[Federal Register Volume 78, Number 77 (Monday, April 22, 2013)]
[Proposed Rules]
[Pages 23686-23688]
[FR Doc No: 2013-09414]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0353; Directorate Identifier 2008-SW-029-AD]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Helicopters

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
certain Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1,
AS332L2, and EC225LP helicopters to require inspecting for the presence
of blind holes in the tail gearbox (TGB) attachment fittings, and, if
they are missing, installing an additional washer under the head of the
attachment bolt until the attachment fitting is replaced with an
airworthy attachment fitting. This proposed AD was prompted by the
discovery of interference between the TGB aft attachment bolt and the
structure fitting, caused by a manufacturing anomaly that omitted the
blind hole required for proper fit of the attachment bolt. This
condition, if not detected and corrected, could result in insufficient
tightening of the TGB casing, damage to the TGB attachment, cracking
under the attachment bolt, and loss of the TGB, resulting in loss of
control of the helicopter.

DATES: We must receive comments on this proposed AD by June 21, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
     Fax:<PHONE_NUMBER>.
     Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (telephone<PHONE_NUMBER>) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
    For service information identified in this proposed AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at http://www.eurocopter.com/techpub. You may review a copy of the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, TX 76137; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this

document. The most helpful comments reference a specific portion of the
proposal, explain the reason for any recommended change, and include
supporting data. To ensure the docket does not contain duplicate
comments, commenters should send only one copy of written comments, or
if comments are filed electronically, commenters should submit only one
time.
    We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.

Discussion

    The Direction G[eacute]n[eacute]rale de L'Aviation Civile France
(DGAC), the aviation authority for France, has issued DGAC AD No. F-
2007-027, dated January 2, 2008 (F-2007-027), to correct an unsafe
condition for certain Eurocopter AS332 series and EC225 LP helicopters.
The DGAC advises that during a scheduled maintenance check, a
helicopter was discovered to have interference between the threaded
section of the aft attachment bolt and the structure fitting. The
interference is because of a manufacturing anomaly in the fittings that
omitted the blind hole for bolt clearance in the structure fitting.
Interference from this missing blind hole does not permit correct axial
tightening of the TGB casing, even if the correct torque load is
applied to the attachment bolt. Insufficient tightening of the bolt can
damage the TGB attachment and initiate a crack under the head of the
attachment bolt. This condition, if not corrected, could result in loss
of the TGB and subsequent loss of control of the helicopter.

FAA's Determination

    These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, DGAC, which is the production
oversight authority for France, has notified us of the unsafe condition
described in its AD. We are proposing this AD because we evaluated all
known relevant information and determined that an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.

Related Service Information

    Eurocopter has issued one Emergency Alert Service Bulletin (EASB),
Revision 1, dated January 4, 2008, with four different numbers. EASB
No. 53.01.58 is for the Model AS332 series helicopters; EASB No.
53.00.58 is for the Model AS532 series helicopters, which are not FAA
type certificated; EASB No. 53A012 is for the Model EC225LP helicopter;
and EASB No. 53A011 is for the Model EC 725AP helicopter, which is not
FAA type certificated. The EASB specifies inspecting the forward and
aft attachment fittings for proper depth of the bolt holes. If the bolt
holes are less than the minimum depth, the EASB specifies checking the
condition of the bolt. If there are no signs of chafing or contact, the
EASB calls for adding an additional washer to the bolt and reinstalling
the bolt in the TGB attachment fitting. If there are signs of chafing
or contact, the EASB requires replacing the bolt with an airworthy bolt
and two washers. The DGAC classified this EASB as mandatory and issued
F-2007-027 to ensure the continued airworthiness of these helicopters.

Proposed AD Requirements

    This proposed AD would require, within 50 hours time-in-service,
inspecting the TGB aft and forward attachment fittings for the presence
of a blind hole and measuring the depth. If the measurement is equal to
or greater than 81 mm, no action would be necessary. If the measurement
is less than 81 mm, the proposed AD would require inspecting the
attachment bolts for chafing or contact marks. If there is no chafing
or marks, the proposed AD would require reinstalling each bolt with an
additional washer. If there is chafing or contact marks, the proposed
AD would require replacing each bolt with an airworthy bolt and an
additional washer.

