Airworthiness Directives; Airbus Airplanes, 11096-11101 [2015-02692]
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11096
Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations
(3) Continuing education/training
standards for State directors of school
nutrition programs and distributing
agencies. Each school year, all State
directors with responsibility for the
National School Lunch Program under
part 210 of this chapter and the School
Breakfast Program under part 220 of this
chapter, as well as those responsible for
the distribution of USDA donated foods
under part 250 of this chapter, must
complete a minimum of 15 hours of
training in core areas that may include
nutrition, operations, administration,
communications and marketing.
Additional hours and topics may be
specified by FNS, as needed, to address
Program integrity and other critical
issues.
(4) Provision of annual training. At
least annually, State agencies with
responsibility for the National School
Lunch Program under part 210 of this
chapter and the School Breakfast
Program under part 220 of this chapter,
as well as State agencies with
responsibility for the distribution of
USDA donated foods under part 250 of
this chapter, must provide or ensure
that State agency staff receive annual
continuing education/training.
(i) Each State agency with
responsibility for the National School
Lunch Program under part 210 of this
chapter and the School Breakfast
Program under part 220 of this chapter
must provide a minimum of 18 hours of
continuing education/training to school
food authorities. Topics include
administrative practices (including
training in application, certification,
verification, meal counting, and meal
claiming procedures); the accuracy of
approvals for free and reduced price
meals; the identification of reimbursable
meals at the point of service; nutrition;
health and food safety standards; the
efficient and effective use of USDA
donated foods; and any other
appropriate topics, as determined by
FNS, to ensure program compliance and
integrity or to address other critical
issues.
(ii) Each State agency with
responsibility for the distribution of
USDA donated foods under part 250 of
this chapter must provide or ensure
receipt of continuing education/training
to State distribution agency staff on an
annual basis. Topics may include the
efficient and effective use of USDA
donated foods; inventory rotation and
control; health and food safety
standards; and any other appropriate
topics, as determined by FNS, to ensure
program compliance and integrity or to
address other critical issues.
(5) Records and recordkeeping. State
agencies must annually retain records
for a period of three years to adequately
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demonstrate compliance with the
professional standards for State
directors of school nutrition programs
established in this paragraph.
(6) Failure to comply. Failure to
comply with the professional standards
in this paragraph may result in
sanctions as specified in paragraph (b)
of this section.
■ 13. Revise § 235.12 to read as follows:
§ 235.12 Information collection/
recordkeeping—OMB assigned control
numbers.
7 CFR Section
where
requirements
are
described
Current OMB control No.
235.3(b) ..........
235.4 ...............
235.5(b), (d) ....
235.7(a), (b) ....
235.9(c), (d) ....
235.11 .............
210.7 ...............
0584–0067.
0584–0067.
0584–0067.
0584–0067.
0584–0067.
0584–0067.
0584–0067.
Dated: February 24, 2015.
Audrey Rowe,
Administrator, Food and Nutrition Service.
[FR Doc. 2015–04234 Filed 2–27–15; 8:45 am]
BILLING CODE 3410–30–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0139; Directorate
Identifier 2012–NM–133–AD; Amendment
39–18081; AD 2015–02–14]
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) 2009–20–
05 for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2009–20–05 required one-time
inspections for cracking, damage,
correct installation, and correct
adjustment of the main landing gear
(MLG) door hinge and actuator fittings
on the keel beam, and corrective actions
if necessary. This new AD expands the
applicability, reduces the compliance
time, and requires repetitive inspections
instead of the one-time inspection. This
AD also requires revising the
maintenance or inspection program.
This AD was prompted by reports of
SUMMARY:
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cracks on fittings that had successfully
passed certain required inspections. We
are issuing this AD to detect and correct
cracking on the MLG door hinge fitting
and actuator fitting on the keel beam,
which could lead to in-flight
detachment of an MLG door, possibly
resulting in injury to persons on the
ground and/or damage to the airplane.
DATES: This AD becomes effective April
6, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 6, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 3, 2009 (74 FR
49795, September 29, 2009).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0139; 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, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com. You may 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–2014–0139.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–20–05,
Amendment 39–16028 (74 FR 49795,
September 29, 2009). AD 2009–20–05
applied to certain Model A318, A319,
A320, and A321 series airplanes. The
NPRM published in the Federal
Register on March 12, 2014 (79 FR
13925).
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The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2012–0118, dated July 4, 2012
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition on the specified products.
The MCAI states:
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Several cases of cracks have reportedly
been found on the MLG door hinge fitting
and on the MLG door actuator fitting on the
keel beam.
This condition, if not detected and
corrected, could lead to in-flight detachment
of a MLG door, possibly resulting in injury
to persons on the ground and/or damage to
the aeroplane.
To address this potential unsafe condition,
EASA issued EASA AD 2007–0161 [https://
ad.easa.europa.eu/blob/easa_ad_2007_0161_
superseded.pdf/AD_2007-0161_1] [which
corresponds to FAA AD 2009–20–05,
Amendment 39–16028 (74 FR 49795,
September 29, 2009)], to require a one-time
inspection of the affected fittings and
accomplishment of the applicable corrective
actions.
