AD 2013-25-08

[Federal Register Volume 78, Number 249 (Friday, December 27, 2013)]
[Rules and Regulations]
[Pages 78694-78698]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-29998]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0365; Directorate Identifier 2012-NM-223-AD; 
Amendment 39-17704; AD 2013-25-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2009-24-09 for 
all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 
and -300 series airplanes. AD 2009-24-09 required 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, installing new lock wire, 
and corrective actions if needed. This new AD expands the 
applicability, reduces the compliance time, changes torque values of 
the check valve tightening, and requires a repetitive inspection 
program for certain check valves in the

[[Page 78695]]

hydraulic systems on airplanes that have had a certain modification 
embodied during production or in-service. This AD was prompted by 
multiple reports of hydraulic line check valves loosening. We are 
issuing this AD to detect and correct such 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.

DATES: This AD becomes effective January 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
December 14, 2009 (74 FR 62208, November 27, 2009).

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-0365; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 8, 2013 (78 FR 
26716), and proposed to supersede AD 2009-24-09, Amendment 39-16068 (74 
FR 62208, November 27, 2009). The NPRM proposed to correct an unsafe 
condition for the specified products. The European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, has issued EASA Airworthiness Directive 2012-
0244R1, dated January 25, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for the specified products. 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 [total] 
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 (<a href="http://ad.easa.europa.eu/blob/easa_ad_2009_0223E_superseded.pdf/EAD_2009-0223-E_1">http://ad.easa.europa.eu/blob/easa_ad_2009_0223E_superseded.pdf/EAD_2009-0223-E_1</a>) [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 (<a href="http://ad.easa.europa.eu/blob/easa_ad_2010_0145_Superseded.pdf/AD_2010-0145_1">http://ad.easa.europa.eu/blob/easa_ad_2010_0145_Superseded.pdf/AD_2010-0145_1</a>), 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 (<a href="http://ad.easa.europa.eu/blob/easa_ad_2011_0139_superseded.pdf/AD_2011-0139_1">http://ad.easa.europa.eu/blob/easa_ad_2011_0139_superseded.pdf/AD_2011-0139_1</a>), 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 to
--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 (<a href="http://ad.easa.europa.eu/blob/easa_ad_2012_0070_Correction_superseded.pdf/AD_2012-0070_1">http://ad.easa.europa.eu/blob/easa_ad_2012_0070_Correction_superseded.pdf/AD_2012-0070_1</a>), 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.
    For the reasons described above, this new [EASA] AD partially 
retains the requirements of EASA AD 2012-0070, which is superseded. 
Additionally, for aeroplanes equipped with P/N CAR401 on which the 
increased torque value has been applied, this new [EASA] AD requires 
repetitive inspections of the check valves and HP manifolds. 
Finally, this [EASA] AD also requires application of a lower torque 
value when a check valve P/N CAR401 is installed on an aeroplane.
    This [EASA] AD is considered to be an interim action and further 
AD action may follow.
    Note: the reporting and the torque value increase requirements 
for check valves P/N CAR401 of EASA AD 2012-0070 are no longer part 
of this new [EASA] AD.

You may obtain further information by examining the MCAI in the AD 
docket. You may examine the MCAI in the AD docket on the Internet at 
<a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-0365-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Change Compliance Time

    US Airways requested that we change the compliance time in 
paragraph (j) of the NPRM (78 FR 26716, May 8, 2013) to 1,000 flight 
hours after the effective date of the AD, or within 1,000 flight hours 
after the date of issuance of the original export certificate of 
airworthiness, whichever occurs later. US Airways stated that this will 
provide an inspection threshold for new airplane deliveries.
    We disagree with changing the compliance time to base it, in part, 
on the date of issuance of the original export certificate of 
airworthiness. In developing appropriate compliances time for this 
final rule, we considered the safety issue as well as the 
recommendations of the manufacturer, the availability of necessary 
repair parts, and the practical aspect of accomplishing the required 
inspection within an interval of time that corresponds to the normal 
maintenance schedules of most affected operators. In addition, the 
compliance time of ``Within 1,000 flight hours after the effective date 
of this AD'' specified in paragraph (j) of this final rule corresponds 
with the compliance time given in the MCAI. We have not changed this 
final rule in this regard.

Change Made to This Final Rule

    We reformatted paragraph (n) of this final rule, and removed an 
unnecessary sentence that appeared at the end of paragraph (n)(2) of 
the NPRM (78 FR 26716, May 8, 2013).

[[Page 78696]]

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 26716, May 8, 2013) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 26716, May 8, 2013).

