Airworthiness Directives; Airbus Airplanes, 9374-9379 [2016-03699]
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
(m) Terminating Action
Accomplishment of the actions required by
paragraphs (k) and (l) of this AD terminate
the requirements of paragraphs (g) and (i) of
this AD.
(n) Parts Installation Prohibition
As of the effective date of this AD, no
person may install or reinstall any barrel nut
P/N SL4081C14SP1 at the forward engine
mount assembly on any airplane, and only P/
N SL4750NA may be installed.
(o) New Exceptions to Service Information
Specifications
(1) Where Boeing Special Attention Service
Bulletin 747–71–2332, Revision 1, dated May
28, 2015, specifies a compliance time ‘‘after
the original issue date of this service
bulletin,’’ this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(2) Where Boeing Special Attention Service
Bulletin 747–71–2332, Revision 1, dated May
28, 2015, specifies to contact Boeing for
appropriate action: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (r) of this AD.
(p) No Alternative Actions or Intervals
After the maintenance or inspection
program has been revised as required by
paragraph (l) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (r) of this
AD.
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(q) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (k) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Special
Attention Service Bulletin 747–71–2332,
dated May 30, 2014, which is not
incorporated by reference in this AD.
(r) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (s)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
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been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2013–24–12
are approved as AMOCs for the
corresponding provisions of this AD.
(5) Except as required by paragraph (o)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (r)(5)(i) and (r)(5)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(s) Related Information
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6428; fax: 425–917–6590; email:
Nathan.p.weigand@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone: 206–
544–5000, extension 1; fax: 206–766–5680;
Internet https://www.myboeingfleet.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.
Issued in Renton, Washington, on February
15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03690 Filed 2–24–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3701; Directorate
Identifier 2015–NM–015–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede
Airworthiness Directive (AD) 2013–25–
08, for all Airbus Model A330–200,
–200 Freighter, and –300 series
airplanes; and Model A340–200 and
–300 series airplanes. AD 2013–25–08
currently requires a repetitive
inspection program on certain check
valves in the hydraulic systems that
includes, among other things,
inspections for lock wire presence and
integrity, traces of seepage or black
deposits, proper torque, alignment of
the check valve and manifold,
installation of new lock wire, and
corrective actions if needed. Since we
issued AD 2013–25–08, Airbus has
developed an improved check valve.
This proposed AD would add airplanes
to the applicability, and require
modifying the green, blue and yellow
high pressure hydraulic manifolds by
replacing certain check valves with
improved check valves, which would
terminate the repetitive inspections
required by this proposed AD. We are
proposing this AD to detect and correct
hydraulic check valve loosening;
loosened valves could result in
hydraulic leaks, possibly leading to the
loss of all three hydraulic systems and
consequent loss of control of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by April 11, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
DATES:
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
3701; 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 proposed 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. Comments will
be available in the AD docket shortly
after receipt.
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 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–3701; Directorate Identifier
2015–NM–015–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On November 26, 2013, we issued AD
2013–25–08, Amendment 39–17704 (78
FR 78694, December 27, 2013) (‘‘AD
2013–25–08’’). AD 2013–25–08 requires
actions intended to address an unsafe
condition on all Airbus Model A330–
200 and –300 series airplanes; and
Model A340–200 and –300 series
airplanes.
Since we issued AD 2013–25–08,
which superseded AD 2009–24–09
Amendment 39–16068 (74 FR 62208,
November 27, 2009), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Union, has
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issued EASA Airworthiness Directive
2015–0009, dated January 16, 2015
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition. The MCAI states:
An A330 operator experienced a Yellow
hydraulic circuit low level due to a loose
check valve, Part Number (P/N) CAR401.
During the inspection on the other two
hydraulic systems, the other three check
valves P/N CAR401 were also found to be
loose with their lock wire broken in two
instances. Airbus A340 aeroplanes are also
equipped with P/N CAR401 high pressure
manifold check valves.
Additional cases of P/N CAR401 check valve
loosening have been reported on aeroplanes
having accumulated more than 1,000 flight
cycles (FC). The check valve fitted on the
Yellow hydraulic system is more affected,
due to additional system cycles induced by
cargo door operation.
This condition, if not detected and corrected,
could result in hydraulic leaks, possibly
leading to the loss of all three hydraulic
systems and consequent loss of control of the
aeroplane.
To address this unsafe condition, EASA
issued Emergency AD 2009–0223–E (https://
ad.easa.europa.eu/blob/easa_ad_2009_
0223E_superseded.pdf/EAD_2009-0223-E_1)
[which corresponds to FAA AD 2009–24–09,
Amendment 39–16068 (74 FR 62208,
November 27, 2009)] to require an inspection
programme to detect any check valve
loosening and, if necessary, to apply the
applicable corrective actions.
EASA AD 2010–0145 (https://
ad.easa.europa.eu/blob/easa_ad_
2010_0145_Superseded.pdf/AD_2010-0145
_1), which superseded EASA EAD 2009–
0223–E retaining its requirements, was
issued to expand the applicability to the
newly certified models A330–223F and
A330–243F.
Prompted by further reported in-service
events of check valve P/N CAR401 loosening
before reaching the threshold of 700 FC,
EASA AD 2011–0139 (https://
ad.easa.europa.eu/blob/easa_ad_
2011_0139_superseded.pdf/AD_2011-0139
_1), which superseded EASA AD 2010–0145,
retaining its requirements, was issued to:
—extend the requirement to identify the P/
N CAR401 check valves to all aeroplanes,
and
—reduce the inspection threshold for
aeroplanes fitted with check valve P/N
CAR401, either installed in production
through Airbus modification 54491, or
installed in service through Airbus Service
Bulletin (SB) A330–29–3101 or Airbus SB
A340–29–4078.
EASA AD 2012–0070 (https://
ad.easa.europa.eu/blob/easa_ad_2012_0070_
Correction_superseded.pdf/AD_2012-0070
_1), which superseded EASA AD 2011–0139,
retaining its requirements, was issued to
require an increased torque value of the
check valve tightening and High Pressure
(HP) manifold re-identification.
Since EASA AD 2012–0070 was issued,
additional in-service events have been
reported on aeroplanes fitted with check
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9375
valves on which the increased torque value
had been applied. Based on those events, it
has been concluded that the action to retorque the check valves with an increased
value is not a satisfactory terminating action
for addressing the issue of those check
valves.
To address that, EASA issued AD 2012–0244,
which partially retained the requirements of
EASA AD 2012–0070, which was
superseded. Additionally, for aeroplanes
equipped with P/N CAR401 on which the
increased torque value had been applied,
EASA AD 2012–0244 required repetitive
inspections of the check valves and HP
manifolds. Finally, EASA AD 2012–0244 also
required application of a lower torque value
when a check valve P/N CAR401 is installed
on an aeroplane.