Since that [EASA] AD was issued, some
cracks have been found on fittings that had
successfully passed the one-time inspection
as required by EASA AD 2007–0161.
Analyses of these cracks have lead Airbus to
reconsider the repetitive inspections of the
MLG door hinge and actuator fittings on the
keel beam, in accordance with the ALI task
533154–02–1 requirement as defined in
Airbus A318/A319/A320/A321
Airworthiness Limitation Items (ALI)
Document, by introducing more restrictive
inspection thresholds and intervals.
For the reasons stated above, this [EASA]
AD, which supersedes EASA AD 2007–0161
and the ALI [Airworthiness Limitations Item]
task 533154–02–1 requirements, expands the
[EASA] AD applicability to all A318/A319/
A320/A321 aeroplanes and requires
repetitive inspections of the MLG door hinge
and actuator fittings on the keel beam at a
new threshold and interval and, depending
on findings, the accomplishment of
applicable corrective actions.
The inspections are detailed, high
frequency eddy current (HFEC), and
ultrasonic inspections for cracking,
damage, correct installation, and correct
adjustment, as applicable. The
corrective actions include correcting
incorrect adjustments and installations,
and repair. This AD also requires
revising the maintenance or inspection
program, as applicable, to remove ALI
task 533154–02–1. You may examine
the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-01390002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
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following presents the comments
received on the NPRM (79 FR 13925,
March 12, 2014) and the FAA’s response
to each comment.
Requests To Reference Revised Service
Bulletins
Airbus and United Airlines (UAL)
requested that we reference Airbus
Service Bulletin A320–53–1195,
Revision 05, dated November 22, 2013;
and Airbus Service Bulletin A320–53–
1196, Revision 04, dated November 22,
2013; as appropriate sources of service
information.
We agree with the commenters’
requests to reference Airbus Service
Bulletin A320–53–1195, Revision 05,
dated November 22, 2013; and Airbus
Service Bulletin A320–53–1196,
Revision 04, dated November 22, 2013;
as appropriate sources of service
information for accomplishing the
required actions in this AD. No
additional work is specified by these
service bulletin revisions for airplanes
modified by any previous issue. We
added a new paragraph (l) to this AD
and redesignated subsequent paragraphs
accordingly. New paragraph (l) gives
credit for actions accomplished using
certain service information before the
effective date of this AD.
We have revised paragraph (i)(1) of
this AD to refer to Airbus Service
Bulletin A320–53–1195, Revision 05,
dated November 22, 2013, and added
paragraph (l)(1) to this AD to give credit
for actions accomplished previously
using Airbus Service Bulletin A320–53–
1195, Revision 03, dated November 8,
2011; or Airbus Service Bulletin A320–
53–1195, Revision 04, dated August 22,
2012.
We have revised paragraph (i)(2) of
this AD to refer to Airbus Service
Bulletin A320–53–1196, Revision 04,
dated November 22, 2013; and added
paragraph (l)(2) to this AD to give credit
for actions accomplished using Airbus
Service Bulletin A320–53–1196,
Revision 02, dated November 8, 2011; or
Airbus Service Bulletin A320–53–1196,
Revision 03, dated August 22, 2012.
Request To Refer to Additional Service
Information for Task Removal
UAL requested that we revise
paragraph (k) of the proposed AD (79 FR
13925, March 12, 2014) to reference
Airbus A318/A319/A320/A321
Airworthiness Limitation Items,
Document AI/S–M4/95A.0252/96, Issue
10, dated October 2009; or Issue 11,
dated September 2010; in addition to
Airbus A318/A319/A320/A321 ALS
Part 2—Damage Tolerant Airworthiness
Limitations Items (DT ALI), Revision 01,
dated April 4, 2012. UAL stated that
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11097
Task 533154–02–1 of the Airbus A318/
A319/A320/A321 ALS Part 2—Damage
Tolerant Airworthiness Limitations
Items (DT ALI), Revision 01, dated April
4, 2012, is ‘‘superseded by Airbus
Service Bulletins A320–53–1195 and
A320–53–1196.’’ UAL explained that
operators that comply with Airbus
A318/A319/A320/A321 ALS Part 2—
Damage Tolerant Airworthiness
Limitations Items (DT ALI), Revision 01,
dated April 4, 2012, should already
have removed Task 533154–02–1 from
their maintenance/inspection programs.
UAL also explained that operators might
not have Airbus A318/A319/A320/A321
ALS Part 2—Damage Tolerant
Airworthiness Limitations Items (DT
ALI), Revision 01, dated April 4, 2012,
in their maintenance/inspection
programs and instead might have Airbus
A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE–M4/
95A.0252/96, Issue 10, dated October
2009; or Issue 11, dated September
2010.
We agree with the commenter’s
request to refer to Airbus A318/A319/
A320/A321 Airworthiness Limitation
Items, Document AI/SE–M4/95A.0252/
96, Issue 10, dated October 2009; or
Issue 11, dated September 2010; in
paragraph (k) of this AD. This revision
will ensure that the actions specified by
Task 533154–02–1 are removed from an
operator’s maintenance inspection
program.
