81_FR_83873 81 FR 83648 - Airworthiness Directives; Airbus Airplanes

81 FR 83648 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 225 (November 22, 2016)

Page Range83648-83653
FR Document2016-25745

We are superseding 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 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, installation of new lock wire, and corrective actions if needed. This new AD removes airplanes from the applicability, and requires modifying the green, blue, and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which terminates the repetitive inspections required by this AD. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to address the unsafe condition on these products.

Federal Register, Volume 81 Issue 225 (Tuesday, November 22, 2016) 
[Federal Register Volume 81, Number 225 (Tuesday, November 22, 2016)]
[Rules and Regulations]
[Pages 83648-83653]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-25745]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3701; Directorate Identifier 2015-NM-015-AD; 
Amendment 39-18689; AD 2016-21-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding 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 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, installation of new 
lock wire, and corrective actions if needed. This new AD removes 
airplanes from the applicability, and requires modifying the green, 
blue, and yellow high pressure hydraulic manifolds by replacing certain 
check valves with improved check valves, which terminates the 
repetitive inspections required by this AD. This AD was prompted by 
multiple reports of hydraulic line check valves loosening. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 27, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 27, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
31, 2014 (78 FR 78694, December 27, 2013).
    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: For service information identified in this final rule, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email [email protected]; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3701.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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 to supersede AD 2013-25-08, Amendment 39-17704 (78 FR 78694, 
December 27, 2013) (``AD 2013-25-08''). AD 2013-25-08 applied to all 
Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and 
Model A340-200 and -300 series airplanes. The NPRM published in the 
Federal Register on February 25, 2016 (81 FR 9374) (``the NPRM''). The 
NPRM was prompted by multiple reports of hydraulic line check valves 
loosening. The NPRM proposed to continue to require 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. The NPRM also proposed to 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 the proposed AD. We are issuing 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.
    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

[[Page 83649]]

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 [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, 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, 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, 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 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 removes airplanes on which 
Airbus modification 203972 has been embodied from 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to the comment.

Support for the NPRM

    American Airlines (AAL) stated that it operates 24 airplanes that 
will be affected by the NPRM, and that it agrees with the need to 
accomplish Airbus Service Bulletin A330-29-3125 on these airplanes.

Request To Reference Revised Service Information

    AAL requested that we revise the NPRM to reference Airbus Service 
Bulletin A330-29-3125, Revision 02, including Appendixes 01 and 02, 
dated January 21, 2016. AAL pointed out that this revision includes 
several corrections in the Accomplishment Instructions.
    We agree to reference the latest service information in this final 
rule. Since we issued the NPRM, Airbus has issued Airbus Service 
Bulletin A330-29-3125, Revision 03, including Appendixes 01 and 02, 
dated April 8, 2016; and Service Bulletin A340-29-4096, Revision 02, 
including Appendixes 01 and 02, dated April 8, 2016. This service 
information states that no additional work is required by these 
revisions for airplanes modified by any previous issue. We have revised 
paragraph (p) of this AD to reference this revised service information 
as appropriate sources of service information for accomplishing the 
actions required by that paragraph. We have also revised paragraph (s) 
of this AD by adding 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, Revision 02, 
including Appendixes 01 and 02, dated January 21, 2016; or 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. Additionally, we have reformatted paragraph (s) of this AD 
to improve readability; this change does not affect the intent or 
requirements of that paragraph.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-29-3125, Revision 03, 
including Appendixes 01 and 02, dated April 8, 2016; and Service 
Bulletin A340-29-4096, Revision 02, including Appendixes 01 and 02, 
dated April 8, 2016. This service information describes procedures for 
modifying 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. These documents are distinct since they apply 
to different airplane models. 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.

Costs of Compliance

    We estimate that this AD affects 88 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:
    The actions required by AD 2013-25-08, and retained in this 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 were 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 AD. The average labor 
rate is $85

[[Page 83650]]

per work-hour. Based on these figures, we estimate the cost of this 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 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 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 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.

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) 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), and 
adding the following new AD:

2016-21-08 Airbus: Amendment 39-18689; Docket No. FAA-2016-3701; 
Directorate Identifier 2015-NM-015-AD.

(a) Effective Date

    This AD is effective December 27, 2016.

(b) Affected ADs

    This AD replaces AD 2013-25-08, Amendment 39-17704 (78 FR 78694, 
December 27, 2013) (``AD 2013-25-08'').

(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; 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.

(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, 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) (``AD 2009-24-09'')), 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 Airbus 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.
    (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 Airbus AOT A340-
29A4086, Revision 1, dated October 8,

[[Page 83651]]

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), whichever occurs first.
    (B) For airplanes on which Airbus Service Bulletin A330-29-3101 
or Airbus Service Bulletin 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 Airbus Service Bulletin A340-29-
4078 but no earlier than 700 flight cycles after the embodiment of 
Airbus Service Bulletin A330-29-3101 or Airbus Service Bulletin 
A340-29-4078.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09), 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 Airbus 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 Airbus 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, 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), 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) Retained Repetitive Inspection Program and Corrective Actions, With 
No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2013-25-08, 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 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). 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, 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), 
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, 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, 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.

[[Page 83652]]

(m) Retained Replacement Check Valve Torque Value, With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2013-25-08, with no changes. As of January 31, 2014 (the effective 
date of AD 2013-25-08), at each replacement of a check valve with a 
check valve having P/N CAR401, apply a torque of 141 to 143 newton 
meters (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, 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), 
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), 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), which is 
incorporated by reference in this AD.
    (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), which is 
incorporated by reference in this AD.

(o) Retained Provisions for Reporting, With No Changes

    This paragraph restates the provisions of paragraph (o) of AD 
2013-25-08, 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 03, 
including Appendixes 01 and 02, dated April 8, 2016; or Airbus 
Service Bulletin A340-29-4096, Revision 02, including Appendixes 01 
and 02, dated April 8, 2016; as applicable.