Note: The reporting and the torque value
increase requirements for check valves P/N
CAR401 of EASA AD 2012–0070 were no
longer part of EASA AD 2012–0244.
EASA AD was revised to clarify which
actions are required for P/N CAR401 check
valves, depending on applied (or not) torque
value.
Since EASA AD 2012–0244R1 (https://
ad.easa.europa.eu/blob/easa_ad_
2012_0244_R1_superseded.pdf/AD_20120244R1_1) was issued, Airbus developed an
improved check valve P/N CAR402, which is
embodied in production through Airbus
modification 203972, and in service through
associated Airbus SB A330–29–3125, or
Airbus SB A340–29–4096, as applicable to
aeroplane type. In addition, these SBs
provide instructions about the torque value
(between 230 and 250 Nm) and reidentification of HP manifolds after check
valve P/N CAR402 installation.
For the reasons described above, this [EASA]
AD retains the requirements of EASA AD
2012–0244R1, which is superseded, and
requires the installation of check valves P/N
CAR402 as terminating action to the
repetitive inspections [and adds airplanes to
the applicability].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
3701.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A330–29–3125, Revision 01, including
Appendixes 01 and 02, dated July 30,
2015; and Service Bulletin A340–29–
4096, Revision 01, including
Appendixes 01 and 02, dated July 30,
2015. This service information describes
procedures for modifying the green,
blue, and yellow high pressure
hydraulic manifolds by replacing each
check valve having part number (P/N)
CAR401 with an improved check valve
having P/N CAR402. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
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Explanation of a Certain Alternative
Method of Compliance (AMOC)
Paragraph (t)(1)(iii) of this proposed
AD states that AMOC ANM–116–14–
429 is not approved as an AMOC for the
corresponding provisions of this AD.
This AMOC defines a terminating action
when Airbus Modification 203972 is
introduced in production or when the
Airbus Service Bulletin A330–29–3125,
dated August 8, 2014, is embodied in
service. This proposed AD will exclude
from the applicability airplanes with
Airbus Modification 203972 and will
mandate actions in accordance with
Airbus Service Bulletin A330–29–3125,
Revision 01, including Appendixes 01
and 02, dated July 30, 2015.
Costs of Compliance
We estimate that this proposed AD
affects 88 airplanes of U.S. registry.
The actions required by AD 2013–25–
08, and retained in this proposed AD
take about 10 work-hours per product,
at an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the actions that are
required by AD 2013–25–08 is $850 per
product.
We also estimate that it would take
about 32 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $239,360, or $2,720 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD. 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 proposed 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 available
costs in our cost estimate.
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Authority for This Rulemaking
§ 39.13
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–25–08, Amendment 39–17704 (78
FR 78694, December 27, 2013), and
adding the following new AD:
Airbus: Docket No. FAA–2016–3701;
Directorate Identifier 2015–NM–015–AD.
(a) Comments Due Date
We must receive comments by April 11,
2016.
(b) Affected ADs
This AD replaces AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013).
(c) Applicability
This AD applies to Airbus airplanes,
certificated in any category, as identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes;
all manufacturer serial numbers except those
on which Airbus modification 203972 has
been embodied in production.
(2) Model A340–211, –212, –213, –311,
–312, and –313 airplanes; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 29, Hydraulic power.
(e) Reason
This AD was prompted by multiple reports
of hydraulic line check valves loosening. We
are issuing this AD to detect and correct
hydraulic check valve loosening, which
could result in hydraulic leaks, possibly
leading to the loss of all three hydraulic
systems and consequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013), with no changes. Except
for Model A330–223F and A330–243F
airplanes: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD.
(1) For airplanes that do not have Airbus
Modification 54491 embodied in production,
or Airbus Service Bulletin A330–29–3101 or
Airbus Service Bulletin A340–29–4078
embodied in service: Within 100 flight cycles
or 28 days after December 14, 2009 (the
effective date of AD 2009–24–09,
Amendment 39–16068 (74 FR 62208,
November 27, 2009)), whichever occurs first,
inspect the check valves on the blue, green,
and yellow hydraulic systems to identify
their part numbers (P/Ns), in accordance
with the instructions of Airbus All Operators
Telex (AOT) A330–29A3111, Revision 1,
dated October 8, 2009 (for Model A330–200
and –300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
(for Model A340–200 and –300 series
airplanes). Accomplishment of the inspection
required by paragraph (h) of this AD
terminates the requirements of this
paragraph.
(i) If check valves having P/N CAR401 are
installed on all three hydraulic systems,
before further flight, do the actions specified
in paragraph (g)(2)(i) of this AD. After
accomplishing the actions required by
paragraph (g)(2)(i) of this AD, do the actions
specified in paragraphs (g)(2)(ii) and
(g)(2)(iii) of this AD at the applicable
compliance times specified in those
paragraphs. Accomplishment of the
inspection required by paragraph (i) of this
AD terminates the requirements of this
paragraph.
(ii) If check valves having P/N CAR401 are
not installed on all three hydraulic systems,
no further action is required by this
paragraph until any check valve having P/N
CAR400 is replaced with a check valve
having P/N CAR401. If any check valve
having P/N CAR400 is replaced by a check
valve having P/N CAR401, before further
flight, do the inspection specified in
paragraph (g)(1) of this AD to determine if all
three hydraulic systems are equipped with
check valves having P/N CAR401.
Accomplishment of the inspection required
by paragraph (h) of this AD terminates the
requirements of this paragraph.
(2) For airplanes on which Airbus
Modification 54491 was embodied in
production, or Airbus Service Bulletin A330–
29–3101; or Airbus Service Bulletin A340–
29–4078 was embodied in service, do the
actions specified in paragraphs (g)(2)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Except as required by paragraph (g)(1)(i)
of this AD, at the applicable times specified
in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of
this AD, as applicable: Do the inspection
program (detailed inspection of the lock wire
for presence and integrity, a detailed
inspection for traces of seepage or black
deposits, and an inspection for proper
torque) on yellow and blue high pressure
manifolds, install new lock wires, and do all
applicable corrective actions, in accordance
with the instructions of paragraph 4.1.1 of
Airbus AOT A330–29A3111, Revision 1,
dated October 8, 2009 (for Model A330–200
and –300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Airbus Model A340–200 and –300 series
airplanes). Do all applicable corrective
actions before further flight. Accomplishment
of the inspection required by paragraph (h)(1)
of this AD terminates the requirements of this
paragraph.