Request To Remove Reporting
Requirement
UAL requested that we not require
reporting, as described in the service
information, if no damage and/or cracks
are found during the inspection of the
hinge fittings. UAL stated that reporting
has insignificant value and is a burden
on the operator. UAL explained that,
since the inspections must be
repetitively accomplished, the rate of
reporting no findings will be significant
without adding valued information, and
that any damage/cracks will be reported
to Airbus when they are contacted for
repair approval.
We disagree with the commenter’s
request to remove the reporting action
required by this AD. A reporting
requirement is instrumental in ensuring
that we can gather as much information
as possible regarding the extent and
nature of the identified unsafe
condition, especially in cases where that
data may not be available through other
established means. Also, the commenter
did not provided any rationale
concerning how eliminating the
reporting requirement will ensure that
future service information from Airbus
will continue to maintain operational
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safety of the fleet. We have not changed
this AD in this regard.
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Request To Remove Requirement To
Refer to This AD in Repair Approvals
UAL requested that we remove the
statement ‘‘for a repair method to be
approved, the repair approval must
specifically refer to this AD’’ in
paragraph (i) of the proposed AD (79 FR
13925, March 12, 2014). UAL stated that
this statement could have a significant
impact on the financial cost and
customer support between the operator
and Airbus. UAL also stated that this
statement should be removed for those
general reasons stated in A4A’s
comment on the same topic in NPRM
2012–NM–101–AD (78 FR 78285,
December 26, 2013), which stated,
among other justifications, that ‘‘The
added costs for this AD and all that may
follow bearing the new procedural
wording represent an unfair burden
placed solely on U.S. registered
aircraft.’’
We concur with the commenter’s
request to remove the requirement to
include the AD reference in repair
approvals. 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 FAAapproved. 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 13925, 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 a State of Design
Authority’s design organization
approval (DOA)’’ to refer to a DAH
authorized to approve required repairs
for the AD.
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Comments were provided to the
NPRM (79 FR 13925, March 12, 2014)
and to an NPRM referenced by the
commenter (i.e., Directorate Identifier
2012–NM–101–AD (78 FR 78285,
December 26, 2013)) about these
proposed changes. One commenter to
the NPRM having Directorate Identifier
2012–NM–101–AD, United Parcel
Service (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 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
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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 AD
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 NPRM 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 from this AD
that the DAH-provided repair
specifically refer to this AD. Before
adopting such a requirement in the
future, 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 an 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.
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
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13925, 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 13925,
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 Airbus Service Bulletin
A320–53–1195, Revision 05, dated
November 22, 2013, which describes
procedures for inspections of the MLG
door actuator fittings on the keel beam,
and corrective actions if necessary. We
also reviewed Airbus Service Bulletin
A320–53–1196, Revision 04, dated
November 22, 2013, which describes
procedures for inspections of the MLG
door hinge fitting on the keel beam, and
corrective actions if necessary. This
service information is reasonably
available; see ADDRESSES for ways to
access this service information.
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Costs of Compliance
We estimate that this AD affects 851
airplanes of U.S. registry.
The actions that are required by AD
2009–20–05, Amendment 39–16028 (74
FR 49795, September 29, 2009), and
retained in this AD take about 28 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 2009–
20–05 is $2,380 per product.
We also estimate that it will take
about 26 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 $1,880,710, or $2,210 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.
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
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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);
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-2014-0139; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
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11099
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
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)
2009–20–05, Amendment 39–16028 (74
FR 49795, September 29, 2009), and
adding the following new AD:
■
2015–02–14 Airbus: Amendment 39–18081.
Docket No. FAA–2014–0139; Directorate
Identifier 2012–NM–133–AD.
(a) Effective Date
This AD becomes effective April 6, 2015.
(b) Affected ADs
This AD replaces AD 2009–20–05,
Amendment 39–16028 (74 FR 49795,
September 29, 2009).
(c) Applicability
This AD applies to the Airbus airplanes
specified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers
(MSNs).
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
on the main landing gear (MLG) door hinge
fitting and actuator fitting on the keel beam.
We are issuing this AD to detect and correct
cracking on the MLG door hinge fitting and
actuator fitting on the keel beam, which
could lead to in-flight detachment of an MLG
door, possibly resulting in injury to persons
on the ground and/or damage to the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained One-Time Inspections and
Corrective Action
This paragraph restates the requirements of
paragraphs (f)(1) and (f)(2) of AD 2009–20–
05, Amendment 39–16028 (74 FR 49795,
September 29, 2009), with specific delegation
approval language. For airplanes having
serial numbers up to MSN 2850 inclusive,
except MSNs 0115, 0184, 0782, 1151, 1190,
2650, 2675, 2706, 2801, and 2837: Do the
actions required by paragraphs (g)(1) and
(g)(2) of this AD.