Costs of Compliance

    We estimate that this proposed AD would affect six helicopters of
U.S. registry. Based on an average estimated labor cost of $85 per
work-hour, we estimate the following costs:
     Inspecting the TGB for the presence of a blind hole would
require 0.50 work-hour for a labor cost of about $43. No parts would be
needed, so the cost would total $43 per helicopter, or $258 for the
fleet.
     Replacing bolts and adding a second washer if needed would
require 0.50 work-hour for a labor cost of about $43. Parts would cost
about $200 for three replacement bolts and the washers for a total cost
of $243 per helicopter.
     Replacing the TGB attachment fitting with an airworthy
fitting would require 40 work-hours for a labor cost of $3,400. Parts
would cost about $1,921 for a total cost of $5,321 per helicopter.

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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; 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 an economic 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

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 adding the following new Airworthiness
Directive (AD):

Eurocopter France Helicopters: Docket No. FAA-2013-0353; Directorate
Identifier 2008-SW-029-AD.

(a) Applicability

    This AD applies to Eurocopter France (Eurocopter) models AS332C,
AS332L, AS332L1, AS332L2, and EC225LP helicopters, serial numbers
(S/N) up to and including 2680 and S/N 9000 through 9009,
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as interference between the
tail gearbox (TGB) attachment bolt and the structure fitting. This
condition could result in insufficient tightening of the TGB casing,
damage to the TGB attachment, cracking under the attachment bolt,
loss of the TGB and consequently, loss of helicopter control.

(c) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

(d) Required Actions

    Within 50 hours time-in-service (TIS):
    (1) Inspect the TGB aft attachment fitting to measure the
dimension for a blind hole as follows:
    (i) Remove the TGB attachment bolt (c) but retain washer (d) as
depicted in Detail A, Figure 1, of Eurocopter Emergency Alert
Service Bulletin (EASB) No. 53.01.58 and EASB No. 53A012, both
Revision 1, and both dated January 4, 2008.
    (ii) Use a depth gauge to measure dimension ``x'' between the
top face of the washer (d) and the bottom of aft fitting (a) as
depicted in Detail A, Figure 1, of the EASB.
    (2) If the measurement is equal to or greater than 81 mm, then
the blind hole is present. Install the TGB attachment bolt (c) with
its washer (d) as depicted in Detail A, Figure 1, of the EASB. Lock
with lockwire.
    (3) If the measurement is less than 81 mm, then the blind hole
is missing. Inspect the end of the threaded section of bolt (c) for
chafing or a contact mark, as depicted in Area 1, Figure 1, of the
EASB.
    (i) If there is no chafing and no contact marks, install bolt
(c) with washer (d) and additional washer (2) as depicted in Detail
B, Figure 1, of the EASB.
    (ii) If there is chafing or a contact mark, replace the TGB
attachment bolt (c) with an airworthy bolt and install with washer
(d) and additional washer (2) as depicted in Detail B, Figure 1, of
the EASB. Lock with lockwire.
    (iii) Within the next 825 hours TIS, replace the TGB aft
attachment fitting with an airworthy attachment fitting.
    (4) Inspect the right and left attachment points of the TGB
forward attachment to measure the dimension for a blind hole, as
follows:
    (i) Remove both TGB attachment bolts (c) but retain washers (d),
as depicted in Detail A, Figure 2, of the EASB.
    (ii) Use a depth gauge to measure dimension ``x'' between the
top face of washer (d) and the bottom of forward fitting (b) at the
right and left attachment points, as depicted in Detail A, Figure 2,
of the EASB.
    (5) If both measurements are equal to or greater than 81 mm,
then the blind hole is present. Install TGB attachment bolt (c) with
its washer (d), as depicted in Detail A, Figure 2, of the EASB. Lock
with lockwire.
    (6) If one or both measurements are less than 81 mm, then the
blind hole is missing. Inspect the end of the threaded section of
each bolt (c) for chafing or a contact mark, as depicted in Area 1,
Figure 2 of the EASB.
    (i) If there is no chafing and no contact marks, for each
attachment point, install bolt (c) with washer (d) and additional
washer (2), as depicted in Detail B, Figure 2, of the EASB.
    (ii) If there is chafing or a contact mark, replace each the TGB
attachment bolt (c) with an airworthy bolt and install bolt (1) with
washer (d) and additional washer (2), as depicted in Detail B,
Figure 2, of the EASB. Lock with lockwire.
    (iii) Within the next 825 hours TIS, replace the TGB forward
attachment fitting with an airworthy attachment fitting.

 (e) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Gary Roach, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(f) Additional Information

    The subject of this AD is addressed in the Direction
G[eacute]n[eacute]rale de L'Aviation Civile France AD No F-2007-027,
dated January 2, 2008.

(g) Subject

    Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor
Gearbox.

    Issued in Fort Worth, Texas, on April 11, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-09414 Filed 4-19-13; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 77, Number 211 (Wednesday, October 31, 2012)]
[Rules and Regulations]
[Pages 65799-65801]
[FR Doc No: 2012-26171]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0596; Directorate Identifier 2011-NM-245-AD;
Amendment 39-17236; AD 2012-21-20]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200 freighter series airplanes, Model A330-200 and -
300 series airplanes, and Model A340-200, -300, -500, and -600 series
airplanes. This AD was prompted by reports of the ram air turbine (RAT)
not deploying when tested. This AD requires identification of the
supplier, part number, and serial number of the installed RAT actuator,
and re-identification of the actuator and RAT, or replacement of the
RAT actuator with a serviceable unit and re-identification of the RAT,
if necessary. We are issuing this AD to prevent non-deployment of the
RAT, which if occurred following a total engine flame-out, or during a
total loss of normal electrical power generation, could result in
reduced control of the airplane.

DATES: This AD becomes effective December 5, 2012.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 5,
2012.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA 1601
Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 227-
1138; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 18, 2012 (77 FR
36209). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:

    During a production test flight, a Ram Air Turbine (RAT) did not
deploy when tested. An investigation, conducted by the RAT
manufacturer Hamilton Sundstrand (HS) and Arkwin Industries,
revealed that the RAT did not deploy due to insufficient stroke
inside one of the actuator deployment solenoids.
    This condition, if occurring following a total engine flame out,
or during a total loss of normal electrical power generation, could
possibly result in reduced control of the aeroplane.
    For the reasons described above, this [European Aviation Safety
Agency] AD requires the modification of the affected RAT actuator
deployment mechanism, or replacement of the RAT actuator with a
modified unit.

The required actions include identification of the supplier, part
number, and serial number of the installed RAT actuator, and re-
identification of the actuator and RAT, or replacement of the RAT
actuator with a serviceable unit and re-identification of the RAT, if
necessary. You may obtain further information by examining the MCAI in
the AD docket.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (77 FR 36209, June 18,
2012) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed--except for
minor editorial changes and re-identification of the sub-paragraphs of
paragraphs (g) and (h) of this final rule. We have determined that
these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (77 FR 36209, June 18, 2012) for correcting the unsafe condition;
and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 36209, June 18, 2012).

Costs of Compliance

    We estimate that this AD will affect 56 products of U.S. registry.
We also estimate that it will take about 14 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will 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 parts. 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 this AD to the U.S. operators
to be $66,640, or $1,190 per product.
    In addition, we estimate that any necessary follow-on actions would
take about 13 work-hours and require parts costing $0, for a cost of
$1,105 per product. We have no way of determining the number of
products that may need these actions.

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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

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 the NPRM (77 FR 36209, June 18, 2012),
the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

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 adding the following new AD:

2012-21-20 Airbus: Amendment 39-17236. Docket No. FAA-2012-0596;
Directorate Identifier 2011-NM-245-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 5,
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -223F -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
all manufacturer serial numbers (MSN); except those on which Airbus
modification 201043 has been embodied in production.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes, all MSN; except those on which Airbus
modification 201043 or 201042 has been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 29: Hydraulic
Power.

(e) Reason

    This AD was prompted by reports of the ram air turbine (RAT) not
deploying when tested. We are issuing this AD to prevent non-
deployment of the RAT, which if occurred following a total engine
flame-out, or during a total loss of normal electrical power
generation, could result in reduced control of the airplane.

(f) Compliance

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

(g) Identification and Replacement for Certain Airbus Model A330, and
A340-200 and -300 Airplanes

    For Airbus Model A330-200 freighter series airplanes, Model
A330-200 and -300 series airplanes, and Model A340-200 and -300
series airplanes: Within 15,000 flight hours or 36 months, whichever
occurs first after the effective date of this AD, identify the
supplier, part number (P/N), and serial number (S/N) of the
installed RAT actuator, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-29-3114,
dated May 18, 2011 (for Model A330-200 freighter series airplanes,
and Model A330-200 and -300 series airplanes); or Airbus Mandatory
Service Bulletin A340-29-4089, dated May 18, 2011 (for Model A340-
200 and -300 series airplanes).
    (1) If the supplier identified is Arkwin, and the identified
actuator part number and serial number are listed as already
modified in Hamilton Sundstrand Service Bulletin ERPS06M-29-18,
dated March 8, 2011, but not yet re-identified: Before further
flight, re-identify the actuator and the RAT, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-29-3114, dated May 18, 2011 (for Model A330-200 freighter
series airplanes, and Model A330-200 and -300 series airplanes); or
Airbus Mandatory Service Bulletin A340-29-4089, dated May 18, 2011
(for Model A340-200 and -300 series airplanes).
    (2) If the supplier identified is Arkwin Industries and the
identified actuator part number and serial number are listed as not
modified as specified in Hamilton Sundstrand Service Bulletin
ERPS06M-29-18, dated March 8, 2011: Before further flight, replace
the RAT actuator with a serviceable unit, and re-identify the RAT,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-29-3114, dated May 18, 2011 (for
Model A330-200 freighter series airplanes, and Model A330-200 and -
300 series airplanes); or Airbus Mandatory Service Bulletin A340-29-
4089, dated May 18, 2011 (for Model A340-200 and -300 series
airplanes).

