicable, has been
accomplished in service; and for airplanes
with MLG rib 5 already repaired as specified
in Airbus Repair Instruction R57240221 or
R57249121, including any airplane with the
MLG rib 5 forward lugs repaired on one
wing; by installation of oversized
interference fit bushes, as specified in Airbus
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Repair Instruction R57240221 or R57249121,
as applicable: Do the actions required by
paragraph (t) of this AD.
(1) Airbus Service Bulletin A300–57–0249,
dated May 22, 2007; Revision 01, dated
December 19, 2007; or Airbus Service
Bulletin A300–57–0249, Revision 02, dated
June 18, 2010 (for Model A300 B4–2C, B4–
103, and B4–203 airplanes).
(2) Airbus Service Bulletin A300–57–6106,
dated May 22, 2007; Revision 01, dated
January 28, 2008; or Airbus 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 Variant F airplanes).
(3) Airbus Service Bulletin A310–57–2090,
dated May 22, 2007; Revision 01, dated
December 19, 2007; or Airbus Service
Bulletin A310–57–2090 Revision 02, dated
June 18, 2010 (for Model A310 series
airplanes).
tkelley on DSK3SPTVN1PROD with PROPOSALS
(v) Compliance Times for Paragraph (t) of
This AD
This paragraph specifies the compliance
times for the actions specified in paragraph
(t) of this AD.
(1) For airplanes identified in paragraph
(c)(1) of this AD: Do the initial inspection
required by paragraph (t) of this AD within
2,500 flight cycles after any modification or
repair specified in paragraph (u) of this AD
was done, or within 550 flight cycles after the
effective date of this AD, whichever occurs
later.
(2) For airplanes identified in paragraph
(c)(2) of this AD: Do the initial inspection
required by paragraph (t) of this AD within
2,500 flight cycles after any modification or
repair specified in paragraph (u) of this AD
was done, or within 775 flight cycles after the
effective date of this AD, whichever occurs
later.
(3) For airplanes identified in paragraph
(c)(1) of this AD: For the repetitive inspection
required by paragraph (t) of this AD, repeat
the inspection within 550 flight cycles after
any detailed inspection, and within 1,000
flight cycles after any ultrasonic inspection,
as applicable.
(4) For airplanes identified in paragraph
(c)(2) of this AD: For the repetitive inspection
required by paragraph (t) of this AD, repeat
the inspection within 775 flight cycles after
any detailed inspection, and within 1,300
flight cycles after any ultrasonic inspection,
as applicable.
(w) New Requirement of This AD: Report
and Detailed Inspection
If, during any ultrasonic inspection
required by paragraph (t) of this AD, any
crack indication is detected: Before further
flight, report to Airbus using the applicable
report sheet attached to the applicable Airbus
service bulletin specified in paragraph (t)(1),
(t)(2), or (t)(3) of this AD, and concurrently
accomplish a detailed inspection for cracking
of the affected MLG rib 5 aft bearing forward
lug, in accordance with the Accomplishment
Instructions of the applicable Airbus service
bulletin specified in paragraph (t)(1), (t)(2), or
(t)(3) of this AD. Repeat the detailed
inspection thereafter at intervals not to
exceed 100 flight cycles.
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(x) New Requirement of This AD: Cracking
Repair
If any cracking is detected during any
detailed inspection required by paragraph (t)
or (w) of this AD: Before further flight, repair
the cracking using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
EASA (or its delegated agent, or the Design
Approval Holder with the EASA design
organization approval, as applicable). For a
repair method to be approved, the repair
approval must specifically refer to this AD.
(y) New Requirement of This AD: Reporting
Submit a report (including both positive
and negative findings), using the reporting
sheet attached to the applicable Airbus
service bulletin specified in paragraph (y)(1),
(y)(2), or (y)(3) of this AD, of the first
inspection required by paragraph (t) 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. Submit the report
within 30 days after the inspection or within
30 days after the effective date of this AD,
whichever occurs later.
(1) Airbus Mandatory Service Bulletin
A300–57–0255, dated January 13, 2012 (for
Model A300 B2–1A, B2–1C, B2K–3C, and
B2–203 airplanes).
(2) Airbus Mandatory Service Bulletin
A300–57–6112, dated January 13, 2012 (for
Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R, F4–605R, and F4–
622R airplanes).
(3) Airbus Mandatory Service Bulletin
A310–57–2101, dated January 13, 2012 (for
Model A310–203, –204, –221, –222, –304,
–322, –324, and –325 airplanes).
(z) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (i) of this AD,
if those actions were performed before May
29, 2012 (the effective date of AD 2012–08–
03, Amendment 39–17019 (77 FR 24367,
April 24, 2012)), using an applicable service
bulletin specified in paragraph (z)(1)(i),
(z)(1)(ii), or (z)(1)(iii) of this AD.