(q) New Provision of This AD: Terminating Action for Repetitive 
Inspections

    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 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 the applicable service information specified 
in paragraphs (s)(1) through (s)(5) of this AD, which are not 
incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-29-3125, dated August 8, 2014.
    (2) Airbus Service Bulletin A330-29-3125, Revision 01, including 
Appendixes 01 and 02, dated July 30, 2015.
    (3) Airbus Service Bulletin A330-29-3125, Revision 02, including 
Appendixes 01 and 02, dated January 21, 2016.
    (4) Airbus Service Bulletin A340-29-4096, dated August 8, 2014.
    (5) Airbus Service Bulletin A340-29-4096, Revision 01, including 
Appendixes 01 and 02, dated July 30, 2015.

(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.
    (ii) AMOC ANM-116-14-180 R1, dated February 21, 2014, is 
approved as an AMOC for the corresponding provisions of this AD.
    (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 is available at the addresses specified in 
paragraphs (v)(6) and (v)(7) of this AD.

(v) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 27, 2016.
    (i) Airbus Service Bulletin A330-29-3125, Revision 03, including 
Appendixes 01 and 02, dated April 8, 2016.
    (ii) Airbus Service Bulletin A340-29-4096, Revision 02, 
including Appendixes 01 and 02, dated April 8, 2016.

[[Page 83653]]

    (4) The following service information was approved for IBR on 
January 31, 2014 (78 FR 78694, December 27, 2013).
    (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.
    (5) 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.
    (6) 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.
    (7) 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.
    (8) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 12, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25745 Filed 11-21-16; 8:45 am]
 BILLING CODE 4910-13-P

83648 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations (h) Dispute resolution. A requester the green, blue, and yellow high 1601 Lind Avenue SW., Renton, WA seeking to engage in dispute resolution pressure hydraulic manifolds by 98057–3356; telephone 425–227–1138; may make a request to the FOIA Public replacing certain check valves with fax 425–227–1149. Liaison and/or OGIS by following the improved check valves, which SUPPLEMENTARY INFORMATION: procedures set forth online in the FDIC’s terminates the repetitive inspections FOIA Service Center at http:// required by this AD. This AD was Discussion www.fdic.gov. prompted by multiple reports of We issued a notice of proposed (i) * * * hydraulic line check valves loosening. rulemaking (NPRM) to amend 14 CFR (2) A person whose initial request for We are issuing this AD to address the part 39 to supersede AD 2013–25–08, records under this section, or whose unsafe condition on these products. Amendment 39–17704 (78 FR 78694, request for a waiver of fees under DATES: This AD is effective December December 27, 2013) (‘‘AD 2013–25– paragraph (f)(1)(x) of this section, has 27, 2016. 08’’). AD 2013–25–08 applied to all been denied, either in part or in whole, The Director of the Federal Register Airbus Model A330–200, –200 has the right to appeal the denial to the approved the incorporation by reference Freighter, and –300 series airplanes; and FDIC’s General Counsel (or designee) of certain publications listed in this AD Model A340–200 and –300 series within 90 calendar days after receipt of as of December 27, 2016. airplanes. The NPRM published in the notification of the denial. Appeals of The Director of the Federal Register Federal Register on February 25, 2016 denials of initial requests or for a waiver approved the incorporation by reference (81 FR 9374) (‘‘the NPRM’’). The NPRM of fees must be in writing and include of certain other publications listed in was prompted by multiple reports of any additional information relevant to this AD as of January 31, 2014 (78 FR hydraulic line check valves loosening. consideration of the appeal. 78694, December 27, 2013). The NPRM proposed to continue to * * * * * The Director of the Federal Register require a repetitive inspection program approved the incorporation by reference on certain check valves in the hydraulic Dated at Washington, DC, this 15th day of November, 2016. of certain other publications listed in systems that includes, among other this AD as of December 14, 2009 (74 FR things, inspections for lock wire By order of the Board of Directors. 62208, November 27, 2009). presence and integrity, traces of seepage Federal Deposit Insurance Corporation. ADDRESSES: For service information or black deposits, proper torque, Valerie J. Best, identified in this final rule, contact alignment of the check valve and Assistant Executive Secretary. Airbus SAS—Airworthiness Office— manifold, installation of new lock wire, [FR Doc. 2016–27961 Filed 11–21–16; 8:45 am] EAL, 1 Rond Point Maurice Bellonte, and corrective actions if needed. The BILLING CODE 6714–01–P 31707 Blagnac Cedex, France; telephone NPRM also proposed to add airplanes to +33 5 61 93 36 96; fax +33 5 61 93 45 the applicability, and require modifying 80; email airworthiness.A330-A340@ the green, blue, and yellow high DEPARTMENT OF TRANSPORTATION airbus.com; Internet http:// pressure hydraulic manifolds by www.airbus.com. You may view this replacing certain check valves with Federal Aviation Administration referenced service information at the improved check valves, which would FAA, Transport Airplane Directorate, terminate the repetitive inspections 14 CFR Part 39 1601 Lind Avenue SW., Renton, WA. required by the proposed AD. We are [Docket No. FAA–2016–3701; Directorate For information on the availability of issuing this AD to detect and correct Identifier 2015–NM–015–AD; Amendment this material at the FAA, call 425–227– hydraulic check valve loosening; 39–18689; AD 2016–21–08] 1221. It is also available on the Internet loosened valves could result in at http://www.regulations.gov by hydraulic leaks, possibly leading to the RIN 2120–AA64 searching for and locating Docket No. loss of all three hydraulic systems and FAA–2016–3701. consequent loss of control of the Airworthiness Directives; Airbus Airplanes Examining the AD Docket airplane. The European Aviation Safety Agency AGENCY: Federal Aviation You may examine the AD docket on (EASA), which is the Technical Agent Administration (FAA), Department of the Internet at http:// for the Member States of the European Transportation (DOT). www.regulations.gov by searching for Union, has issued EASA Airworthiness ACTION: Final rule. and locating Docket No. FAA–2016– Directive 2015–0009, dated January 16, 3701; or in person at the Docket 2015 (referred to after this as the SUMMARY: We are superseding Management Facility between 9 a.m. Mandatory Continuing Airworthiness Airworthiness Directive (AD) 2013–25– and 5 p.m., Monday through Friday, Information, or ‘‘the MCAI’’), to correct 08 for all Airbus Model A330–200, –200 except Federal holidays. The AD docket an unsafe condition. The MCAI states: Freighter, and –300 series airplanes; and contains this AD, the regulatory An A330 operator experienced a Yellow Model A340–200 and –300 series evaluation, any comments received, and hydraulic circuit low level due to a loose airplanes. AD 2013–25–08 required a other information. The address for the check valve, Part Number (P/N) CAR401. repetitive inspection program on certain Docket Office (telephone 800–647–5527) During the inspection on the other two check valves in the hydraulic systems is Docket Management Facility, U.S. hydraulic systems, the other three check that includes, among other things, Department of Transportation, Docket valves P/N CAR401 were also found to be inspections for lock wire presence and Operations, M–30, West Building loose with their lock wire broken in two sradovich on DSK3GMQ082PROD with RULES integrity, traces of seepage or black Ground Floor, Room W12–140, 1200 instances. Airbus A340 aeroplanes are also deposits, proper torque, alignment of New Jersey Avenue SE., Washington, equipped with P/N CAR401 high pressure DC 20590. manifold check valves. the check valve and manifold, Additional cases of P/N CAR401 check installation of new lock wire, and FOR FURTHER INFORMATION CONTACT: valve loosening have been reported on corrective actions if needed. This new Vladimir Ulyanov, Aerospace Engineer, aeroplanes having accumulated more than AD removes airplanes from the International Branch, ANM–116, 1,000 flight cycles (FC). The check valve applicability, and requires modifying Transport Airplane Directorate, FAA, fitted on the Yellow hydraulic system is more VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1

Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83649 affected, due to additional system cycles 203972, and in service through associated Service Bulletin A330–29–3125, induced by cargo door operation. Airbus SB A330–29–3125, or Airbus SB Revision 02, including Appendixes 01 This condition, if not detected and A340–29–4096, as applicable to aeroplane and 02, dated January 21, 2016; or corrected, could result in hydraulic leaks, type. In addition, these SBs provide Airbus Service Bulletin A330–29–3125, possibly leading to the loss of all three instructions about the torque value (between hydraulic systems and consequent loss of 230 and 250 Nm) and re-identification of HP Revision 01, including Appendixes 01 control of the aeroplane. manifolds after check valve P/N CAR402 and 02, dated July 30, 2015; or Airbus To address this unsafe condition, EASA installation. Service Bulletin A340–29–4096, issued Emergency AD 2009–0223–E [which For the reasons described above, this Revision 01, including Appendixes 01 corresponds to FAA AD 2009–24–09, [EASA] AD retains the requirements of EASA and 02, dated July 30, 2015; as Amendment 39–16068 (74 FR 62208, AD 2012–0244R1, which is superseded, and applicable. Additionally, we have November 27, 2009)] to require an inspection requires the installation of check valves P/N reformatted paragraph (s) of this AD to programme to detect any check valve CAR402 as terminating action to the improve readability; this change does loosening and, if necessary, to apply the repetitive inspections [and removes airplanes applicable corrective actions. not affect the intent or requirements of on which Airbus modification 203972 has EASA AD 2010–0145, which superseded been embodied from the applicability]. that paragraph. EASA EAD 2009–0223–E retaining its Conclusion requirements, was issued to expand the You may examine the MCAI in the applicability to the newly certified models AD docket on the Internet at http:// We reviewed the available data, A330–223F and A330–243F. www.regulations.gov by searching for including the comment received, and Prompted by further reported in-service and locating Docket No. FAA–2016– determined that air safety and the events of check valve P/N CAR401 loosening 3701. public interest require adopting this AD before reaching the threshold of 700 FC, with the changes described previously EASA AD 2011–0139, which superseded Comments EASA AD 2010–0145, retaining its and minor editorial changes. We have We gave the public the opportunity to determined that these changes: requirements, was issued to: —Extend the requirement to identify the P/ participate in developing this AD. The • Are consistent with the intent that N CAR401 check valves to all aeroplanes, following presents the comment was proposed in the NPRM for and received on the NPRM and the FAA’s correcting the unsafe condition; and —reduce the inspection threshold for response to the comment. • Do not add any additional burden aeroplanes fitted with check valve P/N upon the public than was already CAR401, either installed in production Support for the NPRM proposed in the NPRM. through Airbus modification 54491, or American Airlines (AAL) stated that it installed in service through Airbus Service operates 24 airplanes that will be Related Service Information Under 1 Bulletin (SB) A330–29–3101 or Airbus SB affected by the NPRM, and that it agrees CFR Part 51 A340–29–4078. with the need to accomplish Airbus EASA AD 2012–0070, which superseded Airbus has issued Service Bulletin EASA AD 2011–0139, retaining its Service Bulletin A330–29–3125 on these A330–29–3125, Revision 03, including requirements, was issued to require an airplanes. Appendixes 01 and 02, dated April 8, increased torque value of the check valve Request To Reference Revised Service 2016; and Service Bulletin A340–29– tightening and High Pressure (HP) manifold Information 4096, Revision 02, including re-identification. Appendixes 01 and 02, dated April 8, Since EASA AD 2012–0070 was issued, AAL requested that we revise the 2016. This service information describes additional in-service events have been NPRM to reference Airbus Service procedures for modifying the green, reported on aeroplanes fitted with check Bulletin A330–29–3125, Revision 02, valves on which the increased torque value blue, and yellow high pressure including Appendixes 01 and 02, dated hydraulic manifolds by replacing each had been applied. Based on those events, it January 21, 2016. AAL pointed out that check valve having P/N CAR401 with an has been concluded that the action to re- torque the check valves with an increased this revision includes several improved check valve having P/N value is not a satisfactory terminating action corrections in the Accomplishment CAR402. These documents are distinct for addressing the issue of those check Instructions. since they apply to different airplane valves. We agree to reference the latest models. This service information is To address that, EASA issued AD 2012– service information in this final rule. reasonably available because the 0244, which partially retained the Since we issued the NPRM, Airbus has requirements of EASA AD 2012–0070, which interested parties have access to it issued Airbus Service Bulletin A330– through their normal course of business was superseded. Additionally, for aeroplanes 29–3125, Revision 03, including equipped with P/N CAR401 on which the or by the means identified in the increased torque value had been applied, Appendixes 01 and 02, dated April 8, ADDRESSES section. EASA AD 2012–0244 required repetitive 2016; and Service Bulletin A340–29– inspections of the check valves and HP 4096, Revision 02, including Costs of Compliance manifolds. Finally, EASA AD 2012–0244 also Appendixes 01 and 02, dated April 8, We estimate that this AD affects 88 required application of a lower torque value 2016. This service information states airplanes of U.S. registry. when a check valve P/N CAR401 is installed that no additional work is required by We estimate the following costs to on an aeroplane. these revisions for airplanes modified comply with this AD: Note: The reporting and the torque value by any previous issue. We have revised The actions required by AD 2013–25– increase requirements for check valves P/N paragraph (p) of this AD to reference 08, and retained in this AD take about CAR401 of EASA AD 2012–0070 were no this revised service information as 10 work-hours per product, at an longer part of EASA AD 2012–0244. appropriate sources of service average labor rate of $85 per work-hour. sradovich on DSK3GMQ082PROD with RULES EASA AD was revised to clarify which information for accomplishing the Based on these figures, the estimated actions are required for P/N CAR401 check actions required by that paragraph. We cost of the actions that were required by valves, depending on applied (or not) torque value. have also revised paragraph (s) of this AD 2013–25–08 is $850 per product. Since EASA AD 2012–0244R1 was issued, AD by adding credit for actions required We also estimate that it would take Airbus developed an improved check valve by paragraph (p) of this AD, if those about 32 work-hours per product to P/N CAR402, which is embodied in actions were performed before the comply with the basic requirements of production through Airbus modification effective date of this AD using Airbus this AD. The average labor rate is $85 VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1

