Airworthiness Directives; Airbus Airplanes, 3513-3516 [2015-00961]
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Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
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.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0068, dated
March 18, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2014–1043.
(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 https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on January
11, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–00993 Filed 1–22–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0076; Directorate
Identifier 2013–NM–246–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A330–200, A330–200
Freighter, and A330–300 series
airplanes; and Airbus Model A340–200,
A340–300, A340–500, and A340–600
series airplanes. This proposed AD was
prompted by a report that, during a
production flight test, the ram air
turbine (RAT) did not pressurize the
green hydraulic system. For certain
airplanes, this proposed AD would
require identification of the part
number, serial number, and standard of
the RAT pump, RAT module, RAT
actuator, and RAT lower gearbox
assembly; replacement of the balance
weight screw, modification of the
emcdonald on DSK67QTVN1PROD with PROPOSALS
SUMMARY:
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actuator coil spring, modification of the
actuator, an inspection of the anti-stall
valve for correct installation in the RAT
pump housing; and corrective actions if
necessary. For certain other airplanes,
this proposed AD would require reidentification or replacement of the RAT
module. We are proposing this AD to
prevent loss of the impeller function
and RAT pump pressurization
capability, which, if preceded by a total
engine flame-out, could result in the
loss of control of the airplane.
DATES: We must receive comments on
this proposed AD by March 9, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 Airbus 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.A330A–340@
airbus.com; Internet https://
www.airbus.com. For Hamilton
Sundstrand service information
identified in this proposed AD, contact
Hamilton Sundstrand, Technical
Publications, Mail Stop 302–9, 4747
Harrison Avenue, P.O. Box 7002,
Rockford, IL 61125–7002; telephone
860–654–3575; fax 860–998–4564; email
tech.solutions@hs.utc.com; Internet
https://www.hamiltonsundstrand.com.
You may view the 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0076; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
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regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM 116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–0076; Directorate Identifier
2013–NM–246–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 https://
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
Union, has issued EASA Airworthiness
Directive 2013–0274, dated November
15, 2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200, A330–200 Freighter,
and A330–300 series airplanes; and
Airbus Model A340–200, A340–300,
A340–500, and A340–600 series
airplanes. The MCAI states:
During a production flight test of an A330–
300 aeroplane, the Ram Air Turbine (RAT)
did not pressurize the green hydraulic
system. Investigation revealed that the
impeller drive (hex) shaft had a reduced
length of engagement with the pump drive
shaft. This caused the impeller drive shaft to
disengage from the pump and disconnect the
impeller. It was determined that the
disconnection was the result of internal hex
dimensions on the pump impeller shaft,
which had been changed in a manufacturing
drawing. From the investigation analysis, it
was possible to identify a list of affected
parts.
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Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
This condition, if not detected and
corrected, could lead to the loss of impeller
function and RAT pump pressurization
capability, possibly resulting, in case of total
engine flame out, to the loss of control of the
aeroplane.
To address this unsafe condition, a new
design RAT pump shaft has been developed
with a decreased hexagonal shaft housing
depth, which increases the hexagonal drive
shaft engagement in the impeller shaft to
carry the impeller torque. Airbus issued
Service Bulletin (SB) A330–29–3122, SB
A340–29–4093 and SB A340–29–5021 to
provide instructions for in-service
replacement of the affected RAT hydraulic
pumps, or re-identification of the RAT pump
and complete RAT module, as applicable.
For the reasons described above, this
[EASA] AD requires identification and
replacement [modification] or reidentification of all affected RAT hydraulic
pumps on A330 and A340–200/300
aeroplanes, and replacement [modification]
of all affected RAT modules on A340–500/600 aeroplanes.
emcdonald on DSK67QTVN1PROD with PROPOSALS
For affected pumps, the required actions
also include concurrent actions, as
applicable, including replacement of the
balance weight screw, modification of
the actuator coil spring, modification of
the actuator, an inspection of the antistall valve for correct installation in the
RAT pump housing and re-installation
if necessary. For affected pumps,
corrective actions include replacement
of the RAT hydraulic pump, and reidentification of the part number of the
RAT module. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–0076.