(i) For Model A300 B4–2C, B4–103, and
B4–203 airplanes: The service bulletins are
specified in paragraphs (z)(1)(i)(A),
(z)(1)(i)(B), and (z)(1)(i)(C) of this AD.
(A) Airbus Service Bulletin A300–57–0249,
dated May 22, 2007, which is not
incorporated by reference in this AD.
(B) Airbus Service Bulletin A300–57–0249,
Revision 01, dated December 19, 2007, which
is not incorporated by reference in this AD.
(C) Airbus Mandatory Service Bulletin
A300–57–0249, Revision 02, dated June 18,
2010.
(ii) For Model A300–600 series airplanes:
The service bulletins are specified in
paragraphs (z)(1)(ii)(A), (z)(1)(ii)(B), and
(z)(1)(ii)(C) of this AD.
(A) Airbus Service Bulletin A300–57–6106,
May 22, 2007, which is not incorporated by
reference in this AD.
(B) Airbus Service Bulletin A300–57–6106,
Revision 01, January 28, 2008, which is not
incorporated by reference in this AD.
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(C) Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010, which is
not incorporated by reference in this AD.
(iii) For Model A310 series airplanes: The
service bulletins are specified in paragraphs
(z)(1)(iii)(A), (z)(1)(iii)(B), and (z)(1)(iii)(C) of
this AD.
(A) Airbus Service Bulletin A310–57–2090,
dated May 22, 2007, which is not
incorporated by reference in this AD.
(B) Airbus Service Bulletin A310–57–2090,
Revision 01, dated December 19, 2007.
(C) Airbus Service Bulletin A310–57–2090,
Revision 02, dated June 18, 2010, which is
not incorporated by reference in this AD.
(2) This paragraph provides credit for
actions required by paragraph (q) of this AD,
if those actions were performed before
September 11, 2012 (the effective date of AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012)), using an applicable
service bulletin specified in paragraphs
(z)(2)(i), (z)(2)(ii), (z)(2)(iii), (z)(2)(iv), and
(z)(2)(v) of this AD.
(i) For Model A300 B4–2C, B4–103, and
B4–203: Airbus Service Bulletin A300–57–
0249, dated May 22, 2007, which is not
incorporated by reference in this AD.
(ii) For Model A300 B4–2C, B4–103, and
B4–203: Airbus Service Bulletin A300–57–
0249, Revision 01, dated December 19, 2007,
which is not incorporated by reference in this
AD.
(iii) For Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes:
Airbus Service Bulletin A300–57–6106,
dated May 22, 2007, which is not
incorporated by reference in this AD.
(iv) For Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes:
Airbus Service Bulletin A300–57–6106,
Revision 01, dated January 28, 2008, which
is not incorporated by reference in this AD.
(v) For Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes:
Airbus Service Bulletin A300–57–6106,
Revision 02, dated June 18, 2010 which is not
incorporated by reference in this AD.
(aa) 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;
phone (425) 227–2125; fax (425) 227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
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standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(i) AMOCs approved previously for AD
2008–17–02, Amendment 39–15640 (73 FR
47032, August 13, 2008), are approved as
AMOCs for the corresponding provisions of
paragraphs (g) and (h) of this AD.
(ii) AMOCs approved previously for AD
2012–08–03, Amendment 39–17019 (77 FR
24367, April 24, 2012), are approved as
AMOCs for the corresponding provisions of
paragraphs (i), (j), and (k) of this AD.
(iii) AMOCs approved previously for AD
2012–15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012), are approved as
AMOCs for the corresponding provisions of
paragraphs (l), (m), (n), and (o) of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the Design Approval
Holder with a State of Design Authority’s
design organization approval, as applicable).
You are required to ensure 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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(bb) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0176, dated September 7,
2012, corrected September 20, 2012, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2014–0142.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
VerDate Mar<15>2010
17:07 Mar 11, 2014
Jkt 232001
Issued in Renton, Washington, on March 4,
2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–05435 Filed 3–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0138; Directorate
Identifier 2013–NM–020–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 95–24–04,
that applies to all Airbus Model A300
series airplanes; Model A300 B4–600,
B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). AD 95–24–
04 requires repetitive inspections to
detect cracks at the aft spar web of the
wings, and repair if necessary. Since we
issued AD 95–24–04, we have
determined that the inspection
threshold and interval must be reduced
to allow timely detection of cracks and
accomplishment of applicable repairs,
because of cracking in the rear spar web
of the wings between certain ribs due to
fatigue-related high shear stress. This
proposed AD would reduce the
inspection compliance time and
interval, and would expand the
applicability to airplanes on which a
certain Airbus modification has been
embodied in production and to
airplanes on which a certain Airbus
service bulletin has been embodied in
service. We are proposing this AD to
detect and correct fatigue-related
cracking, which could result in reduced
structural integrity of the wing.
