Airworthiness Directives; Airbus Airplanes, 7290-7298 [2015-01710]
Download as PDF
<![CDATA[
7290
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Before further flight and thereafter at
intervals not to exceed 10 hours time-inservice, using a light and a mirror, visually
inspect the hopper for a crack at the four fan
attachment points. The hopper is depicted as
item ‘‘a’’ and the fan as item ‘‘b’’ in Figure
1 of Airbus Helicopters Emergency Alert
Service Bulletin No. 05A020, Revision 0,
dated October 20, 2014 (EASB). If there is a
crack in the hopper, replace the hopper with
an airworthy hopper. Examples of a crack are
shown in Figure 2 of the EASB. Replacing the
hopper does not constitute terminating action
for the repetitive visual inspections required
by this AD.
(f) Special Flight Permits
Special flight permits may be issued
provided that the fan is removed.
BILLING CODE 4910–13–P
(h) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
Emergency AD No. 2014–0229–E, dated
October 20, 2014. You may view the EASA
AD on the Internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2015–0133.
rljohnson on DSK3VPTVN1PROD with RULES
(i) Subject
Joint Aircraft Service Component (JASC)
Tracking Code: 6322 Main Rotor Drive
Rotorcraft Cooling Fan System.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Emergency Alert
Service Bulletin No. 05A020, Revision 0,
dated October 20, 2014.
(ii) Reserved.
(3) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum
15:13 Feb 09, 2015
Jkt 235001
Issued in Fort Worth, Texas, on January 16,
2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–01803 Filed 2–9–15; 8:45 am]
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
EAD. Send your proposal to: Eric Haight,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
eric.haight@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
EAD through an AMOC.
VerDate Sep<11>2014
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://
www.airbushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0142; Directorate
Identifier 2012–NM–161–AD; Amendment
39–18093; AD 2015–02–24]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–03–
18, 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 A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. AD 2007–03–18,
AD 2008–17–02, AD 2012–08–03, and
AD 2012–15–14 required 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.
This new AD adds airplanes to the
applicability; and adds, for certain
airplanes, repetitive inspections of the
MLG rib 5 aft bearing forward lugs, and
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
repair if necessary. This AD was
prompted by reports of cracking in the
forward lug of the MLG rib 5 aft bearing
attachment. We are issuing this AD to
detect and correct cracking of the
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: This AD becomes effective
March 17, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 17, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of September 11, 2012 (77 FR
46937, August 7, 2012).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 29, 2012 (77 FR
24367, April 24, 2012).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of September 17, 2008 (73 FR
47032, August 13, 2008).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of February 6, 2007 (72 FR
2612, January 22, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0142; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0142.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
E:\FR\FM\10FER1.SGM
10FER1
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
rljohnson on DSK3VPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede 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). AD 2008–17–02, AD
2012–08–03, and AD 2012–15–14,
applied to 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 A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes); and Model A310 series
airplanes. The NPRM published in the
Federal Register on March 12, 2014 (79
FR 13938).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, 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,
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).
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
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/
#!documentDetail;D=FAA-2014-01420002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 13938,
March 12, 2014) and the FAA’s response
to each comment.
Request To Withdraw the NPRM (79 FR
13938, March 12, 2014)
United Parcel Service (UPS) requested
that we withdraw the NPRM (79 FR
13938, March 12, 2014) and focus on
airplanes that have been serviced at the
facilities where the two airplanes
specified in the Discussion section of
the NPRM had been reworked. UPS
stated that both events are the result of
an operator not following procedures.
We disagree with the commenter’s
request to withdraw the NPRM (79 FR
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
7291
13938, March 12, 2014). This issue
concerns more than one operator and
airplane model. We have no data
indicating that these events are
definitively limited to just one repair
station or operator. Therefore, the
unsafe condition may exist on other
airplanes of a similar type design.
Consequently, the actions required by
this final rule must be done for
airplanes identified in paragraph (c) of
this AD. We have not changed this AD
in this regard.
Request To Revise Post-Modification
Repetitive Inspection
UPS requested that we revise the postmodification repetitive inspections to a
one-time inspection. UPS stated that it
does not believe that the root cause of
the reported events is addressed in the
NPRM (79 FR 13938, March 12, 2014).