(A) For airplanes on which Airbus
Modification 54491 has been embodied in
production: At the later of the times specified
in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2)
of this AD.
(1) Before the accumulation of 1,000 total
flight cycles since first flight but no earlier
than the accumulation of 700 total flight
cycles since first flight.
(2) Within 100 flight cycles or 28 days after
December 14, 2009 (the effective date of AD
2009–24–09, Amendment 39–16068 (74 FR
62208, November 27, 2009)), whichever
occurs first.
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(B) For airplanes on which Airbus Service
Bulletin A330–29–3101 or A340–29–4078
was embodied in service: At the later of the
times specified in paragraphs (g)(2)(i)(B)(1)
and (g)(2)(i)(B)(2) of this AD.
(1) Within 1,000 flight cycles since the
embodiment of Airbus Service Bulletin
A330–29–3101 or A340–29–4078 but no
earlier than 700 flight cycles after the
embodiment of Airbus Service Bulletin
A330–29–3101 or A340–29–4078.
(2) Within 100 flight cycles or 28 days after
December 14, 2009 (the effective date of AD
2009–24–09, Amendment 39–16068 (74 FR
62208, November 27, 2009)), whichever
occurs first.
(ii) Within 900 flight hours after
accomplishment of paragraph (g)(2)(i) of this
AD, do the inspection program (detailed
inspection of the lock wire for presence and
integrity, a detailed inspection for traces of
seepage or black deposits, and an inspection
for proper torque) and install a new lock wire
on the green high pressure manifold; and do
an inspection (detailed inspection for traces
of seepage or black deposits, and detailed
inspection to determine alignment of the
check valve and manifold) on the yellow and
blue high pressure manifolds, and do all
applicable corrective actions; in accordance
with the instructions of paragraph 4.1.2 of
Airbus AOT A330–29A3111, Revision 1,
dated October 8, 2009 (for Model A330–200
and –300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Model A340–200 and –300 series
airplanes). Do all applicable corrective
actions before further flight. Accomplishment
of the inspection program required by
paragraph (i) of this AD terminates the
requirements of this paragraph.
(iii) Within 900 flight hours after
accomplishment of paragraph (g)(2)(ii) of this
AD, and thereafter at intervals not to exceed
900 flight hours, do the inspection program
(detailed inspection for traces of seepage or
black deposits, and detailed inspection to
determine alignment of the check valve and
manifold) on the green, yellow, and blue high
pressure manifolds, and do all applicable
corrective actions, in accordance with the
instructions of paragraph 4.1.3 of Airbus
AOT A330–29A3111, Revision 1, dated
October 8, 2009 (for Model A330–200 and
–300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Model A340–200 and –300 series
airplanes). Do all applicable corrective
actions before further flight. Accomplishment
of the inspection program required by
paragraph (i) of this AD terminates the
requirements of this paragraph.
(h) Retained Inspection, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013, with no changes. For
airplanes equipped with check valves having
P/N CAR400; and for airplanes equipped
with check valves having P/N CAR401,
except for airplanes on which Airbus
Modification 201384 has been embodied
during production, or on which Airbus
Service Bulletin A330–29–3119 (for Model
A330–200, –200F, and –300 series airplanes)
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
9377
or Airbus Service Bulletin A340–29–4091
(for Model A340–200 and –300 series
airplanes) has been embodied in service:
Within 900 flight hours after January 31,
2014 (the effective date of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013)), inspect the check
valves on the blue, green, and yellow
hydraulic systems to identify their part
numbers, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–29–3111, Revision 02,
dated June 23, 2011 (for Model A330–200,
–200F and –300 series airplanes); or Airbus
Service Bulletin A340–29–4086, Revision 02,
dated June 23, 2011 (for Model A340–200
and –300 series airplanes). Accomplishment
of the actions required by this paragraph
terminates the requirements specified in
paragraphs (g)(1) and (g)(1)(ii) of this AD.
(1) If check valves having P/N CAR401 are
installed on all three hydraulic systems:
Before further flight, do the inspection
program (detailed inspection for red mark
presence and alignment integrity of the check
valve and manifold, a detailed inspection for
traces of seepage or black deposits, and an
inspection for proper torque) on yellow and
blue high pressure manifolds, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–29–3111,
Revision 02, dated June 23, 2011 (for Model
A330–200, –200F, and –300 series airplanes);
or Airbus Service Bulletin A340–29–4086,
Revision 02, dated June 23, 2011 (for Model
A340–200 and –300 series airplanes).
Accomplishment of the actions required by
this paragraph terminates the requirements
specified in paragraph (g)(2)(i) of this AD.
(2) If check valves having P/N CAR401 are
not installed on all three hydraulic systems,
no further action is required by this
paragraph until any check valve having P/N
CAR400 is replaced with a check valve
having P/N CAR401. If any check valve
having P/N CAR400 is replaced by a check
valve having P/N CAR401: Before further
flight after such replacement, do the actions
specified in paragraph (h) of this AD, to
determine if all three hydraulic systems are
equipped with check valves having P/N
CAR401. If check valves having P/N CAR401
are installed on all three hydraulic systems:
Before further flight, do the actions specified
in paragraphs (h)(1) and (i) of this AD.
(i) Retained Repetitive Inspection Program
and Corrective Actions, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2013–25–08, Amendment
39–17704 (78 FR 78694, December 27, 2013),
with no changes. Within 900 flight hours
after accomplishment of paragraph (h)(1) of
this AD, do the inspection program (detailed
inspection for red mark presence and
alignment integrity of the check valve and
manifold, a detailed inspection for traces of
seepage or black deposits, and an inspection
for proper torque) on the green, yellow, and
blue system check valves, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–29–3111,
Revision 02, dated June 23, 2011 (for Model
A330–200, –200F, and –300 series airplanes);
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
or Airbus Service Bulletin A340–29–4086,
Revision 02, dated June 23, 2011 (for Model
A340–200 and –300 series airplanes). Do all
applicable corrective actions before further
flight. Repeat the inspection program
thereafter at intervals not to exceed 900 flight
hours. Accomplishment of the actions
required by this paragraph terminates the
requirements specified in paragraphs (g)(1)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD.
