[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70447-70453]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-26986]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0132; Directorate Identifier 2012-NM-007-AD;
Amendment 39-18023; AD 2014-23-07]
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) 2004-16-01 for
certain Airbus Model A330-200 and -300 series airplanes and Model A340-
200 and -300 series airplanes. AD 2004-16-01 required repetitive
inspections for cracking of the chromed area of the left and right
piston rods for the main landing gear (MLG) retraction actuators, and
related investigative and corrective actions if necessary. This new AD
requires repetitive draining of any fluid from the retraction actuator
piston rod internal volume and sealing of the vent hole; repetitive
ultrasonic inspections of the upper end of the piston rods, and
corrective actions if necessary; a one-time ultrasonic inspection
(longitudinal and circumferential) of the full length of the piston
rod, and corrective actions if necessary; and a terminating
modification of the left-hand and right-hand MLG retraction actuators.
This AD was prompted by reports of the piston rods for the MLG
retraction actuators rupturing during flight. We are issuing this AD to
prevent cracking of the piston rods for the MLG retraction actuators,
which could result in rupture of a piston rod, non-damped extension of
the MLG, high loads on the fully extended MLG, and consequent reduced
structural integrity of the MLG.
DATES: This AD becomes effective December 31, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 31,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
19, 2004 (69 FR 46979, August 4, 2004).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0132; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Airbus SAS--
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80;
email [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.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
[[Page 70448]]
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2004-16-01, Amendment 39-13757 (69 FR 46979,
August 4, 2004). AD 2004-16-01 applied to certain Airbus Model A330-200
and -300 series airplanes and Model A340-200 and -300 series airplanes.
The NPRM published in the Federal Register on February 6, 2014 (79 FR
7098; corrected March 20, 2014 (79 FR 15555)). The NPRM was prompted by
reports of the piston rods for the MLG retraction actuators rupturing
during flight.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012 (for Model
A340-200 and -300 series airplanes); and EASA AD 2011-0179R1, dated
March 6, 2012 (for Model A330-200 and -300 series airplanes) (both
referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''); to correct an unsafe condition for the
specified products. EASA AD 2011-0178R1, dated March 6, 2012, corrected
March 7, 2012, states:
During an approach phase, the flight crew of an A330 aeroplane
had to perform a free-fall extension of the left-hand (LH) MLG.
Rupture of the LH MLG retraction actuator piston rod was found
near the rod attachment point. The inspection revealed at the
location of the rupture the presence of corrosion resulting from
incorrect application of the anticorrosion protection, and
circumferential cracks resulting from normal operational loading
effects.
Since the above rupture, new cases of crack propagation along
the length of the piston rod occurred. These ruptures led to a non-
damped extension of the landing gear. Fully extended, the landing
gear assembly was submitted to high loads jeopardising its
structural integrity.
This condition, if not detected and corrected, could lead to MLG
failure during landing or roll-out and consequent damage to the
aeroplane and injury to occupants.
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD F-2005-098 [http://ad.easa.europa.eu/blob/easa_ad_2005_5887_F20050980tb_superseded.pdf/AD_F-2005-098_1] (EASA
approval 2005-5887) [and AD F-2005-099 [http://ad.easa.europa.eu/blob/easa_ad_2005_5888_F20050990tb_superseded.pdf/AD_F-2005-099_2]
(EASA approval 2005-5888)] to address this unsafe condition [the FAA
issued AD 2004-16-01, Amendment 39-13757 (69 FR 46979, August 4,
2004)]. Since that [DGAC France] AD was issued, the results of
extensive investigation determined that the presence of water in the
internal volume of the piston rod can lead to the formation of ice
which represents a potential source of high magnitude tensile hoop
stresses in the material of the rod, leading to propagation of
longitudinal crack in the body of the piston rod.
Prompted by these findings, EASA issued AD 2006-0301 [http://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1], partially retaining the requirements of DGAC France AD F-
2005-099, which was superseded, and to revise the inspection
requirements as follows:
a. Extend the repetitive inspections interval for the removal of
fluid from the internal volume of the piston rod using flight cycles
in lieu of flight hours as this better represents the mechanism for
the accumulation of water within the piston rod.
b. Remove the preliminary visual inspection from the ultrasonic
longitudinal inspection of the upper end of the piston rod.
c. Add a new one-time ultrasonic longitudinal and
circumferential inspection of the full piston rod length to
eliminate any parts that exhibit severe corrosion along the internal
length of the piston rod.
d. Require installation of new design hollow piston rod Part
Number (P/N) 114256328 (Airbus mod. 52980--SB A340-32-4222 Revision
01) without a vent hole, thus eliminating moisture ingress as the
terminating action.