UPS explained that the primary focus of
Airbus Mandatory Service Bulletin
A300–57–6106, Revision 03, dated
January 26, 2012, and the incident
investigation is on sealing and
protection in the bushing head area.
UPS stated that the only difference
between the sealing process of Airbus
Mandatory Service Bulletin A300–57–
6106, Revision 03, dated January 26,
2012, and prior service bulletin revision
levels, is the application of a single coat
of polyurethane paint applied over the
fillet seal around the bushing flange.
UPS explained that, based on a process
review of Airbus Service Bulletin A300–
57–6106 and the failure analysis results
from the two post-modification reported
events, it concurs that a postmodification check of the modification
integrity is valid; however, the postmodification repetitive inspection
should be a one-time inspection to
verify proper accomplishment of the
rework process.
We disagree with the commenter’s
request to revise the post-modification
repetitive inspections to a one-time
inspection. The corresponding MCAI
specifies that the inspection be
repeated; FAA ADs match the MCAI
requirements if the MCAI provides an
adequate level of safety and does not
conflict with FAA policies. The sealing
process could be compromised over
time. Thus a repetitive inspection is
considered necessary to ensure that
corrosion will not occur and to ensure
the structural integrity of the MLG rib 5.
However, under the provisions of
paragraph (aa) of this AD, we might
approve requests for adjustments to the
compliance time if data are submitted to
substantiate that such an adjustment
would provide an acceptable level of
safety. We have not changed this AD in
this regard.
E:\FR\FM\10FER1.SGM
10FER1
7292
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
Request To Supersede AD 2007–03–18,
Amendment 39–14929 (72 FR 5919,
February 8, 2007)
UPS requested that we revise the
wording in paragraph (o) of the NPRM
(79 FR 13938, March 12, 2014) to
terminate the inspections required by
AD 2007–03–18, Amendment 39–14929
(72 FR 5919, February 8, 2007); and to
add AD 2007–03–18 to the list of
superseded ADs in paragraph (b)(1) of
the NPRM. UPS stated that it believes
the intent of paragraph (g) of AD 2012–
15–14, Amendment 39–17143 (77 FR
46937, August 7, 2012), was to
terminate the AD 2007–03–18
inspection requirements upon initiation
of inspections as described in Airbus
Mandatory Service Bulletin A300–57–
6107, including Appendix 01, dated
August 8, 2007.
We agree with the commenter’s
request to add AD 2007–03–18,
Amendment 39–14929 (72 FR 5919,
February 8, 2007), to the list of
superseded ADs in this final rule. We
have revised paragraph (b) of this AD by
removing paragraph (b)(2) of the NPRM
(79 FR 13938, March 12, 2014); redesignating paragraph (b)(1) of the
NPRM as paragraph (b) of this AD;
adding new paragraph (b)(1) to this AD,
which adds AD 2007–03–18 to the list
of superseded ADs in this AD; and redesignating paragraphs (b)(1)(i) through
(b)(1)(iii) of the NPRM as paragraphs
(b)(2) through (b)(4) of this AD,
respectively.
rljohnson on DSK3VPTVN1PROD with RULES
Request To Remove Repair Approval
Requirement
UPS requested that we remove the
statement ‘‘For a repair method to be
approved, the repair approval must
specifically refer to this AD’’ in
paragraph (x) of the NPRM (79 FR
13938, March 12, 2014). UPS
acknowledged that the rules governing
the AD repair and deviation approval
process for foreign-manufactured
aircraft differ from domestic-built
airplanes. UPS recommended that the
FAA meet with U.S. operators of
foreign-built airplanes to discuss
concerns about repair instructions being
used that might not fully address the
unsafe condition and to review options
to alleviate those concerns.
We concur with the commenter’s
request to remove from this final rule
the requirement that repair approvals
must specifically refer to this AD. Our
responses to specific aspects of this
request are presented as follows.
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
authority’s AD. The MCAI or referenced
service information in an FAA AD often
directs the owner/operator to contact
the manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 13938, March 12,
2014), we proposed to prevent the use
of repairs that were not specifically
developed to correct the unsafe
condition, by requiring that the repair
approval provided by the State of
Design Authority or its delegated agent
specifically refer to this FAA AD. This
change was 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 proposed to
change the phrase ‘‘its delegated agent’’
to include ‘‘the Design Approval Holder
(DAH) with State of Design Authority’s
design organization approval’’ to refer to
a DAH authorized to approve required
repairs for the proposed AD.