(j) Retained Repetitive Inspection for Certain
Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2013–25–08, Amendment
39–17704 (78 FR 78694, December 27, 2013),
with no changes. For airplanes equipped
with check valves having P/N CAR401 and
on which Airbus Modification 201384 has
been embodied during production, or on
which Airbus Service Bulletin A330–29–
3119 (for Model A330–200, –200F, and –300
series airplanes); or Airbus Service Bulletin
A340–29–4091 (for Model A340–200 and
–300 series airplanes) has been embodied in
service: Within 1,000 flight hours after
January 31, 2014 (the effective date of AD
2013–25–08, Amendment 39–17704 (78 FR
78694, December 27, 2013)), do a general
visual inspection of the green, yellow, and
blue high pressure manifolds and check
valves having P/N CAR401 for any sign of
rotation of the check valve head, and for any
signs of hydraulic fluid leakage or seepage
(including black deposits), in accordance
with the instructions of Airbus Alert
Operators Transmission A29L001–12, dated
October 11, 2012. Repeat the inspection
thereafter at interval not to exceed 900 flight
hours.
(k) Retained Corrective Action for Certain
Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013), with no changes. If,
during any inspection required by paragraph
(j) of this AD, any sign of rotation of the
check valve head is found, or any sign of
hydraulic fluid leakage or seepage (including
black deposits) is found: Before further flight,
do all applicable corrective actions, in
accordance with the instructions of Airbus
Alert Operators Transmission A29L001–12,
dated October 11, 2012.
rmajette on DSK2TPTVN1PROD with PROPOSALS
(l) Retained Provisions Regarding
Terminating Action, With No Changes
This paragraph restates the provisions of
paragraph (l) of AD 2013–25–08, Amendment
39–17704 (78 FR 78694, December 27, 2013),
with no changes. Accomplishment of the
corrective actions required by this AD does
not constitute terminating action for the
repetitive inspections required by this AD.
(m) Retained Replacement Check Valve
Torque Value, With No Changes
This paragraph restates the requirements of
paragraph (m) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013), with no changes. As of
January 31, 2014 (the effective date of AD
2013–25–08, Amendment 39–17704 (78 FR
78694, December 27, 2013)), at each
replacement of a check valve with a check
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13:27 Feb 24, 2016
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valve having P/N CAR401, apply a torque of
141 to 143 newton meter (N.m) (103.98 to
105.45 pounds-foot (lbf.ft)) during
installation.
(n) Retained Credit for Previous Actions,
With No Changes
This paragraph restates the provisions of
paragraph (n) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013), with no changes.
(1) This paragraph provides credit for
actions required by paragraph (g)(2)(i) of this
AD, if those actions were performed before
December 14, 2009 (the effective date of AD
2009–24–09, Amendment 39–16068 (74 FR
62208, November 27, 2009)), using the
applicable service information specified in
paragraphs (n)(1)(i) and (n)(1)(ii) of this AD.
(i) Airbus AOT A330–29A3111, dated
September 2, 2009 (for Model A330–200 and
-300 series airplanes), which is not
incorporated by reference in this AD.
(ii) Airbus AOT A340–29A4086, dated
September 2, 2009 (for Model A340–200 and
-300 series airplanes), which is not
incorporated by reference in this AD.
(2) This paragraph provides credit for
actions required by paragraph (h) of this AD,
if those actions were performed before
January 31, 2014 (the effective date of AD
2013–25–08, Amendment 39–17704 (78 FR
78694, December 27, 2013)) using the
applicable service information specified in
paragraphs (n)(2)(i) through (n)(2)(iv) of this
AD.
(i) Airbus AOT A330–29A3111, dated
September 2, 2009 (for Model A330–200 and
–300 series airplanes), which is not
incorporated by reference in this AD.
(ii) Airbus AOT A330–29A3111, Revision
1, dated October 8, 2009 (for Model A330–
200 and –300 series airplanes).
(iii) Airbus AOT A340–29A4086, dated
September 2, 2009, (for Model A340–200 and
–300 series airplanes), which is not
incorporated by reference in this AD.
(iv) Airbus AOT A340–29A4086, Revision
1, dated October 8, 2009 (for Model A340–
200 and –300 series airplanes).
(o) Retained Provisions for Reporting, With
No Changes
This paragraph restates the provisions of
paragraph (o) of AD 2013–25–08,
Amendment 39–17704 (78 FR 78694,
December 27, 2013), with no changes.
Although the service information specified in
paragraphs (o)(1) through (o)(5) of this AD
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
(1) Airbus Alert Operators Transmission
A29L001–12, dated October 11, 2012.
(2) Airbus Mandatory Service Bulletin
A330–29–3111, Revision 02, dated June 23,
2011.
(3) Airbus Mandatory Service Bulletin
A340–29–4086, Revision 02, dated June 23,
2011.
(4) Airbus AOT A330–29A3111, Revision
1, dated October 8, 2009.
(5) Airbus AOT A340–29A4086, Revision
1, dated October 8, 2009.
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
(p) New Requirement of This AD: Modify
Hydraulic Systems
Within 36 months after the effective date
of this AD, modify the green, blue, and
yellow high pressure hydraulic manifolds by
replacing each check valve having P/N
CAR401 with an improved check valve
having P/N CAR402, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–29–3125, Revision 01,
including Appendixes 01 and 02, dated July
30, 2015; or Airbus Service Bulletin A340–
29–4096, Revision 01, including Appendixes
01 and 02, dated July 30, 2015; as applicable.
(q) New Requirement of This AD: Repetitive
Inspection Terminating Action
Modification of an airplane, as required by
paragraph (p) of this AD, constitutes
terminating action for the repetitive
inspections required by this AD.
(r) New Requirement of This AD: Parts
Installation Limitations
(1) For an airplane that, as of the effective
date of this AD, has a check valve having P/
N CAR401 installed, after modification of an
airplane as required by paragraph (p) of this
AD, no person may install a check valve
having P/N CAR401, on that airplane.
(2) For an airplane that does not have a
check valve having P/N CAR401 installed, as
of the effective date of this AD, no person
may install a check valve having P/N
CAR401, on that airplane.
(s) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (p) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A330–29–3125, dated August 8, 2014; or
Airbus Service Bulletin A340–29–4096,
dated August 8, 2014; as applicable; which
are not incorporated by reference in this AD.
(t) 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: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOC ANM–116–14–180 R1, dated
February 21, 2014, is approved as an AMOC
for the corresponding provisions of this AD.
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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
(iii) AMOC ANM–116–14–429, dated
September 25, 2014, is not approved as an
AMOC for the corresponding provisions of
this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the 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) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
rmajette on DSK2TPTVN1PROD with PROPOSALS
(u) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0009, dated
January 16, 2015, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–3701.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at 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
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com.
(3) 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
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on February
15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03699 Filed 2–24–16; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
13:27 Feb 24, 2016
Jkt 238001
DEPARTMENT OF THE TREASURY
Internal Revenue Service
[REG–150349–12]
RIN 1545–BL39
Amendments to the Low-Income
Housing Credit Compliance-Monitoring
Regulations
Internal Revenue Service (IRS),
Treasury.