(1) At the latest of the times specified in
paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of
this AD: Perform detailed visual, high
frequency eddy current (HFEC), and
ultrasonic inspections (for cracking, damage,
correct installation, and correct adjustment,
as applicable) of the left-hand (LH) and righthand (RH) MLG door actuator fitting on the
keel beam, and do all applicable corrective
actions before further flight, except as
provided by paragraph (h) of this AD. Do all
actions required by this paragraph in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–53–1195, Revision 02,
including Appendix 01, dated April 5, 2007;
except where that service information
specifies that the applicable corrective action
is contacting Airbus, contact Airbus for
repair instructions and repair before further
flight. As of the effective date of this AD,
where that service information specifies that
the applicable corrective action is contacting
Airbus, before further flight, repair using a
method approved by the Manager, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
(i) Within 6,000 flight cycles since first
flight.
(ii) Within 1,500 flight cycles after
November 3, 2009 (the effective date of AD
2009–20–05, Amendment 39–16028 (74 FR
49795, September 29, 2009)).
(iii) Within 6,000 flight cycles from the
latest MLG door actuator fitting replacement.
(2) At the later of the times specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
Perform detailed visual and HFEC
inspections (for cracking, damage, correct
installation, and correct adjustment, as
applicable) of the LH and RH MLG door
hinge fitting on the keel beam, and do all
applicable corrective actions before further
flight, except as provided by paragraph (h) of
this AD. Do all actions required by this
paragraph in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–53–1196,
Revision 01, including Appendix 01, dated
November 29, 2006; except where that
service information specifies that the
applicable corrective action is contacting
Airbus, contact Airbus for repair instructions
and repair before further flight. As of the
effective date of this AD, where that service
information specifies that the applicable
corrective action is contacting Airbus, before
VerDate Sep<11>2014
14:17 Feb 27, 2015
Jkt 235001
further flight, repair using a method
approved by the Manager, ANM–116,
Transport Airplane Directorate, FAA; or the
EASA; or Airbus’s EASA DOA.
(i) Within 4,500 flight cycles since first
flight.
(ii) Within 1,500 flight cycles after
November 3, 2009 (the effective date of AD
2009–20–05, Amendment 39–16028 (74 FR
49795, September 29, 2009)).
(h) Retained Exception to Paragraph (g) of
This AD
This paragraph restates the exception
specified in paragraph (f)(4) of AD 2009–20–
05, Amendment 39–16028 (74 FR 49795,
September 29, 2009). Where the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–53–1195,
Revision 02, including Appendix 01, dated
April 5, 2007; or Airbus Mandatory Service
Bulletin A320–53–1196, Revision 01,
including Appendix 01, dated November 29,
2006; as applicable; specify to submit a
report where no damage or crack is found
during the inspection required by paragraph
(g)(1) or (g)(2) of this AD: Send the report to
Airbus using the applicable reporting sheet
in Appendix 01 of Airbus Mandatory Service
Bulletin A320–53–1195, Revision 02, dated
April 5, 2007; or Airbus Mandatory Service
Bulletin A320–53–1196, Revision 01, dated
November 29, 2006. Send the report at the
applicable time specified in paragraph (h)(1)
or (h)(2) of this AD.
(1) If the inspection was done on or after
November 3, 2009 (the effective date of AD
2009–20–05, Amendment 39–16028 (74 FR
49795, September 29, 2009)): Submit the
report within 30 days after the inspection.
(2) If the inspection was done before
November 3, 2009 (the effective date of AD
2009–20–05, Amendment 39–16028 (74 FR
49795, September 29, 2009)): Submit the
report within 30 days after November 3,
2009.
(i) New Repetitive Inspections and
Corrective Action
(1) At the latest of the times specified in
paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of
this AD: Perform detailed, HFEC, and
ultrasonic inspections (for cracking, damage,
correct installation, and correct adjustment,
as applicable) of the LH and RH MLG door
actuator fitting on the keel beam, and do all
applicable corrective actions before further
flight. Do all actions required by this
paragraph in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1195, Revision 05,
dated November 22, 2013; except where that
service information specifies that the
applicable corrective action is contacting
Airbus, before further flight, repair 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 inspections
thereafter at intervals not to exceed 2,250
flight cycles.
(i) Before the accumulation of 3,000 flight
cycles since first flight.
(ii) Within 2,250 flight cycles after the most
recent inspection done as described in
Airbus Service Bulletin A320–53–1195, or
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Task 533154–02–1 of the Airbus A318/A319/
A320/A321 Airworthiness Limitations
Section Part 2—Damage Tolerant
Airworthiness Limitations Items (DT ALI), as
applicable.
(iii) Within 1,500 flight cycles after the
effective date of this AD.
(2) At the latest of the times specified in
paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of
this AD: Perform detailed and HFEC
inspections (for cracking, damage, correct
installation, and correct adjustment, as
applicable) of the LH and RH MLG door
hinge fitting on the keel beam, and do all
applicable corrective actions before further
flight. Do all actions required by this
paragraph in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1196, Revision 04,
dated November 22, 2013; except where that
service information specifies that the
applicable corrective action is contacting
Airbus, before further flight, repair 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 inspections
thereafter at intervals not to exceed 3,000
flight cycles.
(i) Before the accumulation of 3,000 flight
cycles since first flight.
(ii) Within 3,000 flight cycles after the most
recent inspection done as described in
Airbus Service Bulletin A320–53–1196, or
Task 533154–02–1 of the Airbus A318/A319/
A320/A321 ALS Part 2—Damage Tolerant
Airworthiness Limitation Items (DT ALI), as
applicable.