UPS also commented on an NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013). UPS stated the following: ‘‘The
proposed wording, being specific to
repairs, eliminates the interpretation
that Airbus messages are acceptable for
approving minor deviations (corrective
actions) needed during accomplishment
of an AD mandated Airbus service
bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed
that paragraph and retitled it
‘‘Contacting the Manufacturer.’’ This
paragraph now clarifies that for any
requirement in this AD to obtain
corrective actions from a manufacturer,
the actions must be accomplished using
a method approved by the FAA, EASA,
or Airbus’s EASA Design Organization
Approval (DOA).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility afforded previously by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
Other commenters to the NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013) pointed out that, in many cases,
the foreign manufacturer’s service
bulletin and the foreign authority’s
MCAI may have been issued some time
before the FAA AD. Therefore, the DOA
may have provided U.S. operators with
an approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
approval document, adding time and
expense to the compliance process with
no safety benefit.
Based on these comments, we
removed the requirement that the DAHprovided repair specifically refer to this
E:\FR\FM\10FER1.SGM
10FER1
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
AD. Before adopting such a
requirement, the FAA will coordinate
with affected DAHs and verify they are
prepared to implement means to ensure
that their repair approvals consider the
unsafe condition addressed in the AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate.
We have also decided not to include
a generic reference to either the
‘‘delegated agent’’ or the ‘‘DAH with
State of Design Authority design
organization approval,’’ but instead we
will provide the specific delegation
approval granted by the State of Design
Authority for the DAH.
Change to Paragraph (h)(3) of This AD
We removed a requirement to use the
latest revision of certain service
information, which appeared as the last
sentence at the end of paragraph (h)(3)
of the NPRM (79 FR 13938, March 12,
2014). That requirement already appears
in paragraph (h)(2) of this AD.
rljohnson on DSK3VPTVN1PROD with RULES
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
13938, March 12, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 13938,
March 12, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
bulletins.
Airbus Service Bulletin A300–57–
0255, including Inspection Reporting
Form, dated January 13, 2012. The
service information describes
procedures for inspections of the
forward lugs of the aft bearing at rib 5
of the MLG on the LH and RH wings.
Airbus Service Bulletin A300–57–
6112, including Inspection Reporting
Form, dated January 13, 2012. The
service information describes
procedures for inspections of the
forward lugs of the aft bearing at rib 5
of the MLG on the LH and RH wings.
Airbus Service Bulletin A310–57–
2090, Revision 02, dated June 18, 2010.
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
The service information describes
procedures for 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.
Airbus Service Bulletin A310–57–
2101, including Inspection Reporting
Form, dated January 13, 2012. The
service information describes
procedures for inspections of the
forward lugs of the aft bearing at rib 5
of the MLG on the LH and RH wings.
This service information is reasonably
available; see ADDRESSES for ways to
access this service information.
Costs of Compliance
We estimate that this 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 AD take about 5 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 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 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 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 AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $49,470, or $255 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this 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 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.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
7293
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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
E:\FR\FM\10FER1.SGM
10FER1
7294
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=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
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.
(4) AD 2012–15–14, Amendment 39–17143
(77 FR 46937, August 7, 2012).
(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.
Adoption of the Amendment
(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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2007–03–18, Amendment 39–14929 (72
FR 5919, February 8, 2007); 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 adding the
following new AD:
■
2015–02–24 Airbus: Amendment 39–18093.
Docket No. FAA–2014–0142; Directorate
Identifier 2012–NM–161–AD.
rljohnson on DSK3VPTVN1PROD with RULES
(a) Effective Date
This AD becomes effective March 17, 2015.
(b) Affected ADs
This AD replaces the ADs specified in
paragraphs (b)(1) through (b)(4) of this AD.
(1) AD 2007–03–18, Amendment 39–14929
(72 FR 5919, February 8, 2007).
(2) AD 2008–17–02, Amendment 39–15640
(73 FR 47032, August 13, 2008).
(3) AD 2012–08–03, Amendment 39–17019
(77 FR 24367, April 24, 2012).