ACTION: Notice of proposed rulemaking
by cross-reference to temporary
regulations.
AGENCY:
In the Rules and Regulations
section of this issue of the Federal
Register, the IRS is issuing final and
temporary regulations concerning the
compliance-monitoring duties of a State
or local housing credit agency (Agency)
for purposes of the low-income housing
credit. The final and temporary
regulations revise and clarify certain
rules relating to the requirements to
conduct physical inspections and
review low-income certifications and
other documentation. The text of the
temporary regulations also serves as the
text of these proposed regulations.
DATES: Comments and requests for a
public hearing must be received by May
25, 2016.
ADDRESSES: Send submissions to:
CC:PA:LPD:PR (REG–150349–12), room
5203, Internal Revenue Service, P.O.
Box 7604, Ben Franklin Station,
Washington, DC 20044. Submissions
may be hand delivered Monday through
Friday between the hours of 8 a.m. and
4 p.m. to: CC:PA:LPD:PR (REG–150349–
12), Courier’s Desk, Internal Revenue
Service, 1111 Constitution Avenue NW.,
Washington, DC. Submissions may also
be sent electronically via the Federal
eRulemaking Portal at
www.regulations.gov (IRS REG–150349–
12).
FOR FURTHER INFORMATION CONTACT:
Concerning the regulations, Jian H.
Grant, (202) 317–4137, and Martha M.
Garcia, (202) 317–6853 (not toll-free
numbers); concerning submission of
comments, the hearing, and/or to be
placed on the building access list to
attend the hearing, Oluwafunmilayo
Taylor at (202) 317–6901 (not a toll-free
number).
SUPPLEMENTARY INFORMATION:
SUMMARY:
Background
Final and temporary regulations in
the Rules and Regulations section of this
issue of the Federal Register amend the
Income Tax Regulations (26 CFR part 1)
Frm 00017
Fmt 4702
Sfmt 4702
relating to section 42 and serve as the
text for these proposed regulations.
Special Analyses
26 CFR Part 1
PO 00000
9379
Certain IRS regulations, including this
one, are exempt from the requirements
of Executive Order 12866, as
supplemented and reaffirmed by
Executive Order 13563. Therefore, a
regulatory assessment is not required. It
also has been determined that section
553(b) of the Administrative Procedure
Act (5 U.S.C. chapter 5) does not apply
to these regulations, and because the
regulations do not impose a collection
of information on small entities, the
Regulatory Flexibility Act (5 U.S.C.
chapter 6) does not apply. Pursuant to
section 7805(f) of the Internal Revenue
Code, this notice of proposed
rulemaking will be submitted to the
Chief Counsel for Advocacy of the Small
Business Administration for comment
on their impact on small business.
Comments and Requests for Public
Hearing
Before these proposed regulations are
adopted as final regulations,
consideration will be given to any
comments that are submitted timely to
the IRS as prescribed in this preamble
under the ‘‘ADDRESSES’’ heading. The
Treasury Department and the IRS
request comments on all aspects of the
proposed rules. All comments will be
available at www.regulations.gov or
upon request. A public hearing will be
scheduled if requested in writing by any
person that timely submits written
comments. If a public hearing is
scheduled, notice of the date, time, and
place for the public hearing will be
published in the Federal Register.
Drafting Information
The principal authors of these
regulations are Jian H. Grant and Martha
M. Garcia, Office of the Associate Chief
Counsel (Passthroughs and Special
Industries). However, other personnel
from the IRS and the Treasury
Department participated in their
development.
List of Subjects in 26 CFR Part 1
Income taxes, Reporting and
recordkeeping requirements.
Proposed Amendments to the
Regulations
Accordingly, 26 CFR part 1 is
proposed to be amended as follows:
PART 1—INCOME TAXES
Paragraph 1. The authority citation
continues to read in part as follows:
■
Authority: 26 U.S.C. 7805 * * *
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]]>Agencies
[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)]
[Proposed Rules]
[Pages 9374-9379]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03699]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3701; Directorate Identifier 2015-NM-015-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-25-
08, for all Airbus Model A330-200, -200 Freighter, and -300 series
airplanes; and Model A340-200 and -300 series airplanes. AD 2013-25-08
currently requires a repetitive inspection program on certain check
valves in the hydraulic systems that includes, among other things,
inspections for lock wire presence and integrity, traces of seepage or
black deposits, proper torque, alignment of the check valve and
manifold, installation of new lock wire, and corrective actions if
needed. Since we issued AD 2013-25-08, Airbus has developed an improved
check valve. This proposed AD would add airplanes to the applicability,
and require modifying the green, blue and yellow high pressure
hydraulic manifolds by replacing certain check valves with improved
check valves, which would terminate the repetitive inspections required
by this proposed AD. We are proposing this AD to detect and correct
hydraulic check valve loosening; loosened valves could result in
hydraulic leaks, possibly leading to the loss of all three hydraulic
systems and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by April 11, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this NPRM, 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 airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on
[[Page 9375]]
the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3701; 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 proposed 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.
Comments will be available in the AD docket shortly after receipt.
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 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3701;
Directorate Identifier 2015-NM-015-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On November 26, 2013, we issued AD 2013-25-08, Amendment 39-17704
(78 FR 78694, December 27, 2013) (``AD 2013-25-08''). AD 2013-25-08
requires actions intended to address an unsafe condition on all Airbus
Model A330-200 and -300 series airplanes; and Model A340-200 and -300
series airplanes.
Since we issued AD 2013-25-08, which superseded AD 2009-24-09
Amendment 39-16068 (74 FR 62208, November 27, 2009), the European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Union, has issued EASA Airworthiness
Directive 2015-0009, dated January 16, 2015 (referred to after this as
the Mandatory Continuing Airworthiness Information, or ``the MCAI''),
to correct an unsafe condition. The MCAI states:
An A330 operator experienced a Yellow hydraulic circuit low level
due to a loose check valve, Part Number (P/N) CAR401. During the
inspection on the other two hydraulic systems, the other three check
valves P/N CAR401 were also found to be loose with their lock wire
broken in two instances. Airbus A340 aeroplanes are also equipped
with P/N CAR401 high pressure manifold check valves.
Additional cases of P/N CAR401 check valve loosening have been
reported on aeroplanes having accumulated more than 1,000 flight
cycles (FC). The check valve fitted on the Yellow hydraulic system
is more affected, due to additional system cycles induced by cargo
door operation.
This condition, if not detected and corrected, could result in
hydraulic leaks, possibly leading to the loss of all three hydraulic
systems and consequent loss of control of the aeroplane.