Related ADs
EASA and the FAA have issued
additional ADs related to the RAT. FAA
AD 2012–21–19, Amendment 39–17235
(77 FR 65812, October 31, 2012), which
corresponds to EASA AD 2011–0197,
dated October 10, 2011, requires an
inspection of the RAT anti-stall valve in
the pump housing for correct setting, reidentification of the RAT pump,
performing a functional ground test of
the RAT, and replacement of the RAT
pump or the RAT assembly with a
serviceable part if necessary. FAA AD
2012–21–19 is applicable to all Airbus
Model A330–200 freighter series
airplanes; Model A330–200 and -300
series airplanes; and Model A340–200
and -300 series airplanes.
The FAA also issued AD 2012–21–20,
Amendment 39–17236 (77 FR 65799,
October 31, 2012), which corresponds to
EASA AD 2011–0204, dated October 14,
2011. FAA AD 2012–21–20 requires
identification of the supplier, part
number, and serial number of the RAT
actuator, and re-identification of the
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RAT actuator and RAT, or replacement
of the RAT actuator with a serviceable
unit and re-identification of the RAT, if
necessary. FAA AD 2012–21–20 is
applicable to 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.
Related Service Information
Airbus has issued the following
service information, which describes
procedures for modification of the RAT
pump hex shaft.
• Airbus Service Bulletin A330–29–
3122, dated October 25, 2012 (for Model
A330–200, –200 Freighter, and –300
series airplanes).
• Airbus Service Bulletin A340–29–
4093, dated October 25, 2012 (for Model
A340–200 and –300 series airplanes).
• Airbus Service Bulletin A340–29–
5021, dated October 2, 2012 (for Model
A340–500 and –600 series airplanes.
Hamilton Sundstrand has issued
Service Bulletin ERPS06M–29–19, dated
August 6, 2012, which describes
procedures for checking and replacing
the RAT hydraulic pump.
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.
Clarification of Service Information
Airbus Service Bulletin A330–29–
3122, dated October 25, 2012 (for Model
A330–200, –200 Freighter, and –300
series airplanes), contains a
typographical error in the vendor
service bulletin reference. The Airbus
service information in some instances
references Hamilton Sundstrand Service
Bulletin ‘‘EPRS06M–29–13,’’ but the
correct reference is ERPS06M–29–19.
Airbus is aware of the error and plans
to correct it when Service Bulletin
A330–29–3122 is revised.
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Costs of Compliance
We estimate that this proposed AD
affects 66 airplanes of U.S. registry.
We also estimate that it would take
about 14 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $78,540, or $1,190 per product.
In addition, we estimate that any
necessary follow-on actions would take
up to 18 work-hours and require parts
costing up to $427,301, for a cost of
$428,831 per product. We have no way
of determining the number of aircraft
that might need this action.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–0076;
Directorate Identifier 2013–NM–246–AD.
(a) Comments Due Date
We must receive comments by March 9,
2015.
(b) Affected ADs
This AD affects AD 2012–21–19,
Amendment 39–17235 (77 FR 65812, October
31, 2012); and AD 2012–21–20, Amendment
39–17236 (77 FR 65799, October 31, 2012).
(c) Applicability
This AD applies to all airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category, all manufacturer
serial numbers.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 29, Hydraulic Power.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(e) Reason
This AD was prompted by a report that,
during a production flight test, the ram air
turbine (RAT) did not pressurize the green
hydraulic system. We are issuing this AD to
prevent loss of the impeller function and
RAT pump pressurization capability, which,
if preceded by a total engine flame-out, could
result in the loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Identification of RAT Components
For Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes; and Model A340–211, –212, –213,
–311, –312, and –313 airplanes: Except as
provided by paragraph (i) of this AD, within
36 months after the effective date of this AD,
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identify the part number, serial number, and
standard (through the mod-dots) of the RAT
pump, RAT module, RAT actuator, and RAT
lower gearbox assembly, in accordance with
the Accomplishment Instructions of the
applicable Airbus service information
specified in paragraphs (g)(1) and (g)(2) of
this AD. A review of airplane maintenance
records is acceptable in lieu of this
identification if the part number, serial
number, and standard can be conclusively
determined from that review.