DATES: We must receive comments on
this proposed AD by April 28, 2014.
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
SUMMARY:
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
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,
Airworthiness Office—EAW, 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 view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
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 MCAI,
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–2014–0138; Directorate Identifier
2013–NM–020–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
E:\FR\FM\12MRP1.SGM
12MRP1
]]>Agencies
[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13938-13944]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05435]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0142; Directorate Identifier 2012-NM-161-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 Airworthiness Directive (AD) 2008-17-
02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model A300 B4-
2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model C4-605R Variant F airplanes
(collectively called A300-600 series airplanes); and Model A310 series
airplanes. AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14 currently
require repetitive inspections of the forward lugs of the aft bearing
at rib 5 of the main landing gear (MLG) on the left-hand (LH) and
right-hand (RH) wings, and repair if necessary; and installation of new
bushes with increased interference fit in the forward lug of the aft
bearing at rib 5 of the MLG on the LH and RH wings. Since we issued AD
2008-17-02, AD 2012-08-03, and AD 2012-15-14, we have received two
reports of ruptured MLG rib 5 forward lugs that had been modified
(bushes with increased interference fit). This proposed AD would add
airplanes to the applicability; and would add, for certain airplanes,
repetitive inspections of the MLG rib 5 aft bearing forward lugs, and
repair if necessary. We are proposing this AD to detect and correct
cracking of the forward lugs of the aft bearing at rib 5 of the MLG on
the LH and RH wings, which could affect the structural integrity of the
MLG attachment, resulting in possible MLG collapse during landing or
rollout.
DATES: We must receive comments on this proposed AD by April 28, 2014.
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--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0142; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this 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-2014-0142;
Directorate Identifier 2012-NM-161-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 July 31, 2008, we issued AD 2008-17-02, Amendment 39-15640 (73
FR 47032, August 13, 2008), for certain Model A310 airplanes.
On April 5, 2012, we issued AD 2012-08-03, Amendment 39-17019 (77
FR 24367, April 24, 2012), for certain Model A300 B4-2C, B4-103, B4-
203, B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-
622R, C4-605R Variant F airplanes; and Model A310-203, -204, 221, -222,
-304, -322, -324, and -325 airplanes.
On July 23, 2012, we issued AD 2012-15-14, Amendment 39-17143 (77
FR 46937, August 7, 2012), for certain Model A300 B4-2C, B4-103, B4-
203, B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-
622R, and C4-605R Variant F airplanes.
AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008);
AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012); and AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012); require
actions intended to address an unsafe condition on the products listed
above.
Since we issued AD 2008-17-02, Amendment 39-15640 (73 FR 47032,
August 13, 2008); AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April
24, 2012); and AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August
7, 2012); the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2012-0176, dated September 7, 2012,
corrected September 20, 2012 (referred to after this as the Mandatory
Continuing Airworthiness Information,
[[Page 13939]]
or ``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Several cases of corrosion of the Main Landing Gear (MLG) Rib 5
aft fitting forward lug have been reported on A310 family
aeroplanes. In some instances, corrosion pits caused the cracking of
the forward lug.
This condition, if not detected and corrected, may lead to the
complete failure of the fitting and thus could affect the structural
integrity of the MLG installation.
EASA ADs 2006-0372R1 (https://ad.easa.europa.eu/blob/easa_ad_2006_0372_R1_superseeded.pdf/AD_2006-0372R1_1), 2007-0195
(https://ad.easa.europa.eu/blob/easa_ad_2007_0195_superseded.pdf/AD_2007-0195_1) [which corresponds with FAA AD 2008-17-02,
Amendment 39-15640 (73 FR 47032, August 13, 2008), 2010-0250 (https://ad.easa.europa.eu/blob/easa_ad_2010_0250_superseded.pdf/AD_2010-0250_1) [which corresponds with FAA AD 2012-15-14, Amendment
39-17143 (77 FR 46937, August 7, 2012)] and 2010-0251 (https://ad.easa.europa.eu/blob/easa_ad_2010_0251_superseded.pdf/AD_2010-0251_1) [which corresponds with FAA AD 2012-08-03, Amendment
39-17019 (77 FR 24367, April 24, 2012)] were issued to address this
condition and required a repetitive inspection programme of the MLG
Rib 5 fitting forward lugs and, as terminating action, the
embodiment of mandatory design change (bushes with increased
interference fit).