83650 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations per work-hour. Based on these figures, List of Subjects in 14 CFR Part 39 required by paragraphs (g)(1) and (g)(2) of we estimate the cost of this AD on U.S. this AD. Air transportation, Aircraft, Aviation (1) For airplanes that do not have Airbus operators to be $239,360, or $2,720 per safety, Incorporation by reference, Modification 54491 embodied in production, product. Safety. or Airbus Service Bulletin A330–29–3101 or We have received no definitive data Airbus Service Bulletin A340–29–4078 that would enable us to provide cost Adoption of the Amendment embodied in service: Within 100 flight cycles estimates for the on-condition actions Accordingly, under the authority or 28 days after December 14, 2009 (the specified in this AD. We have no way delegated to me by the Administrator, effective date of AD 2009–24–09, of determining the number of aircraft the FAA amends 14 CFR part 39 as Amendment 39–16068 (74 FR 62208, that might need these actions. follows: November 27, 2009) (‘‘AD 2009–24–09’’)), whichever occurs first, inspect the check According to the manufacturer, some PART 39—AIRWORTHINESS valves on the blue, green, and yellow of the costs of this AD may be covered hydraulic systems to identify their part under warranty, thereby reducing the DIRECTIVES numbers (P/Ns), in accordance with the cost impact on affected individuals. We instructions of Airbus All Operators Telex do not control warranty coverage for ■ 1. The authority citation for part 39 (AOT) A330–29A3111, Revision 1, dated affected individuals. As a result, we continues to read as follows: October 8, 2009 (for Model A330–200 and have included all available costs in our Authority: 49 U.S.C. 106(g), 40113, 44701. –300 series airplanes); or Airbus AOT A340– cost estimate. 29A4086, Revision 1, dated October 8, 2009 § 39.13 [Amended] (for Model A340–200 and –300 series Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by airplanes). Accomplishment of the inspection removing Airworthiness Directive (AD) required by paragraph (h) of this AD Title 49 of the United States Code terminates the requirements of this specifies the FAA’s authority to issue 2013–25–08, Amendment 39–17704 (78 paragraph. rules on aviation safety. Subtitle I, FR 78694, December 27, 2013), and (i) If check valves having P/N CAR401 are section 106, describes the authority of adding the following new AD: installed on all three hydraulic systems, the FAA Administrator. ‘‘Subtitle VII: 2016–21–08 Airbus: Amendment 39–18689; before further flight, do the actions specified Aviation Programs,’’ describes in more Docket No. FAA–2016–3701; Directorate in paragraph (g)(2)(i) of this AD. After detail the scope of the Agency’s Identifier 2015–NM–015–AD. accomplishing the actions required by authority. paragraph (g)(2)(i) of this AD, do the actions (a) Effective Date specified in paragraphs (g)(2)(ii) and We are issuing this rulemaking under This AD is effective December 27, 2016. (g)(2)(iii) of this AD at the applicable the authority described in ‘‘Subtitle VII, compliance times specified in those Part A, Subpart III, Section 44701: (b) Affected ADs paragraphs. Accomplishment of the General requirements.’’ Under that This AD replaces AD 2013–25–08, inspection required by paragraph (i) of this section, Congress charges the FAA with Amendment 39–17704 (78 FR 78694, AD terminates the requirements of this promoting safe flight of civil aircraft in December 27, 2013) (‘‘AD 2013–25–08’’). paragraph. air commerce by prescribing regulations (c) Applicability (ii) If check valves having P/N CAR401 are for practices, methods, and procedures not installed on all three hydraulic systems, This AD applies to Airbus airplanes, no further action is required by this the Administrator finds necessary for certificated in any category, as identified in paragraph until any check valve having P/N safety in air commerce. This regulation paragraphs (c)(1) and (c)(2) of this AD. CAR400 is replaced with a check valve is within the scope of that authority (1) Model A330–201, –202, –203, –223, having P/N CAR401. If any check valve because it addresses an unsafe condition –223F, –243, –243F, –301, –302, –303, –321, having P/N CAR400 is replaced by a check that is likely to exist or develop on –322, –323, –341, –342, and –343 airplanes, valve having P/N CAR401, before further products identified in this rulemaking all manufacturer serial numbers except those flight, do the inspection specified in on which Airbus modification 203972 has paragraph (g)(1) of this AD to determine if all action. been embodied in production. three hydraulic systems are equipped with Regulatory Findings (2) Model A340–211, –212, –213, –311, check valves having P/N CAR401. –312, and –313 airplanes, all manufacturer Accomplishment of the inspection required We determined that this AD will not serial numbers. by paragraph (h) of this AD terminates the have federalism implications under (d) Subject requirements of this paragraph. Executive Order 13132. This AD will (2) For airplanes on which Airbus not have a substantial direct effect on Air Transport Association (ATA) of Modification 54491 was embodied in the States, on the relationship between America Code 29, Hydraulic power. production, or Airbus Service Bulletin A330– the national government and the States, (e) Reason 29–3101; or Airbus Service Bulletin A340– or on the distribution of power and This AD was prompted by multiple reports 29–4078 was embodied in service, do the responsibilities among the various of hydraulic line check valves loosening. We actions specified in paragraphs (g)(2)(i), levels of government. are issuing this AD to detect and correct (g)(2)(ii), and (g)(2)(iii) of this AD. For the reasons discussed above, I hydraulic check valve loosening; loosened (i) Except as required by paragraph (g)(1)(i) valves could result in hydraulic leaks, of this AD, at the applicable times specified certify that this AD: in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of 1. Is not a ‘‘significant regulatory possibly leading to the loss of all three hydraulic systems and consequent loss of this AD, as applicable: Do the inspection action’’ under Executive Order 12866; control of the airplane. program (detailed inspection of the lock wire 2. Is not a ‘‘significant rule’’ under the for presence and integrity, a detailed DOT Regulatory Policies and Procedures (f) Compliance inspection for traces of seepage or black (44 FR 11034, February 26, 1979); Comply with this AD within the deposits, and an inspection for proper sradovich on DSK3GMQ082PROD with RULES 3. Will not affect intrastate aviation in compliance times specified, unless already torque) on yellow and blue high pressure Alaska; and done. manifolds, install new lock wires, and do all applicable corrective actions, in accordance 4. Will not have a significant (g) Retained Inspections, With No Changes with the instructions of paragraph 4.1.1 of economic impact, positive or negative, This paragraph restates the requirements of Airbus AOT A330–29A3111, Revision 1, on a substantial number of small entities paragraph (g) of AD 2013–25–08, with no dated October 8, 2009 (for Model A330–200 under the criteria of the Regulatory changes. Except for Model A330–223F and and –300 series airplanes); or Airbus AOT Flexibility Act. A330–243F airplanes: Do the actions A340–29A4086, Revision 1, dated October 8, VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1

Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83651 2009 (for Airbus Model A340–200 and –300 actions before further flight. Accomplishment changes. Within 900 flight hours after series airplanes). Do all applicable corrective of the inspection program required by accomplishment of paragraph (h)(1) of this actions before further flight. Accomplishment paragraph (i) of this AD terminates the AD, do the inspection program (detailed of the inspection required by paragraph (h)(1) requirements of this paragraph. inspection for red mark presence and of this AD terminates the requirements of this alignment integrity of the check valve and (h) Retained Inspection, With No Changes paragraph. manifold, a detailed inspection for traces of (A) For airplanes on which Airbus This paragraph restates the requirements of seepage or black deposits, and an inspection Modification 54491 has been embodied in paragraph (h) of AD 2013–25–08, with no for proper torque) on the green, yellow, and production: At the later of the times specified changes. For airplanes equipped with check blue system check valves, and do all in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) valves having P/N CAR400; and for airplanes applicable corrective actions, in accordance of this AD. equipped with check valves having P/N with the Accomplishment Instructions of (1) Before the accumulation of 1,000 total CAR401, except for airplanes on which Airbus Modification 201384 has been Airbus Mandatory Service Bulletin A330–29– flight cycles since first flight but no earlier 3111, Revision 02, dated June 23, 2011 (for than the accumulation of 700 total flight embodied during production, or on which Airbus Service Bulletin A330–29–3119 (for Model A330–200, –200F, and –300 series cycles since first flight. airplanes); or Airbus Mandatory Service (2) Within 100 flight cycles or 28 days after Model A330–200, –200F, and –300 series airplanes) or Airbus Service Bulletin A340– Bulletin A340–29–4086, Revision 02, dated December 14, 2009 (the effective date of AD 29–4091 (for Model A340–200 and –300 June 23, 2011 (for Model A340–200 and –300 2009–24–09), whichever occurs first. series airplanes) has been embodied in series airplanes). Do all applicable corrective (B) For airplanes on which Airbus Service Bulletin A330–29–3101 or Airbus Service service: Within 900 flight hours after January actions before further flight. Repeat the Bulletin A340–29–4078 was embodied in 31, 2014 (the effective date of AD 2013–25– inspection program thereafter at intervals not service: At the later of the times specified in 08), inspect the check valves on the blue, to exceed 900 flight hours. Accomplishment paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of green, and yellow hydraulic systems to of the actions required by this paragraph this AD. identify their part numbers, in accordance terminates the requirements specified in (1) Within 1,000 flight cycles since the with the Accomplishment Instructions of paragraphs (g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of embodiment of Airbus Service Bulletin Airbus Mandatory Service Bulletin A330–29– this AD. A330–29–3101 or Airbus Service Bulletin 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series (j) Retained Repetitive Inspection for Certain A340–29–4078 but no earlier than 700 flight Airplanes, With No Changes cycles after the embodiment of Airbus airplanes); or Airbus Mandatory Service Service Bulletin A330–29–3101 or Airbus Bulletin A340–29–4086, Revision 02, dated This paragraph restates the requirements of Service Bulletin A340–29–4078. June 23, 2011 (for Model A340–200 and –300 paragraph (j) of AD 2013–25–08, with no (2) Within 100 flight cycles or 28 days after series airplanes). Accomplishment of the changes. For airplanes equipped with check December 14, 2009 (the effective date of AD actions required by this paragraph terminates valves having P/N CAR401 and on which 2009–24–09), whichever occurs first. the requirements specified in paragraphs Airbus Modification 201384 has been (g)(1) and (g)(1)(ii) of this AD. embodied during production, or on which (ii) Within 900 flight hours after (1) If check valves having P/N CAR401 are Airbus Service Bulletin A330–29–3119 (for accomplishment of paragraph (g)(2)(i) of this installed on all three hydraulic systems: Model A330–200, –200F, and –300 series AD, do the inspection program (detailed Before further flight, do the inspection airplanes); or Airbus Service Bulletin A340– inspection of the lock wire for presence and program (detailed inspection for red mark 29–4091 (for Model A340–200 and –300 integrity, a detailed