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes: Airbus Service Bulletin A330–29–
3122, dated October 25, 2012.
(2) For Airbus Model A340–211, –212,
–213, –311, –312, and –313 airplanes: Airbus
Service Bulletin A340–29–4093, dated
October 25, 2012.
(h) Corrective and Concurrent Actions
If the serial number of the RAT hydraulic
pump is included in table 7, ‘‘Suspect
Hydraulic Pump Serial Numbers,’’ of
Hamilton Sundstrand Service Bulletin
ERPS06M–29–19, dated August 6, 2012:
Within 36 months after the effective date of
this AD, do all applicable corrective actions,
in accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD. Prior to or concurrently
with doing the corrective actions required by
this paragraph, do the actions specified in
paragraphs (h)(1) through (h)(4) of this AD,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
29–3122, dated October 25, 2012 (for Model
A330–200, –200 Freighter, and –300 series
airplanes); or Airbus Service Bulletin A340–
29–4093, dated October 25, 2012 (for Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes).
(1) Replace the balance weight screw.
(2) Modify the actuator coil spring.
(3) Modify the actuator.
(4) Do a general visual inspection of the
anti-stall valve for correct installation in the
RAT pump housing, and if any incorrect
installation is found, before further flight,
correctly install the anti-stall valve.
(i) Exception to Service Information
Specifications
Where Airbus Service Bulletin A330–29–
3122, dated October 25, 2012 (for Model
A330–200, –200 Freighter, and –300 series
airplanes), refers to Hamilton Sundstrand
Service Bulletin ‘‘EPRS06M–29–13’’ as an
additional source of guidance for doing
certain actions required by paragraph (h) of
this AD, the correct reference should be to
Hamilton Sundstrand Service Bulletin
ERPS06M–29–19.
(j) Re-identification of Part Numbers
If the serial number of the RAT hydraulic
pump is not included in table 7, ‘‘Suspect
Hydraulic Pump Serial Numbers,’’ of
Hamilton Sundstrand Service Bulletin
ERPS06M–29–19, dated August 6, 2012:
Within 36 months after the effective date of
this AD, re-identify the part numbers of the
RAT hydraulic pump and RAT module, in
accordance with the Accomplishment
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Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD.
(k) RAT Module Replacement (Modification)
For Airbus Model A340–541 and –642
airplanes having RAT module P/N 772722D,
772722E, 772722F, or 772722G: Within 36
months after the effective date of this AD,
replace (modify) the RAT module, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
29–5021, dated October 2, 2012.
(l) Exception to Paragraphs (g), (h), and (j)
of This AD
The actions required by paragraph (g), (h)
and (j) of this AD are not required for
airplanes on which Airbus Modification
202537 was embodied in production,
provided it can be determined that, since the
airplane’s first flight, no RAT hydraulic
pump or RAT module having a part number
identified in paragraph (n) of this AD is
installed on that airplane.
(m) Terminating Action for Certain
Requirements of Other ADs
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and A340–211, –212, –213, –311,
–312, and –313 airplanes: Accomplishment
of the actions required by paragraphs (g), (h),
and (j) of this AD constitutes compliance
with the requirements of paragraphs (g)(1)
and (g)(2) of AD 2012–21–19, Amendment
39–17235 (77 FR 65812, October 31, 2012);
and paragraphs (g)(1) and (g)(2) of AD 2012–
21–20, Amendment 39–17236 (77 FR 65799,
October 31, 2012).
(2) For Airbus Model A340–541 and –642
airplanes: Accomplishment of the actions
required by paragraph (k) of this AD
constitutes compliance with the
requirements of paragraphs (h)(1) and (h)(2)
of AD 2012–21–20, Amendment 39–17236
(77 FR 65799, October 31, 2012).