MLG Rib 5 forward lug on A320 family aeroplanes is a similar
design to the A300/A300-600/A310 family. Since those [EASA] ADs were
issued, on two A321 aeroplanes, post modification (bushes with
increased interference fit) MLG Rib 5 forward lugs were reportedly
found ruptured.
One other case was due to a sealant discrepancy that led to
water ingress and consequently corrosion initiation, leading to
cracking. Subsequent investigation results have shown that a
remaining defect, not removed during the repair, had propagated,
resulting in rupture of the lug.
For the reasons stated above, this new [EASA] AD retains the
requirements of EASA ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-
0251, which are superseded, expands the applicability to all models
and series of A300, A310, A300-600 and A300-600ST aeroplanes, and
requires:
--for aeroplanes not yet modified or repaired, implementation of
Modification Service Bulletin (SB) A300-57-0249, A310-57-2090, A300-
57-6106, or A300-57-9019, all at Revision 3, and
--for aeroplanes which already embody that modifications, at
original issue or revision 01 or 02 of the applicable SB, or have
MLG Ribs already repaired in accordance with Airbus repair
instruction R57240221 or R57249121, implementation of an additional
inspection programme [repetitive detailed inspection for cracking or
ultrasonic inspections for any crack indication] and associated
corrective action(s) [detailed inspection for cracking if any crack
indication found, and repair].
The unsafe condition is cracking of the forward lugs of the aft bearing
at rib 5 of the MLG on the LH and RH wings, which could affect the
structural integrity of the MLG attachment, resulting in possible MLG
collapse during landing or rollout. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov by searching for
and locating it in Docket No. FAA-2014-0142.
Relevant Service Information
Airbus has issued the following service information.
Airbus Alert Service Bulletin A300-57A0248, dated December
12, 2006;
Airbus Service Bulletin A300-57-0255, dated January 13,
2012;
Airbus Service Bulletin A300-57-6112, dated January 13,
2012;
Airbus Service Bulletin A310-57-2101, dated January 13,
2012.
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.
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD specify that the repair approval specifically refer to the FAA AD.
This change is intended to clarify the method of compliance and to
provide operators with better visibility of repairs that are
specifically developed and approved to correct the unsafe condition. In
addition, we use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 194 airplanes of U.S.
registry.
The actions that are required by AD 2008-17-02, Amendment 39-15640
(73 FR 47032, August 13, 2008), and retained in this proposed AD take
about 5 work-hours per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that were required by AD 2008-17-02 is $425 per product.
The actions that are required by AD 2012-08-03, Amendment 39-17019
(77 FR 24367, April 24, 2012), and retained in this proposed AD take
about 38 work-hours per product, at an average labor rate of $85 per
work-hour. Required parts cost about $4,590 per product. Based on these
figures, the estimated cost of the actions that were required by AD
2012-08-03 is $7,820 per product.
The actions that are required by AD 2012-15-14, Amendment 39-17143
(77 FR 46937, August 7, 2012), 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 actions
that were required by AD 2012-15-14 is $255 per product.
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 rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $49,470, or $255
per product.
[[Page 13940]]
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD. We have no way of determining the number of products that may need
these actions.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is 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.
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.
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
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:
0
a. Removing Airworthiness Directives (AD) 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008); AD 2012-08-03, Amendment 39-17019
(77 FR 24367, April 24, 2012); and AD 2012-15-14, Amendment 39-17143
(77 FR 46937, August 7, 2012); and
0
b. Adding the following new AD:
Airbus: Docket No. FAA-2013-0142; Directorate Identifier 2012-NM-
161-AD.
(a) Comments Due Date
We must receive comments by April 28, 2014.
(b) Affected ADs
(1) This AD supersedes the ADs specified in paragraphs
(b)(1)(i), (b)(1)(ii), and (b)(1)(iii) of this AD.
(i) AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13,
2008).
(ii) AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24,
2012).
(iii) AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7,
2012).
(2) This AD affects AD 2007-03-18, Amendment 39-14929 (72 FR
5919, February 8, 2007).
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203
airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A300 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.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(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 main landing gear (MLG) rib 5 aft bearing attachment. We are
issuing this AD to detect and correct cracking of the forward lugs
of the aft bearing at rib 5 of the MLG on the left-hand (LH) and
right-hand (RH) wings, which could affect the structural integrity
of the MLG attachment, resulting in possible MLG collapse during
landing or rollout.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Detailed Inspection and Corrective Actions
This paragraph restates the requirements of paragraph (f) of AD
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008). For
Model A310 airplanes, except for those where LH and RH wing MLG rib
5 forward lugs have been repaired by installation of oversized
interference fit bushes as per Airbus A310 Repair Instruction R572-
49121, or which have had Airbus Service Bulletin A310-57-2090
(Airbus Modification 13329) embodied in service: Do the actions
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57A2088, dated November 6, 2006.