(h) Identification and Replacement for Certain Airbus Model A340-500
and -600 Airplanes

    For Model A340-500 and -600 airplanes: Within 15,000 flight
hours or 36 months, whichever occurs first after the effective date
of this AD, identify the part number and serial number of the
installed RAT actuator, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A340-29-5018,
dated May 18, 2011.
    (1) If the identified actuator part number and serial number are
listed as already modified as specified in Hamilton Sundstrand
Service Bulletin ERPS33T-29-5, dated March 8, 2011, but not yet re-
identified: Before further flight, re-identify the actuator and the
RAT, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A340-29-5018, dated May 18, 2011.
    (2) If the identified actuator part number and serial number are
listed as not modified as specified in Hamilton Sundstrand Service
Bulletin ERPS33T-29-5, dated March 8, 2011: Before further flight,
replace the RAT actuator with a serviceable unit, and re-identify
the RAT, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A340-29-5018, dated May 18, 2011.

(i) Parts Installation Limitations

    (1) As of the effective date of this AD, no person may install
any RAT actuator having P/N 5912958 or P/N 1211575-001, or any RAT
having P/N 1702934A having a serial number listed as affected in
Hamilton Sundstrand Service Bulletin ERPS06M-29-18, dated March 8,
2011, on any airplane, unless the RAT actuator has been replaced
with a serviceable unit and the RAT has been re-identified, as
applicable, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-29-3114, dated May 18, 2011
(for Model A330-200 freighter series airplanes, and Model A330-200
and -300 series airplanes); or Airbus Mandatory Service Bulletin
A340-29-4089, dated May 18, 2011 (for Model A340-200 and -300 series
airplanes).
    (2) As of the effective date of this AD, no person may install
any RAT actuator having P/N 5912536 or P/N 1211526-002, or any RAT
having P/N 772722F having a serial number listed as affected in
Hamilton Sundstrand Service Bulletin ERPS33T-29-5, dated March 8,
2011, on any airplane, unless the RAT actuator has been replaced
with a serviceable unit and the RAT has been re-identified, as
applicable, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A340-29-5018, dated May 18, 2011.

(j) 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 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be emailed to<EMAIL_ADDRESS>
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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0204, dated October 14, 2011, and the service
information specified in paragraphs (k)(1), (k)(2), (k)(3), (k)(4),
and (k)(5) of this AD, for related information.
    (1) Airbus Mandatory Service Bulletin A330-29-3114, dated May
18, 2011.
    (2) Airbus Mandatory Service Bulletin A340-29-4089, dated May
18, 2011.
    (3) Airbus Mandatory Service Bulletin A340-29-5018, dated May
18, 2011.
    (4) Hamilton Sundstrand Service Bulletin ERPS06M-29-18, dated
March 8, 2011.
    (5) Hamilton Sundstrand Service Bulletin ERPS33T-29-5, dated
March 8, 2011.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A330-29-3114, dated May
18, 2011.
    (ii) Airbus Mandatory Service Bulletin A340-29-4089, dated May
18, 2011.
    (iii) Airbus Mandatory Service Bulletin A340-29-5018, dated May
18, 2011.
    (iv) Hamilton Sundstrand Service Bulletin ERPS06M-29-18, dated
March 8, 2011.
    (v) Hamilton Sundstrand Service Bulletin ERPS33T-29-5, dated
March 8, 2011.
    (3) For Airbus 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_ADDRESS>
Internet http://www.airbus.com. For Hamilton Sunstrand service
information identified in this AD, contact Hamilton Sundstrand,
Technical Publications, Mail Stop 302-9, 4747 Harrison Avenue, P.O.
Box 7002, Rockford, Illinois 61125-7002; telephone<PHONE_NUMBER>; fax
860-998-4564; email<EMAIL_ADDRESS>Internet http://www.hamiltonsundstrand.com.
    (4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call<PHONE_NUMBER>.
    (5) 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<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 12, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-26171 Filed 10-30-12; 8:45 am]
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