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
(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
AD, and specific delegation approval
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
language in paragraphs (h)(3) and (h)(4)(ii) of
this 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) of this AD for
that MLG rib 5 only.
(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 Mandatory
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 Mandatory Service Bulletin
A310–57–2090, Revision 02, dated June 18,
2010.
(iii) Airbus Mandatory 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. As of the
effective date of this AD: Before further flight,
replace using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). 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
E:\FR\FM\10FER1.SGM
10FER1
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
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.
(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
paragraphs (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. As of the effective date of this
AD: Before further flight, replace using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA; or
Airbus’s EASA DOA. 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.
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.
rljohnson on DSK3VPTVN1PROD with RULES
(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).
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
(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
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 Service Bulletin A310–57–2090
embodied in service.
(k) Retained Exception for Airplanes
Identified in Paragraphs (j)(1), (j)(2), and
(j)(3) of This AD
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 R572–49121, 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,
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
7295
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,
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 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 Service Bulletin A300–57–
6106 has been done in service on the LH and
RH wings.
(o) Retained Exception for Certain Airplanes
Identified in Paragraph (n) of This AD
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): 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.
E:\FR\FM\10FER1.SGM
10FER1
7296
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
(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),
with specific delegation approval language. 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
EASA; or Airbus’s EASA DOA.
rljohnson on DSK3VPTVN1PROD with RULES
(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
EASA; or Airbus’s EASA DOA.
(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).
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
(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, dated 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 Service Bulletin A300–57–0255,
including Inspection Reporting Form, dated
January 13, 2012 (for Model A300 B2–1A,
B2–1C, B2K–3C, and B2–203 airplanes).
(2) Airbus Service Bulletin A300–57–6112,
including Inspection Reporting Form, 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 Service Bulletin A310–57–2101,
including Inspection Reporting Form, dated
January 13, 2012 (for Model A310–203, -204,
-221, -222, -304, -322, -324, and -325
airplanes).
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
(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
R572–49121, 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
Repair Instruction R57240221 or R572–
49121, 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 Mandatory
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 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 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
E:\FR\FM\10FER1.SGM
10FER1
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
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 Airbus’s EASA DOA.
rljohnson on DSK3VPTVN1PROD with RULES
(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 Service Bulletin A300–57–0255,
including Inspection Reporting Form, dated
January 13, 2012 (for Model A300 B2–1A,
B2–1C, B2K–3C, and B2–203 airplanes).
(2) Airbus Service Bulletin A300–57–6112,
including Inspection Reporting Form, 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 Service Bulletin A310–57–2101,
including Inspection Reporting Form, 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, incorporated by reference in AD 2012–
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
15–14, Amendment 39–17143 (77 FR 46937,
August 7, 2012).
(ii) For 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: 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,
dated May 22, 2007, which is not
incorporated by reference in this AD.
(B) Airbus Service Bulletin A300–57–6106,
Revision 01, dated 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,
incorporated by reference in AD 2008–17–02,
Amendment 39–15640 (73 FR 47032, August
13, 2008).
(C) Airbus Service Bulletin A310–57–2090,
Revision 02, dated June 18, 2010, which is
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
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
7297
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.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) 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.
(iii) 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), (k), and (l) of this AD.
(iv) 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 (m) through (s) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(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) EASA
Airworthiness Directive 2012–0176, dated
September 7, 2012, corrected September 20,
2012, for related information. You may
E:\FR\FM\10FER1.SGM
10FER1
7298
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations
rljohnson on DSK3VPTVN1PROD with RULES
examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0142-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (cc)(9) and (cc)(10) of this AD.
(cc) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on March 17, 2015.
(i) Airbus Service Bulletin A300–57–0255,
including Inspection Reporting Form, dated
January 13, 2012.
(ii) Airbus Service Bulletin A300–57–6112,
including Inspection Reporting Form, dated
January 13, 2012.
(iii) Airbus Service Bulletin A310–57–
2090, Revision 02, dated June 18, 2010.
(iv) Airbus Service Bulletin A310–57–
2101, including Inspection Reporting Form,
dated January 13, 2012.
(4) The following service information was
approved for IBR on September 11, 2012 (77
FR 46937, August 7, 2012).