To address this unsafe condition, EASA issued Emergency AD 2009-
0223-E (https://ad.easa.europa.eu/blob/easa_ad_2009_0223E_superseded.pdf/EAD_2009-0223-E_1) [which
corresponds to FAA AD 2009-24-09, Amendment 39-16068 (74 FR 62208,
November 27, 2009)] to require an inspection programme to detect any
check valve loosening and, if necessary, to apply the applicable
corrective actions.
EASA AD 2010-0145 (https://ad.easa.europa.eu/blob/easa_ad_2010_0145_Superseded.pdf/AD_2010-0145_1), which superseded
EASA EAD 2009-0223-E retaining its requirements, was issued to
expand the applicability to the newly certified models A330-223F and
A330-243F.
Prompted by further reported in-service events of check valve P/N
CAR401 loosening before reaching the threshold of 700 FC, EASA AD
2011-0139 (https://ad.easa.europa.eu/blob/easa_ad_2011_0139_superseded.pdf/AD_2011-0139_1), which superseded
EASA AD 2010-0145, retaining its requirements, was issued to:
--extend the requirement to identify the P/N CAR401 check valves to
all aeroplanes, and
--reduce the inspection threshold for aeroplanes fitted with check
valve P/N CAR401, either installed in production through Airbus
modification 54491, or installed in service through Airbus Service
Bulletin (SB) A330-29-3101 or Airbus SB A340-29-4078.
EASA AD 2012-0070 (https://ad.easa.europa.eu/blob/easa_ad_2012_0070_Correction_superseded.pdf/AD_2012-0070_1), which
superseded EASA AD 2011-0139, retaining its requirements, was issued
to require an increased torque value of the check valve tightening
and High Pressure (HP) manifold re-identification.
Since EASA AD 2012-0070 was issued, additional in-service events
have been reported on aeroplanes fitted with check valves on which
the increased torque value had been applied. Based on those events,
it has been concluded that the action to re-torque the check valves
with an increased value is not a satisfactory terminating action for
addressing the issue of those check valves.
To address that, EASA issued AD 2012-0244, which partially retained
the requirements of EASA AD 2012-0070, which was superseded.
Additionally, for aeroplanes equipped with P/N CAR401 on which the
increased torque value had been applied, EASA AD 2012-0244 required
repetitive inspections of the check valves and HP manifolds.
Finally, EASA AD 2012-0244 also required application of a lower
torque value when a check valve P/N CAR401 is installed on an
aeroplane.
Note: The reporting and the torque value increase requirements for
check valves P/N CAR401 of EASA AD 2012-0070 were no longer part of
EASA AD 2012-0244.
EASA AD was revised to clarify which actions are required for P/N
CAR401 check valves, depending on applied (or not) torque value.
Since EASA AD 2012-0244R1 (https://ad.easa.europa.eu/blob/easa_ad_2012_0244_R1_superseded.pdf/AD_2012-0244R1_1) was issued,
Airbus developed an improved check valve P/N CAR402, which is
embodied in production through Airbus modification 203972, and in
service through associated Airbus SB A330-29-3125, or Airbus SB
A340-29-4096, as applicable to aeroplane type. In addition, these
SBs provide instructions about the torque value (between 230 and 250
Nm) and re-identification of HP manifolds after check valve P/N
CAR402 installation.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2012-0244R1, which is superseded, and
requires the installation of check valves P/N CAR402 as terminating
action to the repetitive inspections [and adds airplanes to the
applicability].
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3701.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A330-29-3125, Revision 01,
including Appendixes 01 and 02, dated July 30, 2015; and Service
Bulletin A340-29-4096, Revision 01, including Appendixes 01 and 02,
dated July 30, 2015. This service information describes procedures for
modifying the green, blue, and yellow high pressure hydraulic manifolds
by replacing each check valve having part number (P/N) CAR401 with an
improved check valve having P/N CAR402. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
[[Page 9376]]
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Explanation of a Certain Alternative Method of Compliance (AMOC)
Paragraph (t)(1)(iii) of this proposed AD states that AMOC ANM-116-
14-429 is not approved as an AMOC for the corresponding provisions of
this AD. This AMOC defines a terminating action when Airbus
Modification 203972 is introduced in production or when the Airbus
Service Bulletin A330-29-3125, dated August 8, 2014, is embodied in
service. This proposed AD will exclude from the applicability airplanes
with Airbus Modification 203972 and will mandate actions in accordance
with Airbus Service Bulletin A330-29-3125, Revision 01, including
Appendixes 01 and 02, dated July 30, 2015.
Costs of Compliance
We estimate that this proposed AD affects 88 airplanes of U.S.
registry.
The actions required by AD 2013-25-08, and retained in this
proposed AD take about 10 work-hours per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2013-25-08 is $850 per product.
We also estimate that it would take about 32 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $239,360, or
$2,720 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD. 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 proposed
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 available costs in our
cost estimate.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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)
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), and
adding the following new AD:
Airbus: Docket No. FAA-2016-3701; Directorate Identifier 2015-NM-
015-AD.
(a) Comments Due Date
We must receive comments by April 11, 2016.
(b) Affected ADs
This AD replaces AD 2013-25-08, Amendment 39-17704 (78 FR 78694,
December 27, 2013).
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, as identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301,
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes; all
manufacturer serial numbers except those on which Airbus
modification 203972 has been embodied in production.
(2) Model A340-211, -212, -213, -311, -312, and -313 airplanes;
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
power.
(e) Reason
This AD was prompted by multiple reports of hydraulic line check
valves loosening. We are issuing this AD to detect and correct
hydraulic check valve loosening, which could result in hydraulic
leaks, possibly leading to the loss of all three hydraulic systems
and consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. Except for Model A330-223F and A330-243F airplanes:
Do the actions required by paragraphs (g)(1) and (g)(2) of this AD.
(1) For airplanes that do not have Airbus Modification 54491
embodied in production, or Airbus Service Bulletin A330-29-3101 or
Airbus Service Bulletin A340-29-4078 embodied in service: Within 100
flight cycles or 28 days after December 14, 2009 (the effective date
of AD 2009-24-09, Amendment 39-16068 (74 FR 62208, November 27,
2009)), whichever occurs first, inspect the check valves on the
blue, green, and yellow hydraulic systems to identify their part
numbers (P/Ns), in accordance with the instructions of Airbus All
Operators Telex (AOT) A330-29A3111, Revision 1, dated October 8,
2009 (for Model A330-200 and -300 series airplanes); or AOT A340-
29A4086, Revision 1, dated October 8, 2009
[[Page 9377]]
(for Model A340-200 and -300 series airplanes). Accomplishment of
the inspection required by paragraph (h) of this AD terminates the
requirements of this paragraph.