Costs of Compliance

    We estimate that this AD affects 67 airplanes of U.S. registry.
    The actions that are required by AD 2009-24-09, Amendment 39-16068 
(74 FR 62208, November 27, 2009), and retained in this AD take about 8 
work-hours per product, at an average labor rate of $85 per work hour. 
Based on these figures, the estimated cost of the currently required 
actions is $680 per product.
    We estimate that it will take about 2 work-hours per product to 
comply with the new requirements of this AD. The average labor rate is 
$85 per work-hour. Based on these figures, we estimate the cost of this 
AD on U.S. operators to be $11,390, or $170 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-0365; or in person at the 
Docket Operations office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone (800) 
647-5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 2009), and 
adding the following new AD:

2013-25-08 Airbus: Amendment 39-17704. Docket No. FAA-2013-0365; 
Directorate Identifier 2012-NM-223-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 31, 
2014.

(b) Affected ADs

    This AD supersedes AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers.

(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 such 
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

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Actions

    This paragraph restates the requirements of paragraph (g) of AD 
2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 2009). 
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 (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.

[[Page 78697]]

    (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 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) New Inspection and Actions

    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 the effective date of this AD, 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 Mandatory Service Bulletin A330-29-3111, Revision 02, dated 
June 23, 2011 (for Model A330-200, -200F and -300 series airplanes); 
or Airbus Mandatory 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 Mandatory Service Bulletin A330-29-3111, 
Revision 02, dated June 23, 2011 (for Model A330-200, -200F, and -
300 series airplanes); or Airbus Mandatory 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) New Repetitive Inspection Program and Corrective Actions

    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 Mandatory Service Bulletin A330-29-3111, Revision 02, dated 
June 23, 2011 (for Model A330-200, -200F, and -300 series 
airplanes); or Airbus Mandatory Service Bulletin A340-29-4086, 
Revision 02, dated June 23, 2011 (for Model A340-200 and -300 series 
airplanes). Repeat the inspection program thereafter at intervals 
not to exceed 900 flight hours. Do all applicable corrective actions 
before further flight. 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) New Repetitive Inspection for Certain Airplanes

    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 the 
effective date of this AD, do a general visual

[[Page 78698]]

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) New Corrective Action for Certain Airplanes

    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) No Terminating Action

    Accomplishment of the corrective actions required by this AD 
does not constitute terminating action for the repetitive 
inspections required by this AD.

(m) Replacement Check Valve Torque Value

    As of the effective date of this AD, at each replacement of a 
check valve with a check valve having P/N CAR401, apply a torque of 
141 to 143 newton metre (N.m) (103.98 to 105.45 pounds-foot 
(lbf.ft)) during installation.

(n) Credit for Previous Actions

    (1) This paragraph restates the credit specified in paragraph 
(g)(2)(iv) of AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009). 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), 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 the 
effective date of this AD 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) No Reporting

    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) 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: <a href="/cdn-cgi/l/email-protection#cff6e28e8182e2fefef9e28e82808ce29d8a9e9a8a9c9b9c8fa9aeaee1a8a0b9"><span class="__cf_email__" data-cfemail="eed7c3afa0a3c3dfdfd8c3afa3a1adc3bcabbfbbabbdbabdae888f8fc0898198">[email&#160;protected]</span></a>. 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. AMOCs 
approved for AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009), are approved as AMOCs for the corresponding 
provisions of this AD, except AMOC ANM-116-11-172 is not approved as 
an AMOC for the corresponding provisions of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency Airworthiness Directive 2012-0244R1, 
dated January 25, 2013, for related information. You may examine the 
MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-0365-0003.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (r)(5) and (r)(6) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 31, 2014.
    (i) Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
    (ii) Airbus Mandatory Service Bulletin A330-29-3111, Revision 
02, dated June 23, 2011.
    (iii) Airbus Mandatory Service Bulletin A340-29-4086, Revision 
02, dated June 23, 2011.
    (4) The following service information was approved for IBR on 
December 14, 2009 (74 FR 62208, November 27, 2009).
    (i) Airbus Alert Operators Telex A330-29A3111, Revision 1, dated 
October 8, 2009. Only the first page of this document contains the 
document number, revision level, and date; no other pages of this 
document contain this information.
    (ii) Airbus Alert Operators Telex A340-29A4086, Revision 1, 
dated October 8, 2009. Only the first page of this document contains 
the document number, revision level, and date; no other pages of 
this document contain this information.
    (5) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#6c0d051e1b031e18040502091f1f422d5f5f5c412d5f585c2c0d051e0e191f420f0301"><span class="__cf_email__" data-cfemail="6908001b1e061b1d0100070c1a1a47285a5a5944285a5d592908001b0b1c1a470a0604">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (6) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on November 26, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-29998 Filed 12-26-13; 8:45 am]
BILLING CODE 4910-13-P