(1) Before the accumulation of 12,000 total flight cycles, or
within 14 days after February 6, 2007 (the effective date of AD
2007-02-09, Amendment 39-14896 (72 FR 2612, January 22, 2007)),
whichever occurs later: Perform a detailed visual inspection of the
LH and RH wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH aft bearing forward
lug, contact Airbus and proceed with the replacement before next
flight.
(3) Repeat the inspection at intervals not exceeding 100 flight
cycles.
(h) Retained Actions and Compliance
This paragraph restates the requirements of paragraph (g) of AD
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008), with
new service information for paragraphs (h)(2), (h)(3), and
(h)(4)(ii) of this
[[Page 13941]]
AD. For Model A310 airplanes, except for those where LH and RH wing
MLG rib 5 forward lugs have been repaired by installation of
oversized interference fit bushes as per Airbus A310 Repair
Instruction R572-49121, or which have had Airbus Service Bulletin
A310-57-2090 (Airbus Modification 13329) embodied in service: Before
the accumulation of 12,000 total flight cycles or before the
accumulation of 12,000 flight cycles on MLG rib 5, or within 14 days
after September 17, 2008 (the effective date of AD 2008-17-02),
whichever occurs latest, perform either a detailed visual inspection
(DVI) or an ultrasonic inspection of the LH and RH MLG rib 5 aft
bearing forward lug for cracks, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2091,
excluding Appendix 01, dated May 22, 2007. If a MLG rib 5 has been
replaced on one side only, then the LH and RH must be considered
separately. Doing this inspection ends the requirements of paragraph
(g) for that MLG rib 5 only.
Note 1 to paragraph (h) of this AD: The ultrasonic inspection
will detect any crack at an early stage and will limit the risk of
extensive repairs. This earlier crack detection is not possible with
the DVI.
(1) If no crack is detected during any inspection required by
paragraph (h) of this AD: Repeat the applicable inspection at the
time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not to exceed 100
flight cycles.
(ii) Repeat the ultrasonic inspection thereafter at intervals
not to exceed 825 flight cycles.
(2) Replacement of the MLG rib 5 bushes with new bushes with
high interference fit in the aft bearing forward lugs of MLG rib 5,
in accordance with the Accomplishment Instructions of a service
bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or
(h)(2)(iii) of this AD, ends the repetitive inspections required by
paragraph (h)(1) of this AD for that MLG rib 5 only. As of the
effective date of this AD, use only Airbus Service Bulletin A310-57-
2090, Revision 03, dated January 23, 2012, for the actions specified
in this paragraph.
(i) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007.
(ii) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010.
(iii) Airbus Service Bulletin A310-57-2090, Revision 03, dated
January 23, 2012.
(3) If any crack is detected during the DVI required by
paragraph (h) of this AD: Before further flight, contact Airbus for
replacement instructions and replace the MLG rib 5 bushes before
further flight. Repeat the applicable inspection in paragraph (h) of
this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii)
of this AD. Accomplishing the replacement of the MLG rib 5 bushes
with new bushes with high interference fit in the aft bearing
forward lugs of MLG rib 5, in accordance with the Accomplishment
Instructions of a service bulletin specified in paragraph (h)(2)(i),
(h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive
inspections required by paragraph (h)(1) of this AD for that MLG rib
5 only. As of the effective date of this AD, use only Airbus Service
Bulletin A310-57-2090, Revision 03, dated January 23, 2012, for the
actions specified in this paragraph.
(4) If any crack is detected during the ultrasonic inspection
required by paragraph (h) of this AD, before further flight,
accomplish the actions specified in paragraph (h)(4)(i) or
(h)(4)(ii) of this AD, as applicable.
(i) If any crack is not visible on MLG rib 5: Before further
flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572-
49121, Issue C, dated May 2007. After embodiment of the repair
instruction, no further actions are necessary as required by
paragraph (g) and (h) of this AD and specified in Airbus Service
Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007,
for that MLG rib 5 only.
(ii) If any crack is visible on MLG rib 5: Before further
flight, contact Airbus for rib replacement instructions, and replace
before further flight. Repeat the applicable inspection in paragraph
(h) of this AD at the time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib
5 bushes with new bushes with high interference fit in the aft
bearing forward lugs of MLG rib 5, in accordance with the
Accomplishment Instructions of a service bulletin specified in
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the
repetitive inspections required by paragraph (h) of this AD for that
MLG rib 5 only.