inspection for traces of presence and alignment integrity of the check series airplanes) has been embodied in seepage or black deposits, and an inspection valve and manifold, a detailed inspection for service: Within 1,000 flight hours after for proper torque) and install a new lock wire traces of seepage or black deposits, and an January 31, 2014 (the effective date of AD on the green high pressure manifold; and do inspection for proper torque) on yellow and 2013–25–08), do a general visual inspection an inspection (detailed inspection for traces blue high pressure manifolds, and do all of the green, yellow, and blue high pressure of seepage or black deposits, and detailed applicable corrective actions, in accordance inspection to determine alignment of the manifolds and check valves having P/N with the Accomplishment Instructions of check valve and manifold) on the yellow and CAR401 for any sign of rotation of the check Airbus Mandatory Service Bulletin A330–29– blue high pressure manifolds, and do all valve head, and for any signs of hydraulic 3111, Revision 02, dated June 23, 2011 (for applicable corrective actions; in accordance fluid leakage or seepage (including black Model A330–200, –200F, and –300 series with the instructions of paragraph 4.1.2 of airplanes); or Airbus Mandatory Service deposits), in accordance with the instructions Airbus AOT A330–29A3111, Revision 1, Bulletin A340–29–4086, Revision 02, dated of Airbus Alert Operators Transmission dated October 8, 2009 (for Model A330–200 June 23, 2011 (for Model A340–200 and –300 A29L001–12, dated October 11, 2012. Repeat and –300 series airplanes); or Airbus AOT series airplanes). Accomplishment of the the inspection thereafter at interval not to A340–29A4086, Revision 1, dated October 8, actions required by this paragraph terminates exceed 900 flight hours. 2009 (for Model A340–200 and –300 series the requirements specified in paragraph (k) Retained Corrective Action for Certain airplanes). Do all applicable corrective (g)(2)(i) of this AD. Airplanes, With No Changes actions before further flight. Accomplishment (2) If check valves having P/N CAR401 are of the inspection program required by not installed on all three hydraulic systems, This paragraph restates the requirements of paragraph (i) of this AD terminates the no further action is required by this paragraph (k) of AD 2013–25–08, with no requirements of this paragraph. paragraph until any check valve having P/N changes. If, during any inspection required (iii) Within 900 flight hours after CAR400 is replaced with a check valve by paragraph (j) of this AD, any sign of accomplishment of paragraph (g)(2)(ii) of this having P/N CAR401. If any check valve rotation of the check valve head is found, or AD, and thereafter at intervals not to exceed having P/N CAR400 is replaced by a check any sign of hydraulic fluid leakage or seepage 900 flight hours, do the inspection program valve having P/N CAR401: Before further (including black deposits) is found: Before (detailed inspection for traces of seepage or flight after such replacement, do the actions further flight, do all applicable corrective black deposits, and detailed inspection to specified in paragraph (h) of this AD, to actions, in accordance with the instructions determine alignment of the check valve and determine if all three hydraulic systems are of Airbus Alert Operators Transmission manifold) on the green, yellow, and blue high equipped with check valves having P/N A29L001–12, dated October 11, 2012. pressure manifolds, and do all applicable CAR401. If check valves having P/N CAR401 (l) Retained Provisions Regarding sradovich on DSK3GMQ082PROD with RULES corrective actions, in accordance with the are installed on all three hydraulic systems: instructions of paragraph 4.1.3 of Airbus Terminating Action, With No Changes Before further flight, do the actions specified AOT A330–29A3111, Revision 1, dated in paragraphs (h)(1) and (i) of this AD. This paragraph restates the provisions of October 8, 2009 (for Model A330–200 and paragraph (l) of AD 2013–25–08, with no –300 series airplanes); or Airbus AOT A340– (i) Retained Repetitive Inspection Program changes. Accomplishment of the corrective 29A4086, Revision 1, dated October 8, 2009 and Corrective Actions, With No Changes actions required by this AD does not (for Model A340–200 and –300 series This paragraph restates the requirements of constitute terminating action for the airplanes). Do all applicable corrective paragraph (i) of AD 2013–25–08, with no repetitive inspections required by this AD. VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1