EASA AD 2006-0301 was later revised:
--at revision 01, to correct a number of typographical errors and to
add reference to Airbus SB A340-32-4212 Revision 04, and
--at revision 02 to extend the inspections threshold from 3 to 6
years in service usage for retraction actuator piston rod P/N
114256321 issue 06 which was re-identified to P/N 114256326 issue 01
in accordance with the instructions of Airbus SB A340-32-4260.
More recently, the sampling of piston rod P/N 114256326 issue 1
and P/N 114256321 issue 06 have confirmed the need to replace all
retraction actuator piston rods with a piston rod P/N114256328.
For the reasons described above, this [EASA] AD at original
issue retained the requirements of EASA AD 2006-0301R2 (http://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1), which is superseded, and required the replacement of all
retraction actuator piston rods with a piston rod P/N 114256328,
which constitutes terminating action to the repetitive requirements
of this AD.
This [EASA] AD is revised to clarify that aeroplanes on which
Airbus mod. 52980 has been embodied in production are not required
to accomplish the reidentification of MLG retraction actuator P/N
114256002-055 which is mentioned in the accomplishment instructions
of Airbus SB A340-32-4222 Revision 03.
This [EASA] AD has been republished to correct a typographical
mistake of the applicable Airbus SB number in the Applicability (in
the Note) and in the Reason sections of this [EASA] AD.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0132-0003.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)), and
the FAA's response to each comment.
Request To Reference Latest Service Information
Delta Airlines requested that we reference the latest Airbus
service information, which is Airbus Service Bulletin A330-32-3180,
Revision 05, dated January 27, 2014. Delta Airlines further requested
that we provide credit for actions previously accomplished using Airbus
Service Bulletin A330-32-3180, Revision 03, dated January 28, 2011; and
Airbus Service Bulletin A330-32-3180, Revision 04, dated July 30, 2013.
We agree with Delta Airlines' comment to reference the latest
service information. Airbus Service Bulletin A330-32-3180, Revision 05,
dated January 27, 2014, provides the latest information on the
modification required by this AD. This service bulletin specifies two
additional work-hours for re-identification of the part number of the
MLG retraction actuator for Model A330-200 and -300 series airplanes at
configuration 3, which were modified as described in Airbus Service
Bulletin A330-32-3180, Revision 03, dated January 28, 2011. Re-
identification of the MLG retraction actuator may be considered as a
logical outgrowth of the proposed AD (79 FR 7098, February 6, 2014;
corrected March 20, 2014 (79 FR 15555)) requirements.
Airbus has also released Service Bulletin A340-32-4222, Revision
04, dated July 30, 2013. This service bulletin also specifies two
additional work-hours for re-identification of the part number of the
MLG retraction actuator for Model A340 series airplanes. There are
currently no U.S.-registered Model A340 series airplanes. We have
revised paragraphs (s) and (t) of this AD to specify Airbus Service
Bulletin A330-32-3180, Revision 05, dated January 27, 2014; and Airbus
Service Bulletin A340-32-4222, Revision 04, dated July 30, 2013; as the
appropriate sources of service information for the required actions in
those paragraphs. We have also revised paragraphs (w)(2) and (w)(3) of
this AD to provide credit for previous actions
[[Page 70449]]
accomplished using Airbus Service Bulletin A330-32-3180, Revision 03,
dated January 28, 2011; Airbus Service Bulletin A330-32-3180, Revision
04, dated July 30, 2013; and Airbus Service Bulletin A340-32-4222,
Revision 03, dated January 28, 2011; as applicable.
``Contacting the Manufacturer'' Paragraph in This AD
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 7098, February 6, 2014; corrected March 20, 2014
(79 FR 15555)), 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 a design approval
holder (DAH) with State of Design Authority design organization
approval (DOA), as applicable, to refer to a DAH authorized to approve
required repairs for the proposed AD.