(i) Retained Installation
This paragraph restates the requirements of paragraph (g) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraph (j) of this AD.
Within 30 months after May 29, 2012 (the effective date of AD 2012-
08-03), install new bushes with increased interference fit in the
gear rib 5 aft bearing forward lug on the LH and RH wings, in
accordance with the Accomplishment Instructions of the applicable
service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD; except as specified in paragraph (k) of this AD.
(1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03,
dated January 18, 2012 (for Model A300 B4-2C, B4-103, and B4-203
airplanes).
(2) Airbus Mandatory Service Bulletin A300-57-6106, Revision 03,
dated January 26, 2012 (for Model A300-600 series airplanes).
(3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03,
dated January 23, 2012 (for Model A310 series airplanes).
(j) Affected Airplanes for the Actions Required by Paragraph (i) of
This AD
For airplanes identified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD: Do the actions required by paragraph (i) of this
AD.
(1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all
serial numbers; except airplanes on which the MLG rib 5 forward lugs
of the LH and RH wings have been repaired by installation of
oversized interference fit bushes specified in Airbus Repair
Instruction R57240221, or those on which the LH and RH wings have
had Airbus Mandatory Service Bulletin A300-57-0249 embodied in
service.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus
Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-
605R Variant F airplanes; all serial numbers; except airplanes on
which the MLG rib 5 forward lugs of the LH and RH wings have been
repaired by installation of oversized interference fit bushes
specified in Airbus Repair Instruction R57240221, or those on which
the LH and RH wings have had Airbus Service Bulletin A300-57-6106
embodied in service.
(3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; all serial numbers; except airplanes on which
the MLG rib 5 forward lugs of the LH and RH wings have been repaired
by installation of oversized interference fit bushes specified in
Airbus Repair Instruction R57249121, or those on which the LH and RH
wings have had Airbus Mandatory Service Bulletin A310-57-2090
embodied in service.
(k) Retained Exception
This paragraph restates the requirements of paragraph (h) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraphs (j)(1), (j)(2),
and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG
repaired by installing oversized interference fit bushes, as
specified in Airbus Repair Instruction R57240221 or Airbus Repair
Instruction R57249121, as applicable to the airplane model, then
installing new bushes with increased interference fit in the aft
bearing forward lug of the gear rib, as specified in paragraph (i)
of this AD, is required for the opposite wing only.
(l) Retained Terminating Action for Certain Inspections
This paragraph restates the requirements of paragraph (i) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraphs (j)(1), (j)(2),
and (j)(3) of this AD. Installation of new bushes, as specified in
paragraph (i) of this AD, is terminating action for the repetitive
inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR
5919, February 8, 2007); and by paragraphs (g) and (h) of this AD.
(m) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (g) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD.
Except as provided by paragraph (o) 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 September 11, 2012 (the
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012)), 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,
[[Page 13942]]
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 (m)(1) or (m)(2) of
this AD, until the modification specified in paragraph (q) 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.
(n) Affected Airplanes for the Actions Required by Paragraph (m) of
This AD
For Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A300 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; all
serial numbers; except for airplanes identified in paragraphs
(n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by
paragraph (m) of this AD, except as provided by paragraph (o) of
this AD.
(1) Airplanes on which LH and RH wing MLG rib 5 forward lugs
have oversized interference fit bushings installed per Airbus Repair
Instruction 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 wings.
(3) Model A300-600 series airplanes on which Airbus Mandatory
Service Bulletin A300-57-6106 has been done in service on the LH and
RH wings.
(o) Retained Exception
This paragraph restates the requirements of paragraph (h) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD on
which an inspection required by AD 2007-03-18, Amendment 39-14929
(72 FR 5919, February 8, 2007), has been done as of September 11,
2012 (the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR
46937, August 7, 2012)): Within 100 flight cycles after doing the
most recent inspection required by AD 2007-03-18, or within 10 days
after September 11, 2012, whichever occurs later, do a detailed or
ultrasonic inspection as specified in paragraph (m) of this AD.
Repeat the applicable inspection thereafter at the times specified
in paragraph (m) of this AD.
(p) Retained Repair
This paragraph restates the requirements of paragraph (i) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012). 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 (m) of this AD, before further flight, repair using a
method approved by Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA) (or its delegated agent, or the Design Approval Holder with
EASA's design organization approval, as applicable).
(q) Retained Optional Terminating Modification
This paragraph restates the optional terminating modification of
paragraph (j) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012), and applies to the airplanes identified in
paragraph (n) of this AD. Performing the applicable actions
specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(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
Mandatory Service Bulletin A300-57-6106, Revision 03, dated January
26, 2012 (for Model A300-600 series airplanes); terminates the
repetitive inspections required by paragraph (m) of 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 Bulletin
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service
Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for
Model A300-600 series airplanes).
