[Federal Register Volume 80, Number 40 (Monday, March 2, 2015)]
[Rules and Regulations]
[Pages 11096-11101]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-02692]
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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.
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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 http://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 [email protected]; Internet http://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 http://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 [http://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 http://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 http://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: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(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 http://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 [email protected]; Internet http://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: http://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]
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