No comments were provided to the NPRM (79 FR 7098, February 6,
2014; corrected March 20, 2014 (79 FR 15555)) about these proposed
changes. However, a comment was provided for an NPRM having Directorate
Identifier 2012-NM-101-AD (78 FR 78285, December 26, 2013). The
commenter 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 the 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, the European Aviation Safety Agency (EASA), or Airbus's
EASA Design Organization Approval (DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might have been issued some time before the FAA AD. Therefore, the
DOA might have provided U.S. operators with an approved repair,
developed with full awareness of the unsafe condition, before the FAA
AD is issued. Under these circumstances, to comply with the FAA AD, the
operator would be required to go back to the manufacturer's DOA and
obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``DAH with State of Design Authority design
organization approval,'' but instead we have provided the specific
delegation approval granted by the State of Design Authority for the
DAH.
Conclusion
We reviewed the available data, including the comment 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 7098, February 6, 2014; corrected March 20, 2014 (79 FR
15555)) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 7098, February 6, 2014; corrected
March 20, 2014 (79 FR 15555)).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 24 Model A330-200 and -300 series
airplanes of U.S. registry. There are no
[[Page 70450]]
Model A340-200 or -300 series airplanes of U.S. registry.
We estimate that it will take about 67 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $56,000 per
product (2 actuators). Based on these figures, we estimate the cost of
this AD on U.S. operators to be $1,480,680, or $61,695 per product.
In addition, we estimate that any necessary follow-on actions will
take about 38 work-hours and require parts costing $56,000 (2
actuators), for a cost of $59,230 per product. We have no way of
determining the number of aircraft that might need these actions.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
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-2014-0132; 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)
2004-16-01, Amendment 39-13757 (69 FR 46979, August 4, 2004), and
adding the following new AD:
2014-23-07 Airbus: Amendment 39-18023. Docket No. FAA-2014-0132;
Directorate Identifier 2012-NM-007-AD.
(a) Effective Date
This AD becomes effective December 31, 2014.
(b) Affected ADs
This AD replaces AD 2004-16-01, Amendment 39-13757 (69 FR 46979,
August 4, 2004).
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-211, -212, -213, -311, -312, and -313
airplanes; certificated in any category; all manufacturer serial
numbers, except for those airplanes that have had Airbus
Modification 52980 incorporated in production on both main landing
gear (MLG) units, or airplanes that have had Airbus Modification
54500 incorporated in production.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of the piston rods for the MLG
retraction actuators rupturing during flight. We are issuing this AD
to prevent cracking of the piston rods for the MLG retraction
actuators, which could result in rupture of a piston rod, non-damped
extension of the MLG, high loads on the fully extended MLG, and
consequent reduced structural integrity of the MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Detailed Inspections
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Do a detailed inspection for cracking of the visible
chromed area of the MLG retraction actuator piston rods in the fully
extended position, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330-200 and -300 series
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05,
dated September 26, 2008 (for Model A340-200 and -300 series
airplanes). Repeat the inspection thereafter at intervals not to
exceed 8 days until the actions required by paragraphs (j) and (o)
of this AD are accomplished.
(1) For MLG retraction actuator piston rods that have not had a
detailed inspection accomplished as of the effective date of this
AD, as described in any applicable service information specified in
paragraph (h)(1) or (h)(2) of this AD: At the applicable time
[[Page 70451]]
specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For MLG retraction actuator piston rods having part number
(P/N) 114256309 or P/N 114256321 issue 03: Do the inspection within
60 days after the effective date of this AD, or before the MLG
retraction actuator has been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01 or P/N 114256321 issue 06: Do the inspection
within 60 days after the effective date of this AD, or before the
MLG retraction actuator has been in service 72 months, whichever
occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had a detailed inspection accomplished
as of the effective date of this AD, as described in the applicable
service information specified in paragraph (h)(1) or (h)(2) of this
AD: Inspect within 8 days after the effective date of this AD.
(h) Service Information for Determining Airplane Configuration for the
Actions Required by Paragraph (g) of This AD
(1) For Model A330-200 and -300 series airplanes:
(i) Airbus Service Bulletin A330-32-3173, Revision 01, dated
June 16, 2004;
(ii) Airbus Service Bulletin A330-32-3173, Revision 02, dated
May 11, 2005;
(iii) Airbus Service Bulletin A330-32-3173, Revision 03, dated
March 13, 2006;
(iv) Airbus Service Bulletin A330-32-3173, Revision 04, dated
June 12, 2006; or
(v) Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Service Bulletin A340-32-4212, Revision 01, dated
June 16, 2004;
(ii) Airbus Service Bulletin A340-32-4212, Revision 02, dated
May 11, 2005;
(iii) Airbus Service Bulletin A340-32-4212, Revision 03, dated
March 13, 2006;
(iv) Airbus Service Bulletin A340-32-4212, Revision 04, dated
June 12, 2006; or
(v) Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008.
(i) Corrective Action for Cracking
If any cracking is found during any inspection required by
paragraph (g) of this AD: Before further flight, replace the MLG
retraction actuator with a new or serviceable part, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330-
200 and -300 series airplanes); or Airbus Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and
-300 series airplanes).
(j) Repetitive Fluid Draining and Vent Hole Sealing
At the applicable time specified in paragraph (j)(1) or (j)(2)
of this AD: Drain any fluid from the retraction actuator piston rod
internal volume and seal the vent hole, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-32-3173,
Revision 05, dated September 26, 2008 (for Model A330-200 and -300
series airplanes); or Airbus Service Bulletin A340-32-4212, Revision
05, dated September 26, 2008 (for Model A340-200 and -300 series
airplanes). Repeat the draining and sealing thereafter at intervals
not to exceed 1,000 flight cycles or 24 months, whichever occurs
first.
(1) For MLG retraction actuator piston rods that have not been
inspected and have not had the fluid drained as of the effective
date of this AD, as described in the applicable service information
specified in paragraph (k)(1) or (k)(2) of this AD: At the
applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of
this AD.
(i) For MLG retraction actuator piston rods having P/N 114256309
or P/N 114256321 issue 03: Do the draining and sealing within 60
days after the effective date of this AD, or before the MLG
retraction actuator has been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01 or P/N 114256321 issue 06: Do the draining and
sealing within 60 days after the effective date of this AD, or
before the MLG retraction actuator has been in service 72 months,
whichever occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have been inspected and the fluid drained
as of the effective date of this AD, as described in the applicable
service information specified in paragraph (k)(1) or (k)(2) of this
AD: Do the draining and sealing at the later of the times specified
in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 1,000 flight cycles or 24 months, whichever occurs
first, from the last inspection and fluid drainage accomplished in
accordance with the requirements of paragraph (j) of this AD.
(ii) Within 60 days after the effective date of this AD.
(k) Service Information for Determining Airplane Configuration for the
Actions Required by Paragraph (j) of This AD
(1) For Model A330-200 and -300 series airplanes:
(i) Airbus Service Bulletin A330-32-3173, Revision 02, dated May
11, 2005;
(ii) Airbus Service Bulletin A330-32-3173, Revision 03, dated
March 13, 2006;
(iii) Airbus Service Bulletin A330-32-3173, Revision 04, dated
June 12, 2006; or
(iv) Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Service Bulletin A340-32-4212, Revision 02, dated May
11, 2005;
(ii) Airbus Service Bulletin A340-32-4212, Revision 03, dated
March 13, 2006;
(iii) Airbus Service Bulletin A340-32-4212, Revision 04, dated
June 12, 2006; or
(iv) Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008.
(l) Ultrasonic Inspection
At the applicable time specified in paragraph (l)(1) or (l)(2)
of this AD: Do an ultrasonic longitudinal inspection for cracking of
the retraction actuator piston rod end, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-32-3173,
Revision 05, dated September 26, 2008 (for Model A330-200 and -300
series airplanes); or Airbus Service Bulletin A340-32-4212, Revision
05, dated September 26, 2008 (for Model A340-200 and -300 series
airplanes).
(1) For MLG retraction actuator piston rods that have not had a
non-destructive test (NDT) inspection as of the effective date of
this AD, as described in the applicable service information
specified in paragraph (m)(1) or (m)(2) of this AD: At the
applicable time specified in paragraph (l)(1)(i) or (l)(1)(ii) of
this AD.
(i) For MLG retraction actuator piston rods having P/N 114256309
or P/N 114256321 issue 03: Do the inspection within 60 days after
the effective date of this AD, or before the MLG retraction actuator
has been in service 36 months, whichever occurs later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01 or P/N 114256321 issue 06: Do the inspection
within 60 days after the effective date of this AD, or before the
MLG retraction actuator has been in service 72 months, whichever
occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had an NDT inspection as of the
effective date of this AD, as described in the applicable service
information specified in paragraph (m)(1) or (m)(2) of this AD: Do
the inspection at the later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within 1,400 flight hours, 250 flight cycles, or 4 months,
whichever occurs first after the date of the last ultrasonic
longitudinal inspection performed as described in the applicable
service information specified in paragraph (m)(1) or (m)(2) of this
AD.
(ii) Within 60 days after the effective date of this AD.
(m) Service Information for Determining Airplane Configuration for the
Actions Required by Paragraph (l) of This AD
(1) For Model A330-200 and -300 series airplanes:
(i) Airbus Service Bulletin A330-32-3173, dated December 17,
2003;
(ii) Airbus Service Bulletin A330-32-3173, Revision 01, dated
June 16, 2004;
(iii) Airbus Service Bulletin A330-32-3173, Revision 02, dated
May 11, 2005;
(iv) Airbus Service Bulletin A330-32-3173, Revision 03, dated
March 13, 2006;
(v) Airbus Service Bulletin A330-32-3173, Revision 04, dated
June 12, 2006; or
(vi) Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Service Bulletin A340-32-4212, dated December 17,
2003;
(ii) Airbus Service Bulletin A340-32-4212, Revision 01, dated
June 16, 2004;
(iii) Airbus Service Bulletin A340-32-4212, Revision 02, dated
May 11, 2005;
(iv) Airbus Service Bulletin A340-32-4212, Revision 03, dated
March 13, 2006;
(v) Airbus Service Bulletin A340-32-4212, Revision 04, dated
June 12, 2006; or
[[Page 70452]]
(vi) Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008.
(n) Corrective Action for Ultrasonic Inspection; Repetitive Interval
(1) If the finding of the inspection required by paragraph (l)
of this AD gives an indication of 75 percent or higher of full
screen height (FSH) and between 5 and 7 in time base: Before further
flight, replace the MLG retraction actuator with a new or
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008 (for Model A330-200 and -300 series airplanes);
or Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
(2) If the finding of the inspection required by paragraph (l)
of this AD gives an indication of less than 75 percent FSH and
between 5 and 7 in time base: Repeat the inspection required by
paragraph (l) of this AD thereafter at intervals not to exceed 1,400
flight hours, 250 flight cycles, or 4 months, whichever occurs
first.
(o) One-Time Ultrasonic Inspections of the Full-Length of the Piston
Rod
At the applicable time specified in paragraph (o)(1) or (o)(2)
of this AD: Do a full-length ultrasonic longitudinal and a full-
length circumferential inspection of the chromium-plated area of the
piston rod for cracking, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330-200 and -300 series
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05,
dated September 26, 2008 (for Model A340-200 and -300 series
airplanes).
(1) For MLG retraction actuator piston rods having P/N 114256309
or P/N 114256321 issue 03: Inspect at the later of the times
specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD.
(i) Within 1,750 flight hours, 315 flight cycles, or 5 months
after the effective date of this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has been in service 36
months.
(2) For MLG retraction actuator piston rods having P/N 114256326
issue 01 or P/N 114256321 issue 06: Inspect at the later of the
times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD.
(i) Within 1,750 flight hours, 315 flight cycles, or 5 months
after the effective date of this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has been in service 72
months.
(p) Corrective Action for One-Time Ultrasonic Inspections of the Full-
Length of the Piston Rod
(1) If the finding of the full-length ultrasonic longitudinal
inspection required by paragraph (o) of this AD gives an indication
of 75 percent or higher FSH and between 5 and 7 in time base: Before
further flight, replace the MLG retraction actuator with a new or
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008 (for Model A330-200 and -300 series airplanes);
or Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
(2) If the finding of the full-length ultrasonic circumferential
inspection required by paragraph (o) of this AD gives an indication
of 75 percent or higher FSH and between 7 and 9.5 in time base:
Before further flight, replace the MLG retraction actuator with a
new or serviceable part, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330-200 and -300 series
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05,
dated September 26, 2008 (for Model A340-200 and -300 series
airplanes).
(q) Reporting Requirement
Report the results (regardless of findings) of the detailed
inspection, the fluid drain/seal of the retraction actuator piston
rod, the one-time ultrasonic longitudinal inspection of the piston
rod end, and the one-time full-length ultrasonic longitudinal and
circumferential inspection required by this AD, and the findings of
the actions required by this AD that cause an actuator to be
replaced, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-32-3173, Revision 05, dated September
26, 2008 (for Model A330-200 and -300 series airplanes); or Airbus
Service Bulletin A340-32-4212, Revision 05, dated September 26, 2008
(for Model A340-200 and -300 series airplanes). Submit the report to
Airbus Customer Services Directorate, Attention: SEDCC1 Technical
Data and Documentation Services fax: (+33) 5 61 93 28 06; email:
[email protected]; or via your Airbus resident customer
support office. Submit the report at the applicable time specified
in paragraph (q)(1) or (q)(2) of this AD.
(1) If the actions requiring reporting, as specified in
paragraph (q) of this AD, are done on or after the effective date of
this AD: Submit the report within 90 days after those actions have
been done.
(2) If the actions requiring reporting, as specified in
paragraph (q) of this AD, were done before the effective date of
this AD: Submit the report within 90 days after the effective date
of this AD.
(r) Terminating Actions for Repetitive Detailed Inspections
Accomplishment of the initial drainage of the fluid from the
piston, as required by paragraph (j) of this AD; and the full-length
ultrasonic longitudinal inspection, and the full-length
circumferential inspection, as required by paragraph (o) of this AD;
constitutes terminating action for the repetitive detailed
inspections required by paragraph (g) of this AD, provided no crack
is found during the inspections.
(s) Terminating Modification
Within 48 months after the effective date of this AD: Modify the
left-hand and right-hand MLG retraction actuators, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-32-3180, Revision 05, dated January 27, 2014 (for Model A330-
200 and -300 series airplanes); or Airbus Service Bulletin A340-32-
4222, Revision 04, dated July 30, 2013 (for Model A340-200 and -300
series airplanes). Accomplishment of the modification required by
this paragraph terminates the repetitive requirements of this AD for
the MLG retraction actuator that is modified.
(t) Exception to Re-Identification of the MLG Retraction Actuator
The re-identification of the MLG retraction actuator having P/N
114256002-055, which is described in Airbus Service Bulletin A330-
32-3180, Revision 05, dated January 27, 2014 (for Model A330-200 and
-300 series airplanes); and Airbus Service Bulletin A340-32-4222,
Revision 04, dated July 30, 2013 (for Model A340-200 and -300 series
airplanes); is not required on airplanes that have Airbus
modification 52980 embodied in production.
(u) Optional Parts Installation
Installation of a retraction actuator piston rod having P/N
114256323, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-32-3174, Revision 02, dated September
16, 2005 (for Model A330-200 and -300 series airplanes); or Airbus
Service Bulletin A340-32-4213, Revision 01, dated September 16, 2005
(for Model A340-200 and -300 series airplanes); is an acceptable
method of compliance with the requirements of paragraphs (g), (j),
(l), and (o) of this AD for that installed MLG retraction actuator.
(v) Parts Installation Limitation
As of the effective date of this AD, no person may install a
piston rod having P/N 114256309, P/N 114256321, or P/N 114256326
issue 01 for the MLG retraction actuator on any airplane, unless the
part meets the applicable requirements of this AD at the specified
times and intervals.
(w) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (g), (j), (l), and (o) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraphs (w)(1)(i) through (w)(1)(ix) of
this AD.
(i) Airbus Service Bulletin A330-32-3173, dated December 17,
2003; (for Model A330-200 and -300 series airplanes).
(ii) Airbus Service Bulletin A330-32-3173, Revision 01, dated
June 16, 2004 (for Model A330-200 and -300 series airplanes).
(iii) Airbus Service Bulletin A330-32-3173, Revision 02, dated
May 11, 2005 (for Model A330-200 and -300 series airplanes).
(iv) Airbus Service Bulletin A330-32-3173, Revision 03, dated
March 13, 2006 (for Model A330-200 and -300 series airplanes).
(v) Airbus Service Bulletin A330-32-3173, Revision 04, dated
June 12, 2006 (for Model A330-200 and -300 series airplanes).
(vi) Airbus Service Bulletin A340-32-4212, dated December 17,
2003 (for Model A340-200 and -300 series airplanes).
(vii) Airbus Service Bulletin A340-32-4212, Revision 01, dated
June 16, 2004 (for Model A340-200 and -300 series airplanes).
[[Page 70453]]
(viii) Airbus Service Bulletin A340-32-4212, Revision 02, dated
May 11, 2005; Revision 03, dated March 13, 2006 (for Model A340-200
and -300 series airplanes).
(ix) Airbus Service Bulletin A340-32-4212, Revision 04, dated
June 12, 2006 (for Model A340-200 and -300 series airplanes).
(2) This paragraph provides credit for the actions required by
paragraph (s) of this AD, if the modification was done before the
effective date of this AD using the service information specified in
paragraphs (u)(2)(i) through (u)(2)(iv) of this AD. These service
bulletins are not incorporated by reference in this AD.
(i) Airbus Service Bulletin A330-32-3180, Revision 01, dated
August 15, 2005 for Model A330-200 and -300 series airplanes).
(ii) Airbus Service Bulletin A330-32-3180, Revision 02, dated
April 4, 2007 (for Model A330-200 and -300 series airplanes).
(iii) Airbus Service Bulletin A330-32-3180, Revision 03, dated
January 28, 2011.
(iv) Airbus Service Bulletin A330-32-3180, Revision 04, dated
July 30, 2013.
(v) Airbus Service Bulletin A340-32-4222, Revision 01, dated
August 15, 2005 (for Model A340-200 and -300 series airplanes).
(vi) Airbus Service Bulletin A340-32-4222, Revision 02, dated
April 4, 2007 (for Model A340-200 and -300 series airplanes).
(vii) Airbus Service Bulletin A340-32-4222, Revision 03, dated
January 28, 2011 (for Model A340-200 and -300 series airplanes).
(3) This paragraph provides credit for the actions required by
paragraph (s) of this AD, if the modification was done before the
effective date of this AD using Airbus Service Bulletin A340-32-
4222, dated September 20, 2004; and the re-identification was done
before the effective date of this AD using Airbus Service Bulletin
A340-32-4222, Revision 01, dated August 15, 2005, or Airbus Service
Bulletin A340-32-4222, Revision 02, dated April 4, 2007. These
service bulletins are not incorporated by reference in this AD.
(x) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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 the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (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.
(y) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2011-
0178R1, dated March 6, 2012 (corrected March 7, 2012); and
Airworthiness Directive 2011-0179R1, dated March 6, 2012; for
related information. You may examine the MCAI in the AD docket on
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0132-0003.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (z)(5) and (z)(6) of this AD.
(z) 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
December 31, 2014.
(i) Airbus Service Bulletin A330-32-3173, dated December 17,
2003.
(ii) Airbus Service Bulletin A330-32-3173, Revision 02, dated
May 11, 2005.
(iii) Airbus Service Bulletin A330-32-3173, Revision 03, dated
March 13, 2006.
(iv) Airbus Service Bulletin A330-32-3173, Revision 04, dated
June 12, 2006.
(v) Airbus Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008.
(vi) Airbus Service Bulletin A330-32-3174, Revision 02, dated
September 16, 2005.
(vii) Airbus Service Bulletin A330-32-3180, Revision 05, dated
January 27, 2014.
(viii) Airbus Service Bulletin A340-32-4212, dated December 17,
2003.
(ix) Airbus Service Bulletin A340-32-4212, Revision 02, dated
May 11, 2005.
(x) Airbus Service Bulletin A340-32-4212, Revision 03, dated
March 13, 2006.
(xi) Airbus Service Bulletin A340-32-4212, Revision 04, dated
June 12, 2006.
(xii) Airbus Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008.
(xiii) Airbus Service Bulletin A340-32-4213, Revision 01, dated
September 16, 2005.
(xiv) Airbus Service Bulletin A340-32-4222, Revision 04, dated
July 30, 2013.
(4) The following service information was approved for IBR on
August 19, 2004 (69 FR 46979, August 4, 2004).
(i) Airbus Service Bulletin A330-32-3173, Revision 01, dated
June 16, 2004.
(ii) Airbus Service Bulletin A340-32-4212, Revision 01, dated
June 16, 2004.
(5) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email [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 November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-26986 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P