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[Federal Register Volume 77, Number 157 (Tuesday, August 14, 2012)]
[Proposed Rules]
[Pages 48469-48473]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-19887]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0808; Directorate Identifier 2010-NM-170-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Airbus Model A330-200 and A330-300 series airplanes, and Model A340-200 
and A340-300 series airplanes. This proposed AD was prompted by reports 
of an elevator blocked in the down position due to two independent 
failures; first, the inability of a servo control to switch to active 
mode because it was not detected by a flight control computer, and 
second, an internal hydraulic leak due to the deterioration of an O-
ring seal on a solenoid. This proposed AD would require, depending on 
airplane configuration, modifying three flight control primary 
computers (FCPCs); modifying two flight control secondary computers 
(FCSCs); revising the airplane flight manual (AFM) to include certain 
information; replacing certain O-rings; and checking part number, and 
replacing certain O-ring seals if needed. We are proposing this AD to 
detect and correct O-rings with incorrect part number whose 
deterioration could lead to improper sealing of solenoid valves, and to 
correct FCPC and FCSC software to allow better control of elevator 
positioning; both conditions, if not corrected, could lead to the loss 
of elevator control on takeoff, and potentially reduce the 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by September 28, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

[[Page 48470]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 227-
1138; fax: (425) 227-1149; email: Vladimir.Ulyanov@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0808; 
Directorate Identifier 2010-NM-170-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2010-0081, dated April 27, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:
    This [EASA] AD deals with the two following points:

     Case of an elevator blocked in down position due to two 
independent failures one of which is hidden:
    Each elevator is controlled by two servo controls. In normal 
operation:

--One servo control in active mode controlled by PRIM 1 (Green servo 
control),
--One servo control in damping mode (Yellow or Blue servo control) 
monitored by PRIM 2.

    Change from active mode to damped mode is obtained by means of a 
mode selector which is controlled by two identical solenoid valves 
housed on the servo control. The sealing of each solenoid valve is 
ensured by four O-ring seals.
    During pre-flight control checks, the flight crew of an A330-200 
aeroplane observed that one of the elevators was blocked in down 
position, the ECAM screen displaying ``F/CTL PRIM 1 PITCH FAULT''.

    This condition was due to two independent failures, one of which 
was dormant, which occurred on one of the elevators.
    Investigations revealed that the origin of the elevator 
malfunction was due to the inability of the Yellow servo control to 
switch to active mode.
    This inability:
--Was caused by an internal hydraulic leak due to the deterioration 
of an O-ring seal on a solenoid valve,
--Was not detected by the PRIM 2 computer nor announced to the 
flight crew.
     Incorrect Part Number (P/N) for solenoid valve O-ring 
seals in IPC [illustrated parts catalog]:
    An incorrect O-ring seal P/N in IPC 27-34-51-1 could have led to 
the installation of O-ring seals incompatible with the hydraulic 
fluid, causing them to deteriorate.
    These conditions if not detected could lead to the loss of 
elevator [control] on takeoff and, potentially reduce the 
controllability of the aeroplane.
    The aim of EASA AD 2007-0009 was to:
--Take over the requirements of AD F-2004-158, and
--Require the terminating action for Sec.  (1), (2) and (4) of this 
AD by introducing new capped seals on solenoid valves for A330-200 
only.
    This new [EASA] AD * * * requires the embodiment of the latest 
software standard on the three Flight Control Primary Computers 
(FCPC) and on the two Flight Control Secondary Computers (FCSC) [by 
modifying the FCPCs and FCSCs] * * *.

    The modification is accomplished either by replacing the FCPCs and 
FCSCs with new FCPCs and FCSCs, or by replacing or reprogramming the 
on-board replaceable modules in the FCPCs and FCSCs. Required actions 
also include, depending on airplane configuration, the following 
actions: revising the airplane flight manual (AFM) to include certain 
information; replacing certain O-rings; and checking part number, and 
replacing certain O-ring seals if needed. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued the following service information:
     Airbus All Operators Telex (AOT) A330-27A3129, Revision 
01, dated July 16, 2004.
     Airbus Mandatory Service Bulletin A330-27-3136, Revision 
01, dated July 19, 2006.
     Airbus Mandatory Service Bulletin A330-27-3146, Revision 
01, dated September 3, 2008.
     Airbus Mandatory Service Bulletin A330-27-3148, Revision 
01, including Appendix 1, dated October 9, 2008.
     Airbus Mandatory Service Bulletin A330-27A3131, Revision 
01, including Appendix 01, dated March 3, 2005.
     Airbus Mandatory Service Bulletin A340-27-4144, including 
Appendix 1, dated October 19, 2009.
     Airbus Mandatory Service Bulletin A340-27-4146, dated June 
1, 2007.
     Airbus Mandatory Service Bulletin A340-27-4148, including 
Appendix 1, dated June 13, 2008.
     Airbus Mandatory Service Bulletin A340-27A4130, Revision 
01, including Appendix 01, dated March 3, 2005.
     Airbus Service Bulletin A330-27-3134, Revision 01, dated 
May 12, 2006.
     Airbus Service Bulletin A330-27-3144, Revision 01, 
including Appendix 1, dated July 16, 2009.
     Airbus Service Bulletin A330-27-3145, dated December 16, 
2008.
     Airbus Service Bulletin A340-27-4145, dated December 16, 
2008.
     Airbus Temporary Revision TR4, Issue 1.0, ``TR 4.02.00/25 
Issue 2--Undetected Elevator Control Loss in Case of Dual Failure,'' 
dated November 26, 2009, to the Airbus A330/A340 Airplane Flight 
Manual.
     Airbus Temporary Revision TR22, Issue 1.0, ``TR 4.02.00/40 
Issue 2--Undetected Elevator Control Loss in Case of Dual Failure,'' 
dated November 26, 2009, to the Airbus A330/A340 Airplane Flight 
Manual.

The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

[[Page 48471]]

Differences Between This AD and the MCAI or Service Information

    EASA AD 2010-0081, dated April 27, 2010, contains additional 
requirements to modify the four elevator servo controls installed on 
Model A330-200 series airplanes, as specified in Airbus Service 
Bulletin A330-27-3134. This AD does not contain those requirements 
because those actions are already mandated by FAA AD 2008-06-07, 
Amendment 39-15419 (73 FR 13103, March 12, 2008; as corrected on April 
15, 2008 (73 FR 20367), and must be accomplished within 17 months after 
April 16, 2008 (the effective date of AD 2008-06-07, Amendment 39-
15419). EASA AD 2010-0081, dated April 27, 2010, also contains 
additional requirements to amend the airplane flight manual to include 
the operational procedure specified in paragraph (n) of this proposed 
AD. This proposed AD does not include that requirement, because that 
information is already contained in the U.S. operators' AFMs.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 41 products of U.S. registry. We also estimate that 
it would take about 5 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $0 per product. Where the 
service information lists required parts costs that are covered under 
warranty, we have assumed that there will be no charge for these costs. 
As we do not control warranty coverage for affected parties, some 
parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $17,425, or $425 per product.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2012-0808; Directorate Identifier 2010-NM-
170-AD.

(a) Comments Due Date

    We must receive comments by September 28, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, specified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A330-201, -202, -203, -223, -243, -301, -302, -303, -
321, -322, -323, -341, -342, and -343 airplanes, all manufacturer 
serial numbers (MSN).
    (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes, 
all MSN.

(d) Subject

    Air Transport Association (ATA) of America Code 27: Flight 
controls.

(e) Reason

    This AD was prompted by reports of an elevator blocked in the 
down position due to two independent failures; first, the inability 
of a servo control to switch to active mode because it was not 
detected by a flight control computer, and second, an internal 
hydraulic leak due to the deterioration of an O-ring seal on a 
solenoid. We are issuing this detect and correct O-rings with 
incorrect part number whose deterioration could lead to improper 
sealing of solenoid valves, and to correct FCPC and FCSC software to 
allow better control of elevator positioning; both conditions, if 
not corrected, could lead to the loss of elevator control on 
takeoff, and potentially reduce the controllability 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) Replace O-ring Seals For Elevator Servo Controls Installed in 
Damping Position on Model A330-200 Series Airplanes Only

    For all Airbus Model A330-200 series airplanes, except those on 
which Airbus modifications 53969 and 54833 have been embodied in 
production: At the later of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD, replace the O-ring seals installed on the two 
solenoid valves of each servo control using new O-ring seals, in 
accordance with Airbus All Operators Telex (AOT) A330-27A3129, 
Revision 01, dated July 16, 2004.
    (1) Before the accumulation of 3,000 flight cycles by the servo 
control since first installation on an airplane, or 3,000 flight 
cycles since the installation of the solenoid valve on the servo 
control.
    (2) Within 700 flight hours after the effective date of this AD.

(h) Replace O-ring Seals on Spare Elevator Servo Controls Whose O-ring 
Seals Were Not Replaced as Required by Paragraph (g) of This AD

    For all Airbus Model A330-200 series airplanes, except those on 
which Airbus modifications 53969 and 54833 have been embodied in 
production: As of the effective date of this AD, before the 
installation of an elevator servo control on an Airbus Model A330-
200 airplane, replace the O-ring seals installed on the two spare 
servo control solenoid valves using new O-ring seals, in accordance 
with Airbus AOT A330-27A3129, Revision 01, dated July 16, 2004.

[[Page 48472]]

(i) Replace O-ring Seals with Part Number (P/N) MS28775-XXX or a Part 
Number That Cannot Be Identified

    For Model A330-200 series airplanes which have been modified as 
specified in Airbus AOT A330-27A3129, dated June 24, 2004, but which 
have not been modified as specified in Airbus AOT A330-27A3129, 
Revision 01, dated July 16, 2004; except those airplanes on which 
Airbus modifications 53969 and 54833 have been embodied in 
production: Within 15 days after the effective date of this AD, 
check the (P/N) of the seals installed on the solenoid valve of the 
servo control of the elevator in the damping position. If the seals 
installed have P/N MS28775-XXX or a part number that cannot be 
identified, before further flight, replace the seals with new seals 
using a part number listed in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD, in accordance with Airbus AOT A330-27A3129, Revision 01, 
dated July 16, 2004.
    (1) IPC 27-34-51-1 item 130: NAS1611-011 or NAS1611-011A;
    (2) IPC 27-34-51-1 item 140: NAS1611-012 or NAS1611-012A; or
    (3) IPC 27-34-51-1 item 150: NAS1611-013 or NAS1611-013A.

(j) Replace O-ring Seals on Model A330-200, A330-300, A340-200, and 
A340-300 Series Airplanes

    For Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes equipped with elevator servo controls P/N SC4800-2/-4/-7/-
8 or SC4800-7/-8 modified into P/N SC4800-7A/-9, as specified in 
Airbus Service Bulletin A340-27-4083 or Airbus Service Bulletin 
A330-27-3076: Within 1,400 flight hours after the effective date of 
this AD, replace the O-ring seals installed on the two solenoid 
valves of each elevator servo control in damping position (except 
for Model A330-200 series airplanes which have to comply with 
paragraph (g) of this AD), and in active position, using a new O-
ring seal P/N NAS1611-XXX or P/N NAS1611-XXXA, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27A3131, Revision 01, excluding Appendix 01, dated March 3, 
2005 (for Model A330 series airplanes); or Airbus Mandatory Service 
Bulletin A340-27A4130, Revision 01, excluding Appendix 01, dated 
March 3, 2005 (for Model A340 series airplanes).

(k) Replace O-ring Seals on Spare Elevator Servo Controls on Model 
A330-200, A330-300, A340-200, and A340-300 Series Airplanes

    For the spare elevator servo controls P/N SC4800-2/-4/-7/-8 or 
SC4800-7/-8 modified into P/N SC4800-7A/-9, as specified in Airbus 
Service Bulletin A340-27-4083 or Airbus Service Bulletin A330-27-
3076: Before the installation of a spare elevator servo control on 
an airplane, replace the O-ring seals installed on the two spare 
servo control solenoid valves using a new O-ring seal P/N NAS1611-
XXX or P/N NAS1611-XXXA, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27A3131, 
Revision 01, excluding Appendix 01, dated March 3, 2005 (for Model 
A330 series airplanes); or Airbus Mandatory Service Bulletin A340-
27A4130, Revision 01, excluding Appendix 01, dated March 3, 2005 
(for Model A340 series airplanes).

(l) Modify the Flight Control Primary Computers (FCPCs)

    For all Airbus Model A330-200 and A330-300 series airplanes, 
except those on which both Airbus modifications 53468 and 55697 have 
been embodied in production; and for all Airbus Model A340-200 and 
A340-300 series airplanes, except those on which both modifications 
55879 and 55697 have been embodied in production: Within 24 months 
after the effective date of this AD, modify the three FCPCs in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraphs (l)(1) or (l)(2) of this 
AD.
    (1) Airbus Service Bulletin A330-27-3144, Revision 01, excluding 
Appendix 1, dated July 16, 2009; or Airbus Mandatory Service 
Bulletin A330-27-3148, Revision 01, excluding Appendix 1, dated 
October 9, 2008 (for Model A330 series airplanes).
    (2) Airbus Mandatory Service Bulletin A340-27-4144, excluding 
Appendix 1, dated October 19, 2009; or Airbus Mandatory Service 
Bulletin A340-27-4148, excluding Appendix 1, dated June 13, 2008 
(for Model A340 series airplanes).

(m) Modify the Flight Control Secondary Computers (FCSCs)

    For all Airbus Model A330-200 and A330-300 series airplanes, 
except those on which both Airbus modifications 53468 and 55697 have 
been embodied in production, and for all Airbus Model A340-200 and 
A340-300 series airplanes, except those on which both modifications 
55879 and 55697 have been embodied in production: Within 24 months 
after the effective date of this AD, modify both FCSCs, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraphs (m)(1) or (m)(2) of this 
AD.
    (1) Airbus Mandatory Service Bulletin A330-27-3146, Revision 01, 
dated September 3, 2008; or Airbus Service Bulletin A330-27-3145, 
dated December 16, 2008 (for Model A330 airplanes).
    (2) Airbus Mandatory Service Bulletin A340-27-4146, June 1, 
2007; or Airbus Service Bulletin A340-27-4145, dated December 16, 
2008 (for Model A340 airplanes).

(n) Revise the Airplane Flight Manual

    Before further flight, after doing the applicable actions 
required by both paragraphs (l) and (m) of this AD, remove the 
following procedure from the airplane flight manual, if inserted, in 
accordance with the instructions contained in Airbus Temporary 
Revision TR4, Issue 1.0, ``TR 4.02.00/25 Issue 2--Undetected 
Elevator Control Loss in Case of Dual Failure,'' dated November 26, 
2009, to the Airbus A330/A340 Airplane Flight Manual; and Airbus 
Temporary Revision TR22, Issue 1.0, ``TR 4.02.00/40 Issue 2--
Undetected Elevator Control Loss in Case of Dual Failure,'' dated 
November 26, 2009, to the Airbus A330/A340 Airplane Flight Manual.

Undetected Elevator Control Loss in Case of Dual Failure

    On ground, before takeoff until takeoff power thrust setting, 
apply the following procedure.
     In the case of a F/CTL PRIM 1 FAULT, or F/CTL PRIM 1 
PITCH FAULT: Turn off PRIM 1, then back on to perform a FCPC PRIM 1 
reset.
     If successful: Perform the normal pre-flight Flight 
Control check.
     If unsuccessful: Return to the gate and require 
appropriate maintenance actions.
     In the case of a F/CTL ELEV SERVO FAULT: Return to the 
gate and require appropriate maintenance actions.

(o) Credit for Previous Actions

    This paragraph provides credit for certain actions described in 
the following paragraphs.
    (1) This paragraph provides credit for replacements of the O-
ring seals, as required by paragraphs (j) and (k) of this AD, if 
those actions were performed before the effective date of this AD 
using Airbus Service Bulletin A330-27A3131, dated September 22, 2004 
(for Model A330 airplanes); or Airbus Service Bulletin 340-27A4130, 
dated September 22, 2004 (for Model A340 airplanes).
    (2) This paragraph provides credit for modifications of the 
FCPC, as required by paragraph (l) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-27-3144, dated April 2, 2009 (for Model A330 
airplanes); or Airbus Service Bulletin A340-27-3148, dated July 17, 
2008 (for Model A340 airplanes).
    (3) This paragraph provides credit for modifications of the 
FCSCs, as required by paragraph (m) of this AD, if those actions 
were performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A330-27-3146, dated June 1, 2007 (for 
Model A330 airplanes).

(p) Terminating Action

    Installation of modified servo-controls at all positions on 
Model A330-200 airplanes in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-27-3134, Revision 01, 
dated May 12, 2006; and Airbus Mandatory Service Bulletin A330-27-
3136, Revision 01, dated July 19, 2006; terminates the actions 
required by paragraphs (g), (h), and (i) and of this AD.

(q) 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, 
Washington 98057-

[[Page 48473]]

3356; telephone (425) 227-1138; fax (425) 227-1149. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) 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.

(r) Related Information

    (1) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0081, dated April 27, 2010, and the 
service information specified in paragraphs (r)(1)(i) through 
(r)(1)(xv) of this AD, for related information.
    (i) Airbus AOT A330-27A3129, Revision 01, dated July 16, 2004.
    (ii) Airbus Mandatory Service Bulletin A330-27-3136, Revision 
01, dated July 19, 2006.
    (iii) Airbus Mandatory Service Bulletin A330-27-3146, Revision 
01, dated September 3, 2008.
    (iv) Airbus Mandatory Service Bulletin A330-27-3148, Revision 
01, excluding Appendix 1, dated October 9, 2008.
    (v) Airbus Mandatory Service Bulletin A330-27A3131, Revision 01, 
excluding Appendix 01, dated March 3, 2005.
    (vi) Airbus Mandatory Service Bulletin A340-27-4144, excluding 
Appendix 1, dated October 19, 2009.
    (vii) Airbus Mandatory Service Bulletin A340-27-4146, dated June 
1, 2007.
    (viii) Airbus Mandatory Service Bulletin A340-27-4148, excluding 
Appendix 1, dated June 13, 2008.
    (ix) Airbus Mandatory Service Bulletin A340-27A4130, Revision 
01, excluding Appendix 01, dated March 3, 2005.
    (x) Airbus Service Bulletin A330-27-3134, Revision 01, dated May 
12, 2006.
    (xi) Airbus Service Bulletin A330-27-3144, Revision 01, 
excluding Appendix 1, dated July 16, 2009.
    (xii) Airbus Service Bulletin A330-27-3145, dated December 16, 
2008.
    (xiii) Airbus Service Bulletin A340-27-4145, dated December 16, 
2008.
    (xiv) Airbus Temporary Revision TR4, Issue 1.0, ``TR 4.02.00/25 
Issue 2--Undetected Elevator Control Loss in Case of Dual Failure,'' 
dated November 26, 2009, to the Airbus A330/A340 Airplane Flight 
Manual.
    (xv) Airbus Temporary Revision TR22, Issue 1.0, ``TR 4.02.00/40 
Issue 2--Undetected Elevator Control Loss in Case of Dual Failure,'' 
dated November 26, 2009, to the Airbus A330/A340 Airplane Flight 
Manual.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on August 3, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-19887 Filed 8-13-12; 8:45 am]
BILLING CODE 4910-13-P
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