(i) Airbus Mandatory Service Bulletin
A300–57–0249, Revision 02, dated June 18,
2010.
(ii) Airbus Mandatory Service Bulletin
A300–57–0251, including Appendix 01,
dated August 8, 2007.
(iii) Airbus Mandatory Service Bulletin
A300–57–6106, Revision 03, dated January
26, 2012.
(iv) Airbus Mandatory Service Bulletin
A300–57–6107, including Appendix 01,
August 8, 2007.
(5) The following service information was
approved for IBR on May 29, 2012 (77 FR
24367, April 24, 2012).
(i) Airbus Mandatory Service Bulletin
A300–57–0249, Revision 03, dated January
18, 2012.
(ii) Airbus Mandatory Service Bulletin
A310–57–2090, Revision 03, dated January
23, 2012.
(6) The following service information was
approved for IBR on September 17, 2008 (73
FR 47032, August 13, 2008).
(i) Airbus Service Bulletin A310–57–2090,
Revision 01, dated December 19, 2007.
(ii) Airbus Service Bulletin A310–57–2091,
excluding Appendix 01, dated May 22, 2007.
(iii) Airbus A310 Repair Instruction R572–
49121, Issue C, dated May 2007.
(7) The following service information was
approved for IBR on February 6, 2007 (72 FR
2612, January 22, 2007).
(i) Airbus Service Bulletin A310–57A2088,
excluding Appendix 01, dated November 6,
2006.
(ii) Reserved.
(8) For service information identified in
this 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-
VerDate Sep<11>2014
15:13 Feb 09, 2015
Jkt 235001
eas@airbus.com; Internet https://
www.airbus.com.
(9) 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.
(10) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on January
21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–01710 Filed 2–9–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0750; Directorate
Identifier 2014–NM–147–AD; Amendment
39–18097; AD 2015–03–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Bombardier, Inc. Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. This AD was prompted by
reports of dislodged engine fan cowl
panels. This AD requires installing
additional attaching hardware on the
left and right fan cowl access panels and
the nacelle attaching structures. We are
issuing this AD to prevent damage to the
fuselage and flight control surfaces from
dislodged engine fan cowl panels.
DATES: This AD becomes effective
March 17, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 17, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0750; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
SUMMARY:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this AD, contact Bombardier, Inc., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec
H4S 1Y9, Canada; telephone 514–855–
5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; Internet
https://www.bombardier.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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0750.
FOR FURTHER INFORMATION CONTACT:
Andreas Rambalakos, Aerospace
Engineer, Airframe and Mechanical
Systems Branch, ANE–171, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7345; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Bombardier, Inc. Model CL–
600–2B19 (Regional Jet Series 100 &
440) airplanes. The NPRM published in
the Federal Register on October 2, 2014
(79 FR 59459).
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2014–20, dated July 9, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition.
The MCAI states:
There have been a number of engine fan
cowl panel dislodgement incidents reported
on the Bombardier CL–600–2B19 aeroplane
fleet. The dislodged panels may cause
damage to the fuselage and flight control
surfaces of the aeroplane. Also, the debris
from a dislodged panel may result in runway
contamination and has the potential of
causing injury on the ground.
Although the majority of the subject panel
dislodgements were reported on the first or
second flight after an engine maintenance
task was performed that required removal
and reinstallation of the subject panels, the
frequency of the dislodgements indicates that
the existing attachment design is prone to
human (maintenance) error.
Bombardier has attempted to mitigate this
issue by issuing maintenance advisories
emphasizing the proper installation of engine
fan cowl panels. In order to further mitigate
the potential safety hazard of the subject
panel dislodgement, Bombardier has issued
E:\FR\FM\10FER1.SGM
10FER1
]]>Agencies
[Federal Register Volume 80, Number 27 (Tuesday, February 10, 2015)]
[Rules and Regulations]
[Pages 7290-7298]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01710]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0142; Directorate Identifier 2012-NM-161-AD;
Amendment 39-18093; AD 2015-02-24]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2007-03-18, 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 A300 C4-605R Variant F
airplanes (collectively called Model A300-600 series airplanes); and
Model A310 series airplanes. AD 2007-03-18, AD 2008-17-02, AD 2012-08-
03, and AD 2012-15-14 required 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. This new AD adds airplanes to the applicability; and adds, for
certain airplanes, repetitive inspections of the MLG rib 5 aft bearing
forward lugs, and repair if necessary. This AD was prompted by reports
of cracking in the forward lug of the MLG rib 5 aft bearing attachment.
We are issuing this AD to detect and correct cracking of the 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: This AD becomes effective March 17, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 17,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 11, 2012 (77 FR 46937, August 7, 2012).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 29,
2012 (77 FR 24367, April 24, 2012).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 17, 2008 (73 FR 47032, August 13, 2008).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
February 6, 2007 (72 FR 2612, January 22, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0142; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this 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. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2014-0142.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116,
[[Page 7291]]
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA
98057-3356; telephone 425-227-2125; fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede 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). AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14, applied to
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 A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series
airplanes); and Model A310 series airplanes. The NPRM published in the
Federal Register on March 12, 2014 (79 FR 13938).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, 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, 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/#!documentDetail;D=FAA-2014-0142-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 13938, March 12, 2014) and the FAA's response to each comment.
Request To Withdraw the NPRM (79 FR 13938, March 12, 2014)
United Parcel Service (UPS) requested that we withdraw the NPRM (79
FR 13938, March 12, 2014) and focus on airplanes that have been
serviced at the facilities where the two airplanes specified in the
Discussion section of the NPRM had been reworked. UPS stated that both
events are the result of an operator not following procedures.
We disagree with the commenter's request to withdraw the NPRM (79
FR 13938, March 12, 2014). This issue concerns more than one operator
and airplane model. We have no data indicating that these events are
definitively limited to just one repair station or operator. Therefore,
the unsafe condition may exist on other airplanes of a similar type
design. Consequently, the actions required by this final rule must be
done for airplanes identified in paragraph (c) of this AD. We have not
changed this AD in this regard.
Request To Revise Post-Modification Repetitive Inspection
UPS requested that we revise the post-modification repetitive
inspections to a one-time inspection. UPS stated that it does not
believe that the root cause of the reported events is addressed in the
NPRM (79 FR 13938, March 12, 2014). UPS explained that the primary
focus of Airbus Mandatory Service Bulletin A300-57-6106, Revision 03,
dated January 26, 2012, and the incident investigation is on sealing
and protection in the bushing head area. UPS stated that the only
difference between the sealing process of Airbus Mandatory Service
Bulletin A300-57-6106, Revision 03, dated January 26, 2012, and prior
service bulletin revision levels, is the application of a single coat
of polyurethane paint applied over the fillet seal around the bushing
flange. UPS explained that, based on a process review of Airbus Service
Bulletin A300-57-6106 and the failure analysis results from the two
post-modification reported events, it concurs that a post-modification
check of the modification integrity is valid; however, the post-
modification repetitive inspection should be a one-time inspection to
verify proper accomplishment of the rework process.
We disagree with the commenter's request to revise the post-
modification repetitive inspections to a one-time inspection. The
corresponding MCAI specifies that the inspection be repeated; FAA ADs
match the MCAI requirements if the MCAI provides an adequate level of
safety and does not conflict with FAA policies. The sealing process
could be compromised over time. Thus a repetitive inspection is
considered necessary to ensure that corrosion will not occur and to
ensure the structural integrity of the MLG rib 5. However, under the
provisions of paragraph (aa) of this AD, we might approve requests for
adjustments to the compliance time if data are submitted to
substantiate that such an adjustment would provide an acceptable level
of safety. We have not changed this AD in this regard.
[[Page 7292]]
Request To Supersede AD 2007-03-18, Amendment 39-14929 (72 FR 5919,
February 8, 2007)
UPS requested that we revise the wording in paragraph (o) of the
NPRM (79 FR 13938, March 12, 2014) to terminate the inspections
required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8,
2007); and to add AD 2007-03-18 to the list of superseded ADs in
paragraph (b)(1) of the NPRM. UPS stated that it believes the intent of
paragraph (g) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August
7, 2012), was to terminate the AD 2007-03-18 inspection requirements
upon initiation of inspections as described in Airbus Mandatory Service
Bulletin A300-57-6107, including Appendix 01, dated August 8, 2007.
We agree with the commenter's request to add AD 2007-03-18,
Amendment 39-14929 (72 FR 5919, February 8, 2007), to the list of
superseded ADs in this final rule. We have revised paragraph (b) of
this AD by removing paragraph (b)(2) of the NPRM (79 FR 13938, March
12, 2014); re-designating paragraph (b)(1) of the NPRM as paragraph (b)
of this AD; adding new paragraph (b)(1) to this AD, which adds AD 2007-
03-18 to the list of superseded ADs in this AD; and re-designating
paragraphs (b)(1)(i) through (b)(1)(iii) of the NPRM as paragraphs
(b)(2) through (b)(4) of this AD, respectively.
Request To Remove Repair Approval Requirement
UPS requested that we remove the statement ``For a repair method to
be approved, the repair approval must specifically refer to this AD''
in paragraph (x) of the NPRM (79 FR 13938, March 12, 2014). UPS
acknowledged that the rules governing the AD repair and deviation
approval process for foreign-manufactured aircraft differ from
domestic-built airplanes. UPS recommended that the FAA meet with U.S.
operators of foreign-built airplanes to discuss concerns about repair
instructions being used that might not fully address the unsafe
condition and to review options to alleviate those concerns.
We concur with the commenter's request to remove from this final
rule the requirement that repair approvals must specifically refer to
this AD. Our responses to specific aspects of this request are
presented as follows.
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD. The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact
the manufacturer for corrective actions, such as a repair. Briefly, the
Airworthy Product paragraph allowed owners/operators to use corrective
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved
by the State of Design Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 13938, March 12, 2014), we proposed to prevent
the use of repairs that were not specifically developed to correct the
unsafe condition, by requiring that the repair approval provided by the
State of Design Authority or its delegated agent specifically refer to
this FAA AD. This change was 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 proposed to change the phrase ``its
delegated agent'' to include ``the Design Approval Holder (DAH) with
State of Design Authority's design organization approval'' to refer to
a DAH authorized to approve required repairs for the proposed AD.
UPS also commented on an NPRM having Directorate Identifier 2012-
NM-101-AD (78 FR 78285, December 26, 2013). UPS stated the following:
``The proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed that paragraph and
retitled it ``Contacting the Manufacturer.'' This paragraph now
clarifies that for any requirement in this AD to obtain corrective
actions from a manufacturer, the actions must be accomplished using a
method approved by the FAA, EASA, or Airbus's EASA Design Organization
Approval (DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility afforded previously
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that, in many
cases, the foreign manufacturer's service bulletin and the foreign
authority's MCAI may have been issued some time before the FAA AD.
Therefore, the DOA may have provided U.S. operators with an approved
repair, developed with full awareness of the unsafe condition, before
the FAA AD is issued. Under these circumstances, to comply with the FAA
AD, the operator would be required to go back to the manufacturer's DOA
and obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this
[[Page 7293]]
AD. Before adopting such a requirement, the FAA will coordinate with
affected DAHs and verify they are prepared to implement means to ensure
that their repair approvals consider the unsafe condition addressed in
the AD. Any such requirements will be adopted through the normal AD
rulemaking process, including notice-and-comment procedures, when
appropriate.
We have also decided not to include a generic reference to either
the ``delegated agent'' or the ``DAH with State of Design Authority
design organization approval,'' but instead we will provide the
specific delegation approval granted by the State of Design Authority
for the DAH.
Change to Paragraph (h)(3) of This AD
We removed a requirement to use the latest revision of certain
service information, which appeared as the last sentence at the end of
paragraph (h)(3) of the NPRM (79 FR 13938, March 12, 2014). That
requirement already appears in paragraph (h)(2) of this AD.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 13938, March 12, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 13938, March 12, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following service bulletins.
Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
Airbus Service Bulletin A310-57-2090, Revision 02, dated June 18,
2010. The service information describes procedures for 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.
Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
This service information is reasonably available; see ADDRESSES for
ways to access this service information.
Costs of Compliance
We estimate that this 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 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 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 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 AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $49,470, or $255 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this 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 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
[[Page 7294]]
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007); 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 adding the
following new AD:
2015-02-24 Airbus: Amendment 39-18093. Docket No. FAA-2014-0142;
Directorate Identifier 2012-NM-161-AD.
(a) Effective Date
This AD becomes effective March 17, 2015.