(iii) Within 1,500 flight cycles after the
effective date of this AD.
(j) New Corrective Action Limitation
The accomplishment of a corrective action
on an airplane, as required by paragraph (i)
of this AD, does not constitute terminating
action for the repetitive inspection
requirements of this AD for that airplane.
(k) New Maintenance or Inspection Program
Revision
After the effective date of this AD and
before further flight after doing the
inspection required by paragraph (i) of this
AD: Revise the maintenance or inspection
program, as applicable, to remove Task
533154–02–1 of the Airbus A318/A319/
A320/A321 ALS Part 2—Damage Tolerant
Airworthiness Limitations Items (DT ALI),
Revision 01, dated April 4, 2012; Airbus
A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE–M4/
95A.0252/96, Issue 10, dated October 2009;
or Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96 Issue 11, dated
September 2010. The actions required by this
AD take precedence over Task 533154–02–1
of the Airbus A318/A319/A320/A321 ALS
Part 2—Damage Tolerant Airworthiness
Limitation Items (DT ALI), Revision 01, dated
April 4, 2012; Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 10, dated
October 2009; and Airbus A318/A319/A320/
A321 Airworthiness Limitation Items,
Document AI/SE–M4/95A.0252/96 Issue 11,
dated September 2010.
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(l) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (i)(1) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–53–1195, Revision 03,
dated November 8, 2011; or Airbus Service
Bulletin A320–53–1195, Revision 04, dated
August 22, 2012; which are not incorporated
by reference in this AD.
(2) This paragraph provides credit for
actions required by paragraph (i)(2) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–53–1196, Revision 02,
dated November 8, 2011; or Airbus Service
Bulletin A320–53–1196, Revision 03, dated
August 22, 2012; which are not incorporated
by reference in this AD.
(m) 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference 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
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
VerDate Sep<11>2014
14:17 Feb 27, 2015
Jkt 235001
11101
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
DEPARTMENT OF TRANSPORTATION
(n) Related Information
14 CFR Part 39
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0118, dated
July 4, 2012, for related information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0139-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (o)(5) and (o)(6) of this AD.
[Docket No. FAA–2014–0189; Directorate
Identifier 2013–NM–181–AD; Amendment
39–18099; AD 2015–03–03]
(o) 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 April 6, 2015.
(i) Airbus Service Bulletin A320–53–1195,
Revision 05, dated November 22, 2013.
(ii) Airbus Service Bulletin A320–53–1196,
Revision 04, dated November 22, 2013.
(4) The following service information was
approved for IBR on November 3, 2009 (74
FR 49795, September 29, 2009).
(i) Airbus Mandatory Service Bulletin
A320–53–1195, Revision 02, including
Appendix 01, dated April 5, 2007.
(ii) Airbus Mandatory Service Bulletin
A320–53–1196, Revision 01, including
Appendix 01, dated November 29, 2006.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 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.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–02692 Filed 2–27–15; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 series airplanes,
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). This AD was prompted
by a report of chafing found on the
overflow sensor harness of the surge
tank, and subsequent contact between
the electrical wiring and fuel tank
structure. This AD requires a one-time
inspection for chafing of the overflow
sensor harness, and repair if necessary.
This AD also requires modification of
the sensor harness. We are issuing this
AD to prevent chafing of the harness
and subsequent contact between the
electrical wiring and fuel tank structure,
which could result in electrical arcing
and a fuel tank explosion and
consequent loss of the airplane.
DATES: This AD becomes effective April
6, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 6, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0189 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, 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.airwortheas@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.
SUMMARY:
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]]>Agencies
[Federal Register Volume 80, Number 40 (Monday, March 2, 2015)]
[Rules and Regulations]
[Pages 11096-11101]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02692]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0139; Directorate Identifier 2012-NM-133-AD;
Amendment 39-18081; AD 2015-02-14]
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) 2009-20-05 for
certain Airbus Model A318, A319, A320, and A321 series airplanes. AD
2009-20-05 required one-time inspections for cracking, damage, correct
installation, and correct adjustment of the main landing gear (MLG)
door hinge and actuator fittings on the keel beam, and corrective
actions if necessary. This new AD expands the applicability, reduces
the compliance time, and requires repetitive inspections instead of the
one-time inspection. This AD also requires revising the maintenance or
inspection program. This AD was prompted by reports of cracks on
fittings that had successfully passed certain required inspections. We
are issuing this AD to detect and correct cracking on the MLG door
hinge fitting and actuator fitting on the keel beam, which could lead
to in-flight detachment of an MLG door, possibly resulting in injury to
persons on the ground and/or damage to the airplane.
DATES: This AD becomes effective April 6, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 6,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 3, 2009 (74 FR 49795, September 29, 2009).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0139; 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,
Airworthiness Office--EIAS, 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-
0139.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009). AD 2009-20-05 applied to certain Model A318, A319,
A320, and A321 series airplanes. The NPRM published in the Federal
Register on March 12, 2014 (79 FR 13925).
[[Page 11097]]
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2012-0118, dated July 4, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on the specified
products. The MCAI states:
Several cases of cracks have reportedly been found on the MLG
door hinge fitting and on the MLG door actuator fitting on the keel
beam.