83652 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations (m) Retained Replacement Check Valve (p) New Requirement of This AD: Modify telephone 425–227–1138; fax 425–227–1149. Torque Value, With No Changes Hydraulic Systems Information may be emailed to: 9-ANM-116- This paragraph restates the requirements of Within 36 months after the effective date AMOC-REQUESTS@faa.gov. paragraph (m) of AD 2013–25–08, with no of this AD, modify the green, blue, and (i) Before using any approved AMOC, changes. As of January 31, 2014 (the effective yellow high pressure hydraulic manifolds by notify your appropriate principal inspector, date of AD 2013–25–08), at each replacement replacing each check valve having P/N or lacking a principal inspector, the manager of a check valve with a check valve having CAR401 with an improved check valve of the local flight standards district office/ P/N CAR401, apply a torque of 141 to 143 having P/N CAR402, in accordance with the certificate holding district office. newton meters (N.m) (103.98 to 105.45 Accomplishment Instructions of Airbus (ii) AMOC ANM–116–14–180 R1, dated pounds-foot (lbf.ft)) during installation. Service Bulletin A330–29–3125, Revision 03, February 21, 2014, is approved as an AMOC including Appendixes 01 and 02, dated April for the corresponding provisions of this AD. (n) Retained Credit for Previous Actions, 8, 2016; or Airbus Service Bulletin A340–29– (iii) AMOC ANM–116–14–429, dated With No Changes 4096, Revision 02, including Appendixes 01 September 25, 2014, is not approved as an This paragraph restates the provisions of and 02, dated April 8, 2016; as applicable. AMOC for the corresponding provisions of paragraph (n) of AD 2013–25–08, with no this AD. changes. (q) New Provision of This AD: Terminating Action for Repetitive Inspections (2) Contacting the Manufacturer: As of the (1) This paragraph provides credit for effective date of this AD, for any requirement actions required by paragraph (g)(2)(i) of this Modification of an airplane, as required by in this AD to obtain corrective actions from AD, if those actions were performed before paragraph (p) of this AD, constitutes a manufacturer, the action must be December 14, 2009 (the effective date of AD terminating action for the repetitive accomplished using a method approved by 2009–24–09), using the applicable service inspections required by this AD. the Manager, International Branch, ANM– information specified in paragraphs (n)(1)(i) 116, Transport Airplane Directorate, FAA; or and (n)(1)(ii) of this AD. (r) New Requirement of This AD: Parts Installation Limitations the European Aviation Safety Agency (i) Airbus AOT A330–29A3111, dated (EASA); or Airbus’s EASA Design September 2, 2009 (for Model A330–200 and (1) For an airplane that, as of the effective Organization Approval (DOA). If approved by –300 series airplanes), which is not date of this AD, has a check valve having P/ the DOA, the approval must include the incorporated by reference in this AD. N CAR401 installed, after modification as DOA-authorized signature. (ii) Airbus AOT A340–29A4086, dated required by paragraph (p) of this AD, no (3) Required for Compliance (RC): If any September 2, 2009 (for Model A340–200 and person may install a check valve having P/ –300 series airplanes), which is not service information contains procedures or N CAR401, on that airplane. incorporated by reference in this AD. tests that are identified as RC, those (2) For an airplane that does not have a (2) This paragraph provides credit for procedures and tests must be done to comply check valve having P/N CAR401 installed, as actions required by paragraph (h) of this AD, with this AD; any procedures or tests that are of the effective date of this AD, no person if those actions were performed before not identified as RC are recommended. Those may install a check valve having P/N January 31, 2014 (the effective date of AD CAR401, on that airplane. procedures and tests that are not identified 2013–25–08), using the applicable service as RC may be deviated from using accepted information specified in paragraphs (n)(2)(i) (s) Credit for Previous Actions methods in accordance with the operator’s through (n)(2)(iv) of this AD. This paragraph provides credit for actions maintenance or inspection program without (i) Airbus AOT A330–29A3111, dated required by paragraph (p) of this AD, if those obtaining approval of an AMOC, provided September 2, 2009 (for Model A330–200 and actions were performed before the effective the procedures and tests identified as RC can –300 series airplanes), which is not date of this AD using the applicable service be done and the airplane can be put back in incorporated by reference in this AD. information specified in paragraphs (s)(1) an airworthy condition. Any substitutions or (ii) Airbus AOT A330–29A3111, Revision through (s)(5) of this AD, which are not changes to procedures or tests identified as 1, dated October 8, 2009 (for Model A330– incorporated by reference in this AD. RC require approval of an AMOC. 200 and –300 series airplanes), which is (1) Airbus Service Bulletin A330–29–3125, (u) Related Information incorporated by reference in this AD. dated August 8, 2014. (iii) Airbus AOT A340–29A4086, dated (2) Airbus Service Bulletin A330–29–3125, (1) Refer to Mandatory Continuing September 2, 2009 (for Model A340–200 and Revision 01, including Appendixes 01 and Airworthiness Information (MCAI) EASA –300 series airplanes), which is not 02, dated July 30, 2015. Airworthiness Directive 2015–0009, dated incorporated by reference in this AD. (3) Airbus Service Bulletin A330–29–3125, January 16, 2015, for related information. (iv) Airbus AOT A340–29A4086, Revision Revision 02, including Appendixes 01 and This MCAI may be found in the AD docket 1, dated October 8, 2009 (for Model A340– 02, dated January 21, 2016. on the Internet at http://www.regulations.gov 200 and –300 series airplanes), which is (4) Airbus Service Bulletin A340–29–4096, by searching for and locating Docket No. incorporated by reference in this AD. dated August 8, 2014. FAA–2016–3701. (5) Airbus Service Bulletin A340–29–4096, (2) Service information identified in this (o) Retained Provisions for Reporting, With Revision 01, including Appendixes 01 and AD that is not incorporated by reference is No Changes 02, dated July 30, 2015. available at the addresses specified in This paragraph restates the provisions of paragraphs (v)(6) and (v)(7) of this AD. paragraph (o) of AD 2013–25–08, with no (t) Other FAA AD Provisions (v) Material Incorporated by Reference changes. Although the service information The following provisions also apply to this specified in paragraphs (o)(1) through (o)(5) AD: (1) The Director of the Federal Register of this AD specifies to submit certain (1) Alternative Methods of Compliance approved the incorporation by reference information to the manufacturer, this AD (AMOCs): The Manager, International (IBR) of the service information listed in this does not include that requirement. Branch, ANM–116, Transport Airplane paragraph under 5 U.S.C. 552(a) and 1 CFR (1) Airbus Alert Operators Transmission Directorate, FAA, has the authority to part 51. A29L001–12, dated October 11, 2012. approve AMOCs for this AD, if requested (2) You must use this service information (2) Airbus Mandatory Service Bulletin using the procedures found in 14 CFR 39.19. as applicable to do the actions required by A330–29–3111, Revision 02, dated June 23, In accordance with 14 CFR 39.19, send your this AD, unless this AD specifies otherwise. sradovich on DSK3GMQ082PROD with RULES 2011. request to your principal inspector or local (3) The following service information was (3) Airbus Mandatory Service Bulletin Flight Standards District Office, as approved for IBR on December 27, 2016. A340–29–4086, Revision 02, dated June 23, appropriate. If sending information directly (i) Airbus Service Bulletin A330–29–3125, 2011. to the International Branch, send it to ATTN: Revision 03, including Appendixes 01 and (4) Airbus AOT A330–29A3111, Revision Vladimir Ulyanov, Aerospace Engineer, 02, dated April 8, 2016. 1, dated October 8, 2009. International Branch, ANM–116, Transport (ii) Airbus Service Bulletin A340–29–4096, (5) Airbus AOT A340–29A4086, Revision Airplane Directorate, FAA, 1601 Lind Revision 02, including Appendixes 01 and 1, dated October 8, 2009. Avenue SW., Renton, WA 98057–3356; 02, dated April 8, 2016. VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1

Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83653 (4) The following service information was SUMMARY: We are adopting a new 1200 New Jersey Avenue SE., approved for IBR on January 31, 2014 (78 FR airworthiness directive (AD) for certain Washington, DC 20590. 78694, December 27, 2013). Bombardier, Inc. Model CL–600–2C10 FOR FURTHER INFORMATION CONTACT: (i) Airbus Alert Operators Transmission (Regional Jet Series 700, 701, and 702), A29L001–12, dated October 11, 2012. Cesar Gomez, Aerospace Engineer, (ii) Airbus Mandatory Service Bulletin CL–600–2D15 (Regional Jet Series 705), Airframe and Mechanical Systems A330–29–3111, Revision 02, dated June 23, CL–600–2D24 (Regional Jet Series 900), Branch, ANE–171, FAA, New York 2011. and CL–600–2E25 (Regional Jet Series Aircraft Certification Office, 1600 (iii) Airbus Mandatory Service Bulletin 1000) airplanes. This AD was prompted Stewart Avenue, Suite 410, Westbury, A340–29–4086, Revision 02, dated June 23, by a determination that wear and NY 11590; telephone 516–228–7318; fax 2011. possible leakage of the high-pressure 516–794–5531. (5) The following service information was seal in the cylinder of the No. 3 approved for IBR on December 14, 2009 (74 SUPPLEMENTARY INFORMATION: hydraulic system reservoir could occur FR 62208, November 27, 2009). and cause high hydraulic fluid Discussion (i) Airbus Alert Operators Telex A330– 29A3111, Revision 1, dated October 8, 2009. temperature and/or prevent the system We issued a notice of proposed Only the first page of this document contains from reaching normal operating rulemaking (NPRM) to amend 14 CFR the document number, revision level, and pressure. This AD requires repetitive part 39 by adding an AD that would date; no other pages of this document contain operational checks for wear and leakage apply to certain Bombardier, Inc. Model this information. of the high-pressure seal in the cylinder CL–600–2C10 (Regional Jet Series 700, (ii) Airbus Alert Operators Telex A340– of the reservoir of the No. 3 hydraulic 701, and 702), CL–600–2D15 (Regional 29A4086, Revision 1, dated October 8, 2009. system, and corrective actions if Jet Series 705), CL–600–2D24 (Regional Only the first page of this document contains necessary. We are issuing this AD to the document number, revision level, and Jet Series 900), and CL–600–2E25 address the unsafe condition on these (Regional Jet Series 1000) airplanes. The date; no other pages of this document contain this information. products. NPRM published in the Federal (6) For service information identified in DATES: This AD is effective December Register on July 1, 2016 (81 FR 43122) this AD, contact Airbus SAS—Airworthiness 27, 2016. (‘‘the NPRM’’). The NPRM was Office—EAL, 1 Rond Point Maurice Bellonte, prompted by a determination that wear 31707 Blagnac Cedex, France; telephone +33 The Director of the Federal Register and possible leakage of the high- 5 61 93 36 96; fax +33 5 61 93 45 80; email approved the incorporation by reference pressure seal in the cylinder of the No. airworthiness.A330-A340@airbus.com; of a certain publication listed in this AD 3 hydraulic system reservoir could Internet http://www.airbus.com. as of December 27, 2016. (7) You may view this service information occur and cause high hydraulic fluid at the FAA, Transport Airplane Directorate, ADDRESSES: For service information temperature and/or prevent the system 1601 Lind Avenue SW., Renton, WA. For identified in this final rule, contact from reaching normal operating information on the availability of this Bombardier, Inc., 400 Côte Vertu Road pressure. The NPRM proposed to material at the FAA, call 425–227–1221. West, Dorval, Québec H4S 1Y9, Canada; require repetitive operational checks for (8) You may view this service information Widebody Customer Response Center wear and leakage of the high-pressure that is incorporated by reference at the North America toll-free telephone 1– seal in the cylinder of the reservoir of National Archives and Records 866–538–1247 or direct-dial telephone the No. 3 hydraulic system, and Administration (NARA). For information on 1–514–855–2999; fax 514–855–7401; corrective actions if necessary. We are the availability of this material at NARA, call email ac.yul@aero.bombardier.com; issuing this AD to detect and correct 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibr- Internet http://www.bombardier.com. wear and leakage of the high-pressure locations.html. You may view this referenced service seal in the cylinder of the reservoir of information at the FAA, Transport the No. 3 hydraulic system, which can Issued in Renton, Washington, on October Airplane Directorate, 1601 Lind Avenue result in high hydraulic fluid 12, 2016. SW., Renton, WA. For information on temperature. High hydraulic fluid Michael Kaszycki, the availability of this material at the temperature combined with a Acting Manager, Transport Airplane FAA, call 425–227–1221. It is also temperature transducer malfunction Directorate, Aircraft Certification Service. available on the Internet at http:// could result in un-annunciated [FR Doc. 2016–25745 Filed 11–21–16; 8:45 am] www.regulations.gov by searching for overheating of the hydraulic system and BILLING CODE 4910–13–P and locating Docket No. FAA–2016– consequent ignition sources inside the 7421. fuel tank, which, combined with Examining the AD Docket flammable fuel vapors, could result in a DEPARTMENT OF TRANSPORTATION fuel tank explosion and consequent loss Federal Aviation Administration You may examine the AD docket on of the airplane. the Internet at http:// Transport Canada Civil Aviation 14 CFR Part 39 www.regulations.gov by searching for (TCCA), which is the aviation authority and locating Docket No. FAA–2016– for Canada, has issued Canadian [Docket No. FAA–2016–7421; Directorate 7421; or in person at the Docket Airworthiness Directive CF–2015–27, Identifier 2015–NM–145–AD; Amendment Management Facility between 9 a.m. dated September 14, 2015 (referred to 39–18705; AD 2016–22–16] and 5 p.m., Monday through Friday, after this as the Mandatory Continuing RIN 2120–AA64 except Federal holidays. The AD docket Airworthiness Information, or ‘‘the contains this AD, the regulatory MCAI’’), to correct an unsafe condition sradovich on DSK3GMQ082PROD with RULES Airworthiness Directives; Bombardier, evaluation, any comments received, and for certain Bombardier, Inc. Model CL– Inc. Airplanes other information. The street address for 600–2C10 (Regional Jet Series 700, 701, AGENCY: Federal Aviation the Docket Office (telephone 800–647– and 702), CL–600–2D15 (Regional Jet Administration (FAA), Department of 5527) is Docket Management Facility, Series 705), CL–600–2D24 (Regional Jet Transportation (DOT). U.S. Department of Transportation, Series 900), and CL–600–2E25 (Regional Docket Operations, M–30, West Jet Series 1000) airplanes. The MCAI ACTION: Final rule. Building Ground Floor, Room W12–140, states: VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1


Document Created: 2018-02-14 08:28:58
Document Modified: 2018-02-14 08:28:58
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective December 27, 2016.
ContactVladimir 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.
FR Citation81 FR 83648 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR