[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70447-70453]
[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_ADDRESS>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,

1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

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

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

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

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

    (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_ADDRESS>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).

    (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<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information
may be emailed to<EMAIL_ADDRESS>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_ADDRESS>
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<PHONE_NUMBER>, 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


[Federal Register: April 15, 2008 (Volume 73, Number 73)]
[Rules and Regulations]
[Page 20159-20161]
[DOCID:fr15ap08-2]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0304; Directorate Identifier 2008-NE-08-AD;
Amendment 39-15470; AD 2008-06-52]
RIN 2120-AA64

Airworthiness Directives; Thielert Aircraft Engines GmbH (TAE)
Model TAE 125-02-99 Engines

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This document publishes in the Federal Register an amendment
adopting emergency airworthiness directive (AD) 2008-06-52 that was
sent previously to all known U.S. owners and operators of certain TAE
Model TAE 125-02-99 engines. This AD requires, before further flight,
replacing the high-pressure fuel line and installing a high-pressure
fuel line support. This AD results from reports of in-flight engine
shutdown incidents on airplanes equipped with TAE 125-02-99 engines. We
are issuing this AD to prevent an in-flight engine shutdown or engine
fire due to a cracked fuel line.

DATES: This AD becomes effective April 30, 2008 to all persons except
those persons to whom it was made immediately effective by emergency AD
2008-06-52, issued on March 12, 2008, which contained the requirements
of this amendment. The Director of the Federal Register approved the
incorporation by reference of certain publications listed in the
regulations as of April 30, 2008.
    We must receive any comments on this AD by June 16, 2008.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
     Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax:<PHONE_NUMBER>.
    Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D-09350,
Lichtenstein, Germany, telephone: +49-37204-696-0; fax: +49-37204-696-
55; e-mail<EMAIL_ADDRESS>for the service information
identified in this AD.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail
<EMAIL_ADDRESS>telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: On March 12, 2008, the FAA issued emergency
AD 2008-06-52, that applies to TAE model TAE 125-02-99 engines with a
serial number from 02-02-1500 through 02-02-2279. That AD requires,
before further flight, replacing the high-pressure fuel line and
installing a high-pressure fuel line support. That AD resulted from
reports of in-flight engine shutdown incidents on airplanes equipped
with TAE 125-02-99 engines. This was found to be the result of a
cracked high-pressure fuel line between the high-pressure pump and fuel
rail. These cracks were caused by excessive vibration of the fuel line.
This condition, if not corrected, could result in an in-flight engine
shutdown or engine fire due to a cracked fuel line.

Relevant Service Information

    We have reviewed and approved the technical contents of TAE Service
Bulletin (SB) No. TM TAE 125-1005 P1, Revision 1, dated February 11,
2008, and SB No. TM TAE 125-1005 P1, Revision 2, dated March 6, 2008.
Those SBs describe procedures for installing a new high-pressure fuel
line and a high-pressure fuel line bracket.

FAA's Determination and Requirements of This AD

    Since the unsafe condition described is likely to exist or develop
on other engines of the same type design, we issued emergency AD 2008-
06-52 to prevent an in-flight engine shutdown or engine fire due to a
cracked fuel line. This AD requires, before further flight, replacing
the high-pressure fuel line and installing a high-pressure fuel line
support. You must use the service information described previously to
perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause existed to make the AD effective immediately on March 12, 2008,
to all known U.S. owners and operators of certain TAE 125-02-99
engines. These conditions still exist, and we are publishing the AD in
the Federal Register as an amendment to Section 39.13 of part 39 of the
Code of Federal Regulations (14 CFR part 39) to make it effective to
all persons.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2008-0304;
Directorate Identifier 2008-NE-08-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of the
Web site, anyone can find and read the comments in any of our dockets,
including, if provided, the name of the individual who sent the comment
(or signed the comment on behalf of an association, business, labor
union, etc.). You may review the DOT's complete Privacy Act Statement
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone<PHONE_NUMBER>) is the same as
the Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.

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 have 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); and
    3. 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.
    We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (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 adding the following new airworthiness
directive:

2008-06-52 Thielert Aircraft Engines GmbH: Amendment 39-15470.
Docket No. FAA-2008-0304; Directorate Identifier 2008-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April
30, 2008, to all persons except those persons to whom it was made
immediately effective by emergency AD 2008-06-52, issued March 12,
2008, which contained the requirements of this amendment.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Thielert Aircraft Engines GmbH (TAE)
model TAE 125-02-99 engines with a serial number (SN) from 02-02-
1500 through 02-02-2279. These engines are installed on, but not
limited to, Cessna 172 and (Reims-built) F172 series (STC No.
SA01303WI); and Diamond DA42 airplanes.

Unsafe Condition

    (d) This AD results from reports of in-flight engine shutdown
incidents on airplanes equipped with TAE 125-02-99 engines. This was
found to be the result of a cracked high-pressure fuel line between
the high-pressure pump and fuel rail. These cracks were caused by
excessive vibration of the fuel line. We are issuing this AD to
prevent an in-flight engine shutdown or engine fire due to a cracked
fuel line.

Compliance

    (e) You are responsible for having the actions required by this
AD performed before the next flight after the effective date of this
AD, unless the actions have already been done.

Corrective Action

    (f) Before the next flight, install a new high-pressure fuel
line and a high-pressure fuel line bracket using TAE Service
Bulletin (SB) No. TM TAE 125-1005 P1, Revision 2, dated March 6,
2008, or TAE SB No. TM TAE 125-1005 P1, Revision 1, dated February
11, 2008.

Alternative Methods of Compliance

    (g) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (h) We are limiting special flight permits to relocating the
airplane to the next maintenance station, to a maximum flight
duration of 2 hours, and to visual flight rules.

Related Information

    (i) EASA Emergency Airworthiness Directive (EAD) No. 2008-
0056R1-E, dated March 11, 2008, and EASA EAD No. 2008-0027-E, dated
February 13, 2008, also address the subject of this AD.
    (j) Contact Jason Yang, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail<EMAIL_ADDRESS>
telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>, for more information
about this AD.

Material Incorporated by Reference

    (k) You must use the service information specified in Table 1 of
this AD to perform the actions required by this AD. The Director of
the Federal Register approved the incorporation by reference of the
documents listed in Table 1 of this AD in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. You can get a copy from Thielert Aircraft
Engines GmbH, Platanenstrasse 14 D-09350, Lichtenstein, Germany,
telephone: +49-37204-696-0; fax: +49-37204-696-55; e-mail:
<EMAIL_ADDRESS>You may review copies at the FAA, New
England Region, 12 New England Executive Park, Burlington, MA; or 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.

                                      Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
          Service Bulletin No.                     Page            Revision                  Date
----------------------------------------------------------------------------------------------------------------
TM TAE 125-1005 P1, Total Pages--6......  ALL..................            1  February 11, 2008.
TM TAE 125-1005 P1, Total Pages--6......  ALL..................            2  March 6, 2008.
----------------------------------------------------------------------------------------------------------------

    Issued in Burlington, Massachusetts, on April 10, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-8118 Filed 4-14-08; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register: September 8, 2010 (Volume 75, Number 173)]
[Notices]
[Page 54694-54695]
[DOCID:fr08se10-140]

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DEPARTMENT OF TRANSPORTATION

Federal Railroad Administration

Notice of Availability of a Supplemental Draft Environmental
Impact Statement for the DesertXpress High-Speed Passenger Rail Project

AGENCY: Federal Railroad Administration (FRA), United States Department
of Transportation (DOT).

ACTION: Notice.

-----------------------------------------------------------------------

SUMMARY: FRA is issuing this notice to advise the public that a
Supplemental Draft EIS has been prepared for the DesertXpress High-
Speed Passenger Train Project (Project). FRA is the lead agency for the
environmental review process and has prepared the Supplemental Draft
EIS consistent with the provisions of Section 102(2)(c) of the National
Environmental Policy Act (NEPA) of 1969 (42 U.S.C. 4321 et seq.), the
Counsel of Environmental Quality (CEQ) regulations implementing NEPA
(40 CFR parts 1500 et seq.) and FRA's Procedures for Considering
Environmental Impacts (64 FR 28545; May 26, 1999).
    DesertXpress Enterprises Inc., the Project proponent, proposes to
construct and operate a fully grade-separated, dedicated double-track,
passenger-only railroad along an approximately 200-mile corridor, from
Victorville, CA, to Las Vegas, NV. After publication of the Draft EIS
and in response to substantive comments submitted by interested
agencies and the public, the Project proponent proposed several project
modifications and additions. After reviewing the proposed project
modifications and additions, FRA determined a Supplemental Draft EIS
describing the potential environmental effects of the modifications and
additions was necessary to fulfill its responsibility under NEPA.

DATES: Written comments on the Supplemental Draft EIS for the
DesertXpress Project should be provided to FRA on or before October 18
2010. Public hearings are scheduled on October 13 and October 14, 2010,
at the times and dates listed in the Addresses Section below in Las
Vegas, NV and Barstow, CA.

ADDRESSES: Written comments on the Supplemental Draft EIS should be
sent to Ms. Wendy Messenger, Environmental Protection Specialist,
Office of Railroad Policy and Development, ATTN: DesertXpress EIS,
Federal Railroad Administration, U.S. Department of Transportation,
1200 New Jersey Avenue, SE., MS-20, Washington, DC 20590 or via e-mail
with the subject line DesertXpress EIS to<EMAIL_ADDRESS>
Comments may also be provided orally or in writing at the public
hearings scheduled at the following locations:
     Las Vegas, NV, Wednesday, October 13, 2010, 5:30 to 8 p.
m., Hampton Inn Tropicana, SW. Event Center B, 4975 Dean Martin Drive,
Las Vegas, NV; and
     Barstow, CA, Thursday, October 14, 2010, 5:30 to 8 p.m.,
Lenwood Hampton Inn, Jackrabbit Room 1, 2710 Lenwood Road, Barstow, CA.

FOR FURTHER INFORMATION CONTACT: Ms. Wendy Messenger, Environmental
Protection Specialist, Office of Railroad Policy and Development,
Federal Railroad Administration, U.S. Department of Transportation,
1200 New Jersey Avenue, SE., MS-20, Washington, DC 20590 (telephone:
202-493-6396).

SUPPLEMENTARY INFORMATION: Following the March 18, 2009 publication of
the Draft EIS on the Project, several project modifications and
additions were proposed to address substantive comments received during
public and agency review of the Draft EIS and to reduce or avoid
significant environmental effects. After evaluating the proposed
project modifications and additions, FRA determined, pursuant to 40 CFR
1502.9, that it was necessary to prepare a supplement to the Draft EIS
analyzing the potential environmental impacts that might result from
those modifications and additions. Therefore, in compliance with CEQ's
regulations and FRA's Procedures for Considering Environmental Impacts,
FRA, in cooperation with the Bureau of Land Management (BLM), Surface
Transportation Board (STB), Federal Highway Administration (FHWA), and
the National Park Service (NPS), and with the added participation of
the California Department of Transportation (Caltrans) and the Nevada
Department of Transportation (NDOT), prepared a Supplemental Draft EIS.
    The Project would involve the construction and operation of an
interstate high-speed passenger train system between Victorville, CA
and Las Vegas, NV, along an approximately 200-mile corridor. The
project proponent proposes to construct nearly the entire fully grade-
separated, dedicated double-track, passenger-only railroad either in
the median of, or immediately alongside, Interstate-15 (I-15).
    The proposed project modifications and additions do not in any way
change the underlying purpose of, or need for, the project. The need
for high-speed passenger rail service arises from several factors,
including high and increasing travel demand with limited increases in
capacity on I-15, constraints to the expansion of air travel, and
frequent highway vehicle accidents on the I-15 corridor. The
DesertXpress high-speed passenger train is intended to provide reliable
and safe passenger rail transportation using proven high-speed rail
technology that would be a convenient alternative to automobile travel
on I-15 or air travel to and from Las Vegas, and that would add
transportation capacity along the I-15 corridor.
    Consistent with the requirements of NEPA, the Supplemental Draft
EIS evaluates the environmental effects of the proposed modifications
and additions, which include a new Victorville passenger station option
at Dale Evans Parkway, a rail alignment through the Barstow area
following the I-15 freeway corridor from Lenwood through Yermo, CA, a
new rail alignment through the Clark Mountains near the Mojave National
Preserve, new sites for maintenance and operation facilities in
unincorporated Clark County, NV, relocation of portions of the rail
alignment in metropolitan Las Vegas from the immediate I-15 corridor to
the Industrial Road/Dean Martin Drive corridor, and several alignment
modifications to reduce or avoid environmental impacts, improve
operating characteristics, or avoid conflicts with other planned
projects.
    Copies of both the Supplemental Draft EIS and Draft EIS are
available online at FRA's Web site: http://www.fra.dot.gov; they are
also available for viewing at the following locations near the planned
rail system:
     Victorville City Library, 15011 Circle Drive, Victorville,
CA 92395;
     Barstow Library, 304 East Buena Vista, Barstow, CA 92311;
     Clark County Library, 1401 E. Flamingo Road, Las Vegas, NV
89119; and
     Las Vegas Library, 833 Las Vegas Blvd. N., Las Vegas, NV
80101.

    Issued in Washington, DC, on September 1, 2010.
Mark E. Yachmetz,
Associate Administrator for Railroad Policy & Development.
[FR Doc. 2010-22246 Filed 9-7-10; 8:45 am]
BILLING CODE 4910-06-P


[Federal Register: August 12, 2009 (Volume 74, Number 154)]
[Notices]
[Page 40576-40577]
[DOCID:fr12au09-50]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CP09-451-000]

Tennessee Gas Pipeline Company; Notice of Application

August 5, 2009.
    Take notice that on July 31, 2009, Tennessee Gas Pipeline Company
(Tennessee), 1001 Louisiana Street, Houston, Texas 77002, filed in
Docket No. CP09-451-000, an application

pursuant to Section 7(b) of the Natural Gas Act (NGA) and Part 157 of
the Commission's regulations, requesting authorization to abandon
certain inactive supply pipelines, associated meters, and appurtenances
located in the West Delta area in Federal offshore waters and in State
waters in Plaquemines Parish, Louisiana, all as more fully set forth in
the application which is on file with the Commission and open to public
inspection. This filing may also be viewed on the Commission's Web site
at http://www.ferc.gov using the ``eLibrary'' link. Enter the docket
number, excluding the last three digits, in the docket number field to
access the document. For assistance, call<PHONE_NUMBER> or TTY, (202)
502-8659.
    Any questions regarding this application should be directed to
Susan T. Halbach, Senior Counsel, Tennessee Gas Pipeline Company, 1001
Louisiana Street, Houston, Texas 77002, or by calling<PHONE_NUMBER>
(telephone) or<PHONE_NUMBER> (fax<EMAIL_ADDRESS>Kathy
Cash, Principal Analyst, Rates and Regulatory Affairs, Tennessee Gas
Pipeline Company, 1001 Louisiana Street, Houston, Texas 77002, or by
calling<PHONE_NUMBER> (telephone) or<PHONE_NUMBER> (fax),
<EMAIL_ADDRESS>or to Thomas G. Joyce, Manager, Certificates,
Tennessee Gas Pipeline Company, 1001 Louisiana Street, Houston, Texas
77002, or by calling<PHONE_NUMBER> (telephone) or<PHONE_NUMBER>
(fax<EMAIL_ADDRESS>    Pursuant to Section 157.9 of the Commission's rules, 18 CFR 157.9,
within 90 days of this Notice the Commission staff will either:
complete its environmental assessment (EA) and place it into the
Commission's public record (eLibrary) for this proceeding, or issue a
Notice of Schedule for Environmental Review. If a Notice of Schedule
for Environmental Review is issued, it will indicate, among other
milestones, the anticipated date for the Commission staff's issuance of
the final environmental impact statement (FEIS) or EA for this
proposal. The filing of the EA in the Commission's public record for
this proceeding or the issuance of a Notice of Schedule for
Environmental Review will serve to notify Federal and State agencies of
the timing for the completion of all necessary reviews, and the
subsequent need to complete all Federal authorizations within 90 days
of the date of issuance of the Commission staff's FEIS or EA.
    There are two ways to become involved in the Commission's review of
this project. First, any person wishing to obtain legal status by
becoming a party to the proceedings for this project should, on or
before the comment date stated below, file with the Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426, a
motion to intervene in accordance with the requirements of the
Commission's Rules of Practice and Procedure (18 CFR 385.214 or
385.211) and the Regulations under the NGA (18 CFR 157.10). A person
obtaining party status will be placed on the service list maintained by
the Secretary of the Commission and will receive copies of all
documents filed by the applicant and by all other parties. A party must
submit 14 copies of filings made with the Commission and must mail a
copy to the applicant and to every other party in the proceeding. Only
parties to the proceeding can ask for court review of Commission orders
in the proceeding.
    However, a person does not have to intervene in order to have
comments considered. The second way to participate is by filing with
the Secretary of the Commission, as soon as possible, an original and
two copies of comments in support of or in opposition to this project.
The Commission will consider these comments in determining the
appropriate action to be taken, but the filing of a comment alone will
not serve to make the filer a party to the proceeding. The Commission's
rules require that persons filing comments in opposition to the project
provide copies of their protests only to the party or parties directly
involved in the protest.
    Persons who wish to comment only on the environmental review of
this project should submit an original and two copies of their comments
to the Secretary of the Commission. Environmental commenters will be
placed on the Commission's environmental mailing list, will receive
copies of the environmental documents, and will be notified of meetings
associated with the Commission's environmental review process.
Environmental commenters will not be required to serve copies of filed
documents on all other parties. However, the non-party commenters will
not receive copies of all documents filed by other parties or issued by
the Commission (except for the mailing of environmental documents
issued by the Commission) and will not have the right to seek court
review of the Commission's final order.
    Motions to intervene, protests and comments may be filed
electronically via the Internet in lieu of paper; see, 18 CFR
385.2001(a)(1)(iii) and the instructions on the Commission's Web site
under the ``e-Filing'' link. The Commission strongly encourages
electronic filings.
    Comment Date: August 26, 2009.

Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. E9-19268 Filed 8-11-09; 8:45 am]

BILLING CODE 6717-01-P