This condition, if not detected and corrected, could lead to in-
flight detachment of a MLG door, possibly resulting in injury to
persons on the ground and/or damage to the aeroplane.
To address this potential unsafe condition, EASA issued EASA AD
2007-0161 [https://ad.easa.europa.eu/blob/easa_ad_2007_0161_superseded.pdf/AD_2007-0161_1] [which corresponds
to FAA AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29,
2009)], to require a one-time inspection of the affected fittings
and accomplishment of the applicable corrective actions.
Since that [EASA] AD was issued, some cracks have been found on
fittings that had successfully passed the one-time inspection as
required by EASA AD 2007-0161. Analyses of these cracks have lead
Airbus to reconsider the repetitive inspections of the MLG door
hinge and actuator fittings on the keel beam, in accordance with the
ALI task 533154-02-1 requirement as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation Items (ALI) Document, by
introducing more restrictive inspection thresholds and intervals.
For the reasons stated above, this [EASA] AD, which supersedes
EASA AD 2007-0161 and the ALI [Airworthiness Limitations Item] task
533154-02-1 requirements, expands the [EASA] AD applicability to all
A318/A319/A320/A321 aeroplanes and requires repetitive inspections
of the MLG door hinge and actuator fittings on the keel beam at a
new threshold and interval and, depending on findings, the
accomplishment of applicable corrective actions.
The inspections are detailed, high frequency eddy current (HFEC), and
ultrasonic inspections for cracking, damage, correct installation, and
correct adjustment, as applicable. The corrective actions include
correcting incorrect adjustments and installations, and repair. This AD
also requires revising the maintenance or inspection program, as
applicable, to remove ALI task 533154-02-1. You may examine the MCAI in
the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0139-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 13925, March 12, 2014) and the FAA's response to each comment.
Requests To Reference Revised Service Bulletins
Airbus and United Airlines (UAL) requested that we reference Airbus
Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013;
and Airbus Service Bulletin A320-53-1196, Revision 04, dated November
22, 2013; as appropriate sources of service information.
We agree with the commenters' requests to reference Airbus Service
Bulletin A320-53-1195, Revision 05, dated November 22, 2013; and Airbus
Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013; as
appropriate sources of service information for accomplishing the
required actions in this AD. No additional work is specified by these
service bulletin revisions for airplanes modified by any previous
issue. We added a new paragraph (l) to this AD and redesignated
subsequent paragraphs accordingly. New paragraph (l) gives credit for
actions accomplished using certain service information before the
effective date of this AD.
We have revised paragraph (i)(1) of this AD to refer to Airbus
Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013,
and added paragraph (l)(1) to this AD to give credit for actions
accomplished previously using Airbus Service Bulletin A320-53-1195,
Revision 03, dated November 8, 2011; or Airbus Service Bulletin A320-
53-1195, Revision 04, dated August 22, 2012.
We have revised paragraph (i)(2) of this AD to refer to Airbus
Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013;
and added paragraph (l)(2) to this AD to give credit for actions
accomplished using Airbus Service Bulletin A320-53-1196, Revision 02,
dated November 8, 2011; or Airbus Service Bulletin A320-53-1196,
Revision 03, dated August 22, 2012.
Request To Refer to Additional Service Information for Task Removal
UAL requested that we revise paragraph (k) of the proposed AD (79
FR 13925, March 12, 2014) to reference Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/S-M4/95A.0252/96, Issue 10,
dated October 2009; or Issue 11, dated September 2010; in addition to
Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant Airworthiness
Limitations Items (DT ALI), Revision 01, dated April 4, 2012. UAL
stated that Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part
2--Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision
01, dated April 4, 2012, is ``superseded by Airbus Service Bulletins
A320-53-1195 and A320-53-1196.'' UAL explained that operators that
comply with Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4,
2012, should already have removed Task 533154-02-1 from their
maintenance/inspection programs. UAL also explained that operators
might not have Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4,
2012, in their maintenance/inspection programs and instead might have
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/
SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated
September 2010.
We agree with the commenter's request to refer to Airbus A318/A319/
A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/
96, Issue 10, dated October 2009; or Issue 11, dated September 2010; in
paragraph (k) of this AD. This revision will ensure that the actions
specified by Task 533154-02-1 are removed from an operator's
maintenance inspection program.
Request To Remove Reporting Requirement
UAL requested that we not require reporting, as described in the
service information, if no damage and/or cracks are found during the
inspection of the hinge fittings. UAL stated that reporting has
insignificant value and is a burden on the operator. UAL explained
that, since the inspections must be repetitively accomplished, the rate
of reporting no findings will be significant without adding valued
information, and that any damage/cracks will be reported to Airbus when
they are contacted for repair approval.
We disagree with the commenter's request to remove the reporting
action required by this AD. A reporting requirement is instrumental in
ensuring that we can gather as much information as possible regarding
the extent and nature of the identified unsafe condition, especially in
cases where that data may not be available through other established
means. Also, the commenter did not provided any rationale concerning
how eliminating the reporting requirement will ensure that future
service information from Airbus will continue to maintain operational
[[Page 11098]]
safety of the fleet. We have not changed this AD in this regard.