(b) Affected ADs
This AD replaces the ADs specified in paragraphs (b)(1) through
(b)(4) of this AD.
(1) AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8,
2007).
(2) AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13,
2008).
(3) AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24,
2012).
(4) AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7,
2012).
(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 AD, and specific delegation approval language in
paragraphs (h)(3) and (h)(4)(ii) of this 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) of this AD for that MLG rib 5 only.
(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 Mandatory 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 Mandatory Service Bulletin A310-57-2090, Revision
02, dated June 18, 2010.
(iii) Airbus Mandatory 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. As of the effective date of this AD: Before further
flight, replace using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA); or Airbus's EASA
Design Organization Approval (DOA). 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
[[Page 7295]]
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.
(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
paragraphs (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. As of the effective date of this AD: Before
further flight, replace using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA; or Airbus's EASA DOA. 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.
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.
(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 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 Service Bulletin A310-57-2090 embodied in
service.
(k) Retained Exception for Airplanes Identified in Paragraphs (j)(1),
(j)(2), and (j)(3) of This AD
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 R572-49121, 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, 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 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 Service
Bulletin A300-57-6106 has been done in service on the LH and RH
wings.
(o) Retained Exception for Certain Airplanes Identified in Paragraph
(n) of This AD
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): 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.
[[Page 7296]]
(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), with
specific delegation approval language. 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 EASA; or Airbus's EASA DOA.
(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 EASA; or Airbus's EASA DOA.
(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, dated 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 Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C,
B2K-3C, and B2-203 airplanes).
(2) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, 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 Service Bulletin A310-57-2101, including Inspection
Reporting Form, 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 R572-49121, 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 Repair Instruction R57240221 or R572-49121, 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 Mandatory 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 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 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
[[Page 7297]]
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 Airbus's EASA DOA.
(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 Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C,
B2K-3C, and B2-203 airplanes).
(2) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, 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 Service Bulletin A310-57-2101, including Inspection
Reporting Form, 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, incorporated by reference in AD 2012-15-14,
Amendment 39-17143 (77 FR 46937, August 7, 2012).
(ii) For 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: 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, dated May 22, 2007,
which is not incorporated by reference in this AD.
(B) Airbus Service Bulletin A300-57-6106, Revision 01, dated
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, incorporated by reference in AD 2008-17-02,
Amendment 39-15640 (73 FR 47032, August 13, 2008).
(C) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010, which is 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.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) 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.
(iii) 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), (k), and (l) of
this AD.
(iv) 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 (m) through (s) of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(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) EASA Airworthiness Directive 2012-0176, dated September 7,
2012, corrected September 20, 2012, for related information. You may
[[Page 7298]]
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0142-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (cc)(9) and (cc)(10) of this AD.
(cc) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
March 17, 2015.
(i) Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012.
(ii) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012.
(iii) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010.
(iv) Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012.
(4) The following service information was approved for IBR on
September 11, 2012 (77 FR 46937, August 7, 2012).
(i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010.
(ii) Airbus Mandatory Service Bulletin A300-57-0251, including
Appendix 01, dated August 8, 2007.
(iii) Airbus Mandatory Service Bulletin A300-57-6106, Revision
03, dated January 26, 2012.
(iv) Airbus Mandatory Service Bulletin A300-57-6107, including
Appendix 01, August 8, 2007.
(5) The following service information was approved for IBR on
May 29, 2012 (77 FR 24367, April 24, 2012).
(i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03,
dated January 18, 2012.
(ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision
03, dated January 23, 2012.
(6) The following service information was approved for IBR on
September 17, 2008 (73 FR 47032, August 13, 2008).
(i) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007.
(ii) Airbus Service Bulletin A310-57-2091, excluding Appendix
01, dated May 22, 2007.
(iii) Airbus A310 Repair Instruction R572-49121, Issue C, dated
May 2007.
(7) The following service information was approved for IBR on
February 6, 2007 (72 FR 2612, January 22, 2007).
(i) Airbus Service Bulletin A310-57A2088, excluding Appendix 01,
dated November 6, 2006.
(ii) Reserved.
(8) For service information identified in this 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.
(9) 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.
(10) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-01710 Filed 2-9-15; 8:45 am]
BILLING CODE 4910-13-P
