[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]


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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).

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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 http://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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on

[[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 http://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 http://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 (http://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 (http://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 (http://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 (http://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 (http://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 http://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: [email protected].
    (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 http://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 [email protected]; Internet http://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 [email protected]; 
Internet http://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