Request To Remove Requirement To Refer to This AD in Repair Approvals
UAL requested that we remove the statement ``for a repair method to
be approved, the repair approval must specifically refer to this AD''
in paragraph (i) of the proposed AD (79 FR 13925, March 12, 2014). UAL
stated that this statement could have a significant impact on the
financial cost and customer support between the operator and Airbus.
UAL also stated that this statement should be removed for those general
reasons stated in A4A's comment on the same topic in NPRM 2012-NM-101-
AD (78 FR 78285, December 26, 2013), which stated, among other
justifications, that ``The added costs for this AD and all that may
follow bearing the new procedural wording represent an unfair burden
placed solely on U.S. registered aircraft.''
We concur with the commenter's request to remove the requirement to
include the AD reference in repair approvals. 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 13925, 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 a
State of Design Authority's design organization approval (DOA)'' to
refer to a DAH authorized to approve required repairs for the AD.
Comments were provided to the NPRM (79 FR 13925, March 12, 2014)
and to an NPRM referenced by the commenter (i.e., Directorate
Identifier 2012-NM-101-AD (78 FR 78285, December 26, 2013)) about these
proposed changes. One commenter to the NPRM having Directorate
Identifier 2012-NM-101-AD, United Parcel Service (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 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 AD 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 NPRM 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 from this AD
that the DAH-provided repair specifically refer to this AD. Before
adopting such a requirement in the future, 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
an 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.
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
[[Page 11099]]
13925, 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 13925, 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 Airbus Service Bulletin A320-53-1195, Revision 05,
dated November 22, 2013, which describes procedures for inspections of
the MLG door actuator fittings on the keel beam, and corrective actions
if necessary. We also reviewed Airbus Service Bulletin A320-53-1196,
Revision 04, dated November 22, 2013, which describes procedures for
inspections of the MLG door hinge fitting on the keel beam, and
corrective actions if necessary. This service information is reasonably
available; see ADDRESSES for ways to access this service information.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
The actions that are required by AD 2009-20-05, Amendment 39-16028
(74 FR 49795, September 29, 2009), and retained in this AD take about
28 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 2009-20-05 is $2,380 per product.
We also estimate that it will take about 26 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 $1,880,710, or $2,210 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.
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);
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-2014-0139; 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)
2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009), and
adding the following new AD:
2015-02-14 Airbus: Amendment 39-18081. Docket No. FAA-2014-0139;
Directorate Identifier 2012-NM-133-AD.
(a) Effective Date
This AD becomes effective April 6, 2015.
(b) Affected ADs
This AD replaces AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009).
(c) Applicability
This AD applies to the Airbus airplanes specified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers (MSNs).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks on the main landing
gear (MLG) door hinge fitting and actuator fitting on the keel beam.
We are issuing this AD to detect and correct cracking on the MLG
door hinge fitting and actuator fitting on the keel beam, which
could lead to in-flight detachment of an MLG door, possibly
resulting in injury to persons on the ground and/or damage to the
airplane.
[[Page 11100]]
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained One-Time Inspections and Corrective Action
This paragraph restates the requirements of paragraphs (f)(1)
and (f)(2) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009), with specific delegation approval language. For
airplanes having serial numbers up to MSN 2850 inclusive, except
MSNs 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837:
Do the actions required by paragraphs (g)(1) and (g)(2) of this AD.
(1) At the latest of the times specified in paragraphs
(g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Perform detailed
visual, high frequency eddy current (HFEC), and ultrasonic
inspections (for cracking, damage, correct installation, and correct
adjustment, as applicable) of the left-hand (LH) and right-hand (RH)
MLG door actuator fitting on the keel beam, and do all applicable
corrective actions before further flight, except as provided by
paragraph (h) of this AD. Do all actions required by this paragraph
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320-53-1195, Revision 02, including
Appendix 01, dated April 5, 2007; except where that service
information specifies that the applicable corrective action is
contacting Airbus, contact Airbus for repair instructions and repair
before further flight. As of the effective date of this AD, where
that service information specifies that the applicable corrective
action is contacting Airbus, before further flight, repair using a
method approved by the Manager, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
(i) Within 6,000 flight cycles since first flight.
(ii) Within 1,500 flight cycles after November 3, 2009 (the
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009)).
(iii) Within 6,000 flight cycles from the latest MLG door
actuator fitting replacement.
(2) At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD: Perform detailed visual and HFEC
inspections (for cracking, damage, correct installation, and correct
adjustment, as applicable) of the LH and RH MLG door hinge fitting
on the keel beam, and do all applicable corrective actions before
further flight, except as provided by paragraph (h) of this AD. Do
all actions required by this paragraph in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-53-1196, Revision 01, including Appendix 01, dated November 29,
2006; except where that service information specifies that the
applicable corrective action is contacting Airbus, contact Airbus
for repair instructions and repair before further flight. As of the
effective date of this AD, where that service information specifies
that the applicable corrective action is contacting Airbus, before
further flight, repair using a method approved by the Manager, ANM-
116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's
EASA DOA.
(i) Within 4,500 flight cycles since first flight.