(3) If damage or corrosion is detected during any inspection
specified in paragraph (q)(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 Mandatory Service Bulletin A300-57-6106,
Revision 03, dated January 26, 2012 (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 EASA (or its delegated agent, or the Design Approval Holder
with EASA's design organization approval, as applicable).
(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 Mandatory Service Bulletin A300-57-6106,
Revision 03, dated January 26, 2012 (for Model A300-600 series
airplanes).
(r) Retained Terminating Action for AD 2007-03-18, Amendment 39-14929
(72 FR 5919, February 8, 2007)
This paragraph restates the terminating action statement of
paragraph (k) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012), and applies to the airplanes identified in
paragraph (n) of this AD. Doing the actions required by paragraph
(q) of this AD terminates the inspections required by AD 2007-03-18,
Amendment 39-14929 (72 FR 5919, February 8, 2007), for that
airplane.
(s) Retained Reporting
This paragraph restates the requirements of paragraph (l) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD.
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 (m) 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 (s)(1) or (s)(2) of this AD.
(1) If the inspection was done on or after September 11, 2012
(the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR
46937, August 7, 2012)): Submit the report within 30 days after the
inspection.
(2) If the inspection was done before September 11, 2012 (the
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012)): Submit the report within 30 days after September
11, 2012.
(t) New Repetitive Inspections
For airplanes identified in paragraph (u) of this AD: At the
applicable time specified in paragraph (v)(1) or (v)(2) of this AD,
do a detailed inspection for cracking, or an ultrasonic inspection
for any crack indications of the LH and RH MLG rib 5 aft bearing
forward lugs, in accordance with the Accomplishment Instructions of
the applicable service bulletin specified in paragraph (t)(1),
(t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at
intervals not to exceed the applicable time specified in paragraph
(v)(3) or (v)(4) of this AD.
(1) Airbus Mandatory Service Bulletin A300-57-0255, dated
January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203
airplanes).
(2) Airbus Mandatory Service Bulletin A300-57-6112, dated
January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, and F4-622R airplanes).
(3) Airbus Mandatory Service Bulletin A310-57-2101, dated
January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322,
-324, and -325 airplanes).
(u) Affected Airplanes for the Actions Required by Paragraph (t) of
This AD
For airplanes on which any modification or repair described in
the service bulletins identified in paragraph (u)(1), (u)(2), or
(u)(3) of this AD, as applicable, has been accomplished in service;
and for airplanes with MLG rib 5 already repaired as specified in
Airbus Repair Instruction R57240221 or R57249121, including any
airplane with the MLG rib 5 forward lugs repaired on one wing; by
installation of oversized interference fit bushes, as specified in
Airbus
[[Page 13943]]
Repair Instruction R57240221 or R57249121, as applicable: Do the
actions required by paragraph (t) of this AD.
(1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007;
Revision 01, dated December 19, 2007; or Airbus Service Bulletin
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
2C, B4-103, and B4-203 airplanes).
(2) Airbus Service Bulletin A300-57-6106, dated May 22, 2007;
Revision 01, dated January 28, 2008; or Airbus 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 Variant F airplanes).
(3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007;
Revision 01, dated December 19, 2007; or Airbus Service Bulletin
A310-57-2090 Revision 02, dated June 18, 2010 (for Model A310 series
airplanes).
(v) Compliance Times for Paragraph (t) of This AD
This paragraph specifies the compliance times for the actions
specified in paragraph (t) of this AD.
(1) For airplanes identified in paragraph (c)(1) of this AD: Do
the initial inspection required by paragraph (t) of this AD within
2,500 flight cycles after any modification or repair specified in
paragraph (u) of this AD was done, or within 550 flight cycles after
the effective date of this AD, whichever occurs later.
(2) For airplanes identified in paragraph (c)(2) of this AD: Do
the initial inspection required by paragraph (t) of this AD within
2,500 flight cycles after any modification or repair specified in
paragraph (u) of this AD was done, or within 775 flight cycles after
the effective date of this AD, whichever occurs later.
(3) For airplanes identified in paragraph (c)(1) of this AD: For
the repetitive inspection required by paragraph (t) of this AD,
repeat the inspection within 550 flight cycles after any detailed
inspection, and within 1,000 flight cycles after any ultrasonic
inspection, as applicable.
(4) For airplanes identified in paragraph (c)(2) of this AD: For
the repetitive inspection required by paragraph (t) of this AD,
repeat the inspection within 775 flight cycles after any detailed
inspection, and within 1,300 flight cycles after any ultrasonic
inspection, as applicable.