(i) If check valves having P/N CAR401 are installed on all three
hydraulic systems, before further flight, do the actions specified
in paragraph (g)(2)(i) of this AD. After accomplishing the actions
required by paragraph (g)(2)(i) of this AD, do the actions specified
in paragraphs (g)(2)(ii) and (g)(2)(iii) of this AD at the
applicable compliance times specified in those paragraphs.
Accomplishment of the inspection required by paragraph (i) of this
AD terminates the requirements of this paragraph.
(ii) If check valves having P/N CAR401 are not installed on all
three hydraulic systems, no further action is required by this
paragraph until any check valve having P/N CAR400 is replaced with a
check valve having P/N CAR401. If any check valve having P/N CAR400
is replaced by a check valve having P/N CAR401, before further
flight, do the inspection specified in paragraph (g)(1) of this AD
to determine if all three hydraulic systems are equipped with check
valves having P/N CAR401. Accomplishment of the inspection required
by paragraph (h) of this AD terminates the requirements of this
paragraph.
(2) For airplanes on which Airbus Modification 54491 was
embodied in production, or Airbus Service Bulletin A330-29-3101; or
Airbus Service Bulletin A340-29-4078 was embodied in service, do the
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and
(g)(2)(iii) of this AD.
(i) Except as required by paragraph (g)(1)(i) of this AD, at the
applicable times specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD, as applicable: Do the inspection program
(detailed inspection of the lock wire for presence and integrity, a
detailed inspection for traces of seepage or black deposits, and an
inspection for proper torque) on yellow and blue high pressure
manifolds, install new lock wires, and do all applicable corrective
actions, in accordance with the instructions of paragraph 4.1.1 of
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for
Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Airbus Model A340-200 and -
300 series airplanes). Do all applicable corrective actions before
further flight. Accomplishment of the inspection required by
paragraph (h)(1) of this AD terminates the requirements of this
paragraph.
(A) For airplanes on which Airbus Modification 54491 has been
embodied in production: At the later of the times specified in
paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD.
(1) Before the accumulation of 1,000 total flight cycles since
first flight but no earlier than the accumulation of 700 total
flight cycles since first flight.
(2) Within 100 flight cycles or 28 days after December 14, 2009
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR
62208, November 27, 2009)), whichever occurs first.
(B) For airplanes on which Airbus Service Bulletin A330-29-3101
or A340-29-4078 was embodied in service: At the later of the times
specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this
AD.
(1) Within 1,000 flight cycles since the embodiment of Airbus
Service Bulletin A330-29-3101 or A340-29-4078 but no earlier than
700 flight cycles after the embodiment of Airbus Service Bulletin
A330-29-3101 or A340-29-4078.
(2) Within 100 flight cycles or 28 days after December 14, 2009
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR
62208, November 27, 2009)), whichever occurs first.
(ii) Within 900 flight hours after accomplishment of paragraph
(g)(2)(i) of this AD, do the inspection program (detailed inspection
of the lock wire for presence and integrity, a detailed inspection
for traces of seepage or black deposits, and an inspection for
proper torque) and install a new lock wire on the green high
pressure manifold; and do an inspection (detailed inspection for
traces of seepage or black deposits, and detailed inspection to
determine alignment of the check valve and manifold) on the yellow
and blue high pressure manifolds, and do all applicable corrective
actions; in accordance with the instructions of paragraph 4.1.2 of
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for
Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Model A340-200 and -300
series airplanes). Do all applicable corrective actions before
further flight. Accomplishment of the inspection program required by
paragraph (i) of this AD terminates the requirements of this
paragraph.
(iii) Within 900 flight hours after accomplishment of paragraph
(g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900
flight hours, do the inspection program (detailed inspection for
traces of seepage or black deposits, and detailed inspection to
determine alignment of the check valve and manifold) on the green,
yellow, and blue high pressure manifolds, and do all applicable
corrective actions, in accordance with the instructions of paragraph
4.1.3 of Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009
(for Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Model A340-200 and -300
series airplanes). Do all applicable corrective actions before
further flight. Accomplishment of the inspection program required by
paragraph (i) of this AD terminates the requirements of this
paragraph.
(h) Retained Inspection, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013, with
no changes. For airplanes equipped with check valves having P/N
CAR400; and for airplanes equipped with check valves having P/N
CAR401, except for airplanes on which Airbus Modification 201384 has
been embodied during production, or on which Airbus Service Bulletin
A330-29-3119 (for Model A330-200, -200F, and -300 series airplanes)
or Airbus Service Bulletin A340-29-4091 (for Model A340-200 and -300
series airplanes) has been embodied in service: Within 900 flight
hours after January 31, 2014 (the effective date of AD 2013-25-08,
Amendment 39-17704 (78 FR 78694, December 27, 2013)), inspect the
check valves on the blue, green, and yellow hydraulic systems to
identify their part numbers, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02,
dated June 23, 2011 (for Model A330-200, -200F and -300 series
airplanes); or Airbus Service Bulletin A340-29-4086, Revision 02,
dated June 23, 2011 (for Model A340-200 and -300 series airplanes).
Accomplishment of the actions required by this paragraph terminates
the requirements specified in paragraphs (g)(1) and (g)(1)(ii) of
this AD.
(1) If check valves having P/N CAR401 are installed on all three
hydraulic systems: Before further flight, do the inspection program
(detailed inspection for red mark presence and alignment integrity
of the check valve and manifold, a detailed inspection for traces of
seepage or black deposits, and an inspection for proper torque) on
yellow and blue high pressure manifolds, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02,
dated June 23, 2011 (for Model A330-200, -200F, and -300 series
airplanes); or Airbus Service Bulletin A340-29-4086, Revision 02,
dated June 23, 2011 (for Model A340-200 and -300 series airplanes).
Accomplishment of the actions required by this paragraph terminates
the requirements specified in paragraph (g)(2)(i) of this AD.
(2) If check valves having P/N CAR401 are not installed on all
three hydraulic systems, no further action is required by this
paragraph until any check valve having P/N CAR400 is replaced with a
check valve having P/N CAR401. If any check valve having P/N CAR400
is replaced by a check valve having P/N CAR401: Before further
flight after such replacement, do the actions specified in paragraph
(h) of this AD, to determine if all three hydraulic systems are
equipped with check valves having P/N CAR401. If check valves having
P/N CAR401 are installed on all three hydraulic systems: Before
further flight, do the actions specified in paragraphs (h)(1) and
(i) of this AD.