(ii) Within 1,500 flight cycles after November 3, 2009 (the
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009)).
(h) Retained Exception to Paragraph (g) of This AD
This paragraph restates the exception specified in paragraph
(f)(4) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September
29, 2009). Where the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-53-1195, Revision 02, including Appendix 01,
dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53-
1196, Revision 01, including Appendix 01, dated November 29, 2006;
as applicable; specify to submit a report where no damage or crack
is found during the inspection required by paragraph (g)(1) or
(g)(2) of this AD: Send the report to Airbus using the applicable
reporting sheet in Appendix 01 of Airbus Mandatory Service Bulletin
A320-53-1195, Revision 02, dated April 5, 2007; or Airbus Mandatory
Service Bulletin A320-53-1196, Revision 01, dated November 29, 2006.
Send the report at the applicable time specified in paragraph (h)(1)
or (h)(2) of this AD.
(1) If the inspection was done on or after November 3, 2009 (the
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009)): Submit the report within 30 days after the
inspection.
(2) If the inspection was done before November 3, 2009 (the
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795,
September 29, 2009)): Submit the report within 30 days after
November 3, 2009.
(i) New Repetitive Inspections and Corrective Action
(1) At the latest of the times specified in paragraphs
(i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD: Perform detailed,
HFEC, and ultrasonic inspections (for cracking, damage, correct
installation, and correct adjustment, as applicable) of the LH and
RH MLG door actuator fitting on the keel beam, and do all applicable
corrective actions before further flight. Do all actions required by
this paragraph in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1195, Revision 05, dated November
22, 2013; except where that service information specifies that the
applicable corrective action is contacting Airbus, before further
flight, repair 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 inspections thereafter at intervals
not to exceed 2,250 flight cycles.
(i) Before the accumulation of 3,000 flight cycles since first
flight.
(ii) Within 2,250 flight cycles after the most recent inspection
done as described in Airbus Service Bulletin A320-53-1195, or Task
533154-02-1 of the Airbus A318/A319/A320/A321 Airworthiness
Limitations Section Part 2--Damage Tolerant Airworthiness
Limitations Items (DT ALI), as applicable.
(iii) Within 1,500 flight cycles after the effective date of
this AD.
(2) At the latest of the times specified in paragraphs
(i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD: Perform detailed
and HFEC inspections (for cracking, damage, correct installation,
and correct adjustment, as applicable) of the LH and RH MLG door
hinge fitting on the keel beam, and do all applicable corrective
actions before further flight. Do all actions required by this
paragraph in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1196, Revision 04, dated November
22, 2013; except where that service information specifies that the
applicable corrective action is contacting Airbus, before further
flight, repair 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 inspections thereafter at intervals
not to exceed 3,000 flight cycles.
(i) Before the accumulation of 3,000 flight cycles since first
flight.
(ii) Within 3,000 flight cycles after the most recent inspection
done as described in Airbus Service Bulletin A320-53-1196, or Task
533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--Damage
Tolerant Airworthiness Limitation Items (DT ALI), as applicable.
(iii) Within 1,500 flight cycles after the effective date of
this AD.
(j) New Corrective Action Limitation
The accomplishment of a corrective action on an airplane, as
required by paragraph (i) of this AD, does not constitute
terminating action for the repetitive inspection requirements of
this AD for that airplane.
(k) New Maintenance or Inspection Program Revision
After the effective date of this AD and before further flight
after doing the inspection required by paragraph (i) of this AD:
Revise the maintenance or inspection program, as applicable, to
remove Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part
2--Damage Tolerant Airworthiness Limitations Items (DT ALI),
Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Airbus A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated
September 2010. The actions required by this AD take precedence over
Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--
Damage Tolerant Airworthiness Limitation Items (DT ALI), Revision
01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated
October 2009; and Airbus A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated
September 2010.
[[Page 11101]]
(l) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (i)(1) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-53-
1195, Revision 03, dated November 8, 2011; or Airbus Service
Bulletin A320-53-1195, Revision 04, dated August 22, 2012; which are
not incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraph (i)(2) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-53-
1196, Revision 02, dated November 8, 2011; or Airbus Service
Bulletin A320-53-1196, Revision 03, dated August 22, 2012; which are
not incorporated by reference in this AD.
(m) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) 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 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0118, dated July 4, 2012,
for related information. You may examine the MCAI in the AD docket
on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0139-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (o)(5) and (o)(6) of this AD.
(o) 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
April 6, 2015.
(i) Airbus Service Bulletin A320-53-1195, Revision 05, dated
November 22, 2013.
(ii) Airbus Service Bulletin A320-53-1196, Revision 04, dated
November 22, 2013.
(4) The following service information was approved for IBR on
November 3, 2009 (74 FR 49795, September 29, 2009).
(i) Airbus Mandatory Service Bulletin A320-53-1195, Revision 02,
including Appendix 01, dated April 5, 2007.
(ii) Airbus Mandatory Service Bulletin A320-53-1196, Revision
01, including Appendix 01, dated November 29, 2006.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 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.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-02692 Filed 2-27-15; 8:45 am]
BILLING CODE 4910-13-P