(w) New Requirement of This AD: Report and Detailed Inspection
If, during any ultrasonic inspection required by paragraph (t)
of this AD, any crack indication is detected: Before further flight,
report to Airbus using the applicable report sheet attached to the
applicable Airbus service bulletin specified in paragraph (t)(1),
(t)(2), or (t)(3) of this AD, and concurrently accomplish a detailed
inspection for cracking of the affected MLG rib 5 aft bearing
forward lug, in accordance with the Accomplishment Instructions of
the applicable Airbus service bulletin specified in paragraph
(t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed inspection
thereafter at intervals not to exceed 100 flight cycles.
(x) New Requirement of This AD: Cracking Repair
If any cracking is detected during any detailed inspection
required by paragraph (t) or (w) of this AD: Before further flight,
repair the cracking using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA (or its delegated agent, or the Design Approval Holder
with the EASA design organization approval, as applicable). For a
repair method to be approved, the repair approval must specifically
refer to this AD.
(y) New Requirement of This AD: Reporting
Submit a report (including both positive and negative findings),
using the reporting sheet attached to the applicable Airbus service
bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this
AD, of the first inspection required by paragraph (t) 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. Submit the report within 30 days
after the inspection or within 30 days after the effective date of
this AD, whichever occurs later.
(1) Airbus Mandatory Service Bulletin A300-57-0255, dated
January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203
airplanes).
(2) Airbus Mandatory Service Bulletin A300-57-6112, dated
January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, and F4-622R airplanes).
(3) Airbus Mandatory Service Bulletin A310-57-2101, dated
January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322,
-324, and -325 airplanes).
(z) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before May
29, 2012 (the effective date of AD 2012-08-03, Amendment 39-17019
(77 FR 24367, April 24, 2012)), using an applicable service bulletin
specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this
AD.
(i) For Model A300 B4-2C, B4-103, and B4-203 airplanes: The
service bulletins are specified in paragraphs (z)(1)(i)(A),
(z)(1)(i)(B), and (z)(1)(i)(C) of this AD.
(A) Airbus Service Bulletin A300-57-0249, dated May 22, 2007,
which is not incorporated by reference in this AD.
(B) Airbus Service Bulletin A300-57-0249, Revision 01, dated
December 19, 2007, which is not incorporated by reference in this
AD.
(C) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010.
(ii) For Model A300-600 series airplanes: The service bulletins
are specified in paragraphs (z)(1)(ii)(A), (z)(1)(ii)(B), and
(z)(1)(ii)(C) of this AD.
(A) Airbus Service Bulletin A300-57-6106, May 22, 2007, which is
not incorporated by reference in this AD.
(B) Airbus Service Bulletin A300-57-6106, Revision 01, January
28, 2008, which is not incorporated by reference in this AD.
(C) Airbus Service Bulletin A300-57-6106, Revision 02, dated
June 18, 2010, which is not incorporated by reference in this AD.
(iii) For Model A310 series airplanes: The service bulletins are
specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and
(z)(1)(iii)(C) of this AD.
(A) Airbus Service Bulletin A310-57-2090, dated May 22, 2007,
which is not incorporated by reference in this AD.
(B) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007.
(C) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010, which is not incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraph (q) of this AD, if those actions were performed before
September 11, 2012 (the effective date of AD 2012-15-14, Amendment
39-17143 (77 FR 46937, August 7, 2012)), using an applicable service
bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii),
(z)(2)(iv), and (z)(2)(v) of this AD.
(i) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service
Bulletin A300-57-0249, dated May 22, 2007, which is not incorporated
by reference in this AD.
(ii) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service
Bulletin A300-57-0249, Revision 01, dated December 19, 2007, which
is not incorporated by reference in this AD.
(iii) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622,
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, dated May 22, 2007, which is not
incorporated by reference in this AD.
(iv) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, Revision 01, dated January 28, 2008,
which is not incorporated by reference in this AD.
(v) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, Revision 02, dated June 18, 2010
which is not incorporated by reference in this AD.
(aa) 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; phone (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
[[Page 13944]]
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(i) AMOCs approved previously for AD 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the
corresponding provisions of paragraphs (g) and (h) of this AD.
(ii) AMOCs approved previously for AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the
corresponding provisions of paragraphs (i), (j), and (k) of this AD.
(iii) AMOCs approved previously for AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the
corresponding provisions of paragraphs (l), (m), (n), and (o) of
this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the Design Approval Holder with a State of
Design Authority's design organization approval, as applicable). You
are required to ensure 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.
(bb) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0176, dated September 7, 2012, corrected September 20, 2012, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2014-0142.
(2) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 4, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-05435 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P