(i) Retained Repetitive Inspection Program and Corrective Actions, With
No Changes
This paragraph restates the requirements of paragraph (i) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. Within 900 flight hours after accomplishment of
paragraph (h)(1) of this AD, do the inspection program (detailed
inspection for red mark presence and alignment integrity of the
check valve and manifold, a detailed inspection for traces of
seepage or black deposits, and an inspection for proper torque) on
the green, yellow, and blue system check valves, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02,
dated June 23, 2011 (for Model A330-200, -200F, and -300 series
airplanes);
[[Page 9378]]
or Airbus Service Bulletin A340-29-4086, Revision 02, dated June 23,
2011 (for Model A340-200 and -300 series airplanes). Do all
applicable corrective actions before further flight. Repeat the
inspection program thereafter at intervals not to exceed 900 flight
hours. Accomplishment of the actions required by this paragraph
terminates the requirements specified in paragraphs (g)(1)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD.
(j) Retained Repetitive Inspection for Certain Airplanes, With No
Changes
This paragraph restates the requirements of paragraph (j) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. For airplanes equipped with check valves having P/N
CAR401 and on which Airbus Modification 201384 has been embodied
during production, or on which Airbus Service Bulletin A330-29-3119
(for Model A330-200, -200F, and -300 series airplanes); or Airbus
Service Bulletin A340-29-4091 (for Model A340-200 and -300 series
airplanes) has been embodied in service: Within 1,000 flight hours
after January 31, 2014 (the effective date of AD 2013-25-08,
Amendment 39-17704 (78 FR 78694, December 27, 2013)), do a general
visual inspection of the green, yellow, and blue high pressure
manifolds and check valves having P/N CAR401 for any sign of
rotation of the check valve head, and for any signs of hydraulic
fluid leakage or seepage (including black deposits), in accordance
with the instructions of Airbus Alert Operators Transmission
A29L001-12, dated October 11, 2012. Repeat the inspection thereafter
at interval not to exceed 900 flight hours.
(k) Retained Corrective Action for Certain Airplanes, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. If, during any inspection required by paragraph (j)
of this AD, any sign of rotation of the check valve head is found,
or any sign of hydraulic fluid leakage or seepage (including black
deposits) is found: Before further flight, do all applicable
corrective actions, in accordance with the instructions of Airbus
Alert Operators Transmission A29L001-12, dated October 11, 2012.
(l) Retained Provisions Regarding Terminating Action, With No Changes
This paragraph restates the provisions of paragraph (l) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. Accomplishment of the corrective actions required
by this AD does not constitute terminating action for the repetitive
inspections required by this AD.
(m) Retained Replacement Check Valve Torque Value, With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. As of January 31, 2014 (the effective date of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013)), at
each replacement of a check valve with a check valve having P/N
CAR401, apply a torque of 141 to 143 newton meter (N.m) (103.98 to
105.45 pounds-foot (lbf.ft)) during installation.
(n) Retained Credit for Previous Actions, With No Changes
This paragraph restates the provisions of paragraph (n) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes.
(1) This paragraph provides credit for actions required by
paragraph (g)(2)(i) of this AD, if those actions were performed
before December 14, 2009 (the effective date of AD 2009-24-09,
Amendment 39-16068 (74 FR 62208, November 27, 2009)), using the
applicable service information specified in paragraphs (n)(1)(i) and
(n)(1)(ii) of this AD.
(i) Airbus AOT A330-29A3111, dated September 2, 2009 (for Model
A330-200 and -300 series airplanes), which is not incorporated by
reference in this AD.
(ii) Airbus AOT A340-29A4086, dated September 2, 2009 (for Model
A340-200 and -300 series airplanes), which is not incorporated by
reference in this AD.
(2) This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before
January 31, 2014 (the effective date of AD 2013-25-08, Amendment 39-
17704 (78 FR 78694, December 27, 2013)) using the applicable service
information specified in paragraphs (n)(2)(i) through (n)(2)(iv) of
this AD.
(i) Airbus AOT A330-29A3111, dated September 2, 2009 (for Model
A330-200 and -300 series airplanes), which is not incorporated by
reference in this AD.
(ii) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009
(for Model A330-200 and -300 series airplanes).
(iii) Airbus AOT A340-29A4086, dated September 2, 2009, (for
Model A340-200 and -300 series airplanes), which is not incorporated
by reference in this AD.
(iv) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009
(for Model A340-200 and -300 series airplanes).
(o) Retained Provisions for Reporting, With No Changes
This paragraph restates the provisions of paragraph (o) of AD
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013),
with no changes. Although the service information specified in
paragraphs (o)(1) through (o)(5) of this AD specifies to submit
certain information to the manufacturer, this AD does not include
that requirement.
(1) Airbus Alert Operators Transmission A29L001-12, dated
October 11, 2012.
(2) Airbus Mandatory Service Bulletin A330-29-3111, Revision 02,
dated June 23, 2011.
(3) Airbus Mandatory Service Bulletin A340-29-4086, Revision 02,
dated June 23, 2011.
(4) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009.
(5) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009.
(p) New Requirement of This AD: Modify Hydraulic Systems
Within 36 months after the effective date of this AD, modify the
green, blue, and yellow high pressure hydraulic manifolds by
replacing each check valve having P/N CAR401 with an improved check
valve having P/N CAR402, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-29-3125, Revision 01,
including Appendixes 01 and 02, dated July 30, 2015; or Airbus
Service Bulletin A340-29-4096, Revision 01, including Appendixes 01
and 02, dated July 30, 2015; as applicable.
(q) New Requirement of This AD: Repetitive Inspection Terminating
Action
Modification of an airplane, as required by paragraph (p) of
this AD, constitutes terminating action for the repetitive
inspections required by this AD.
(r) New Requirement of This AD: Parts Installation Limitations
(1) For an airplane that, as of the effective date of this AD,
has a check valve having P/N CAR401 installed, after modification of
an airplane as required by paragraph (p) of this AD, no person may
install a check valve having P/N CAR401, on that airplane.
(2) For an airplane that does not have a check valve having P/N
CAR401 installed, as of the effective date of this AD, no person may
install a check valve having P/N CAR401, on that airplane.
(s) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(p) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A330-29-3125, dated
August 8, 2014; or Airbus Service Bulletin A340-29-4096, dated
August 8, 2014; as applicable; which are not incorporated by
reference in this AD.
(t) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOC ANM-116-14-180 R1, dated February 21, 2014, is
approved as an AMOC for the corresponding provisions of this AD.
[[Page 9379]]
(iii) AMOC ANM-116-14-429, dated September 25, 2014, is not
approved as an AMOC for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the 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) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(u) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0009, dated January 16,
2015, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2016-3701.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at 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 airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com.
(3) 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 airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on February 15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-03699 Filed 2-24-16; 8:45 am]
BILLING CODE 4910-13-P