(n) Parts Installation Prohibition
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and A340–211, –212, –213, –311,
–312, and –313 airplanes: After modification
of the RAT module as required by paragraph
(h) of this AD, no person may install any
complete RAT module having a part number
(P/N) identified in paragraph (n)(1)(i) of this
AD, or any RAT hydraulic pump having the
part number identified in paragraph (n)(1)(ii)
of this AD, on any airplane.
(i) RAT module P/N 766351, 768084,
770379, 770952, 770952A, 770952B,
1702934, 1702934A, or 1702934B.
(ii) RAT hydraulic pump P/N 5909522
(Parker P/N 4207902).
(2) For Airbus Model A340–541 and –642
airplanes: After modification of the RAT
module as required by paragraph (k) of this
AD, no person may install any complete RAT
module having P/N 772722D, 772722E,
772722F, or 772722G, on any airplane.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
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Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
(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: 9-ANM-116AMOC-REQUESTS@faa.gov. 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) Contacting the Manufacturer: 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.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0274, dated
November 15, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–0076.
(2) 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 airworthiness.A330A340@airbus.com; Internet https://
www.airbus.com. For Hamilton Sundstrand
service information identified in this AD,
contact Hamilton Sundstrand, Technical
Publications, Mail Stop 302–9, 4747 Harrison
Avenue, P.O. Box 7002, Rockford, IL 61125–
7002; telephone 860–654–3575; fax 860–998–
4564; email tech.solutions@hs.utc.com;
Internet https://
www.hamiltonsundstrand.com. You may
view the 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.
Issued in Renton, Washington, on January
14, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–00961 Filed 1–22–15; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1044; Directorate
Identifier 2014–NM–148–AD]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Cessna Aircraft Company Model 500,
501, 550, 551, S550, 560, and 650
airplanes. This proposed AD was
prompted by reports of smoke and/or
fire in the tailcone caused by sparking
due to excessive wear of the brushes in
the air conditioning (A/C) motor. This
proposed AD would require inspections
to determine if certain A/C compressor
motors are installed and to determine
the accumulated hours on certain A/C
compressor motor assemblies; and
repetitive replacement of the brushes in
the A/C compressor motor assembly, or,
as an option to the brush replacement,
deactivation of the A/C system and
placard installation; and return of
replaced brushes to Cessna. We are
proposing this AD to prevent the
brushes in the A/C motor from wearing
down beyond their limits, which could
result in the rivet in the brush
contacting the commutator, causing
sparks and consequent fire and/or
smoke in the tailcone with no means to
detect or extinguish the fire and/or
smoke.
SUMMARY:
We must receive comments on
this proposed AD by March 9, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Cessna
Aircraft Co., P.O. Box 7706, Wichita, KS
DATES:
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
67277; telephone 316–517–6215; fax
316–517–5802; email citationpubs@
cessna.textron.com; Internet https://
www.cessnasupport.com/newlogin.html.
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
1044; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Craig Henrichsen, Aerospace Engineer,
Electrical Systems and Avionics Branch,
ACE–119W, FAA, Wichita Aircraft
Certification Office (ACO), 1801 Airport
Road, Room 100, Mid-Continent
Airport, Wichita, KS 67209; phone:
316–946–4110; fax: 316–946–4107;
email: Craig.Henrichsen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2014–1044; Directorate Identifier 2014–
NM–148–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 because of those
comments.
We will post all comments we
receive, without change, to https://
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
We have received reports of smoke/
fire (three reports of fire) in the tailcone
of Cessna Aircraft Company Model 525,
550, and 560 airplanes, where
investigation revealed brushes had worn
E:\FR\FM\23JAP1.SGM
23JAP1
Agencies
[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3513-3516]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00961]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0076; Directorate Identifier 2013-NM-246-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A330-200, A330-200 Freighter, and A330-300 series
airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600
series airplanes. This proposed AD was prompted by a report that,
during a production flight test, the ram air turbine (RAT) did not
pressurize the green hydraulic system. For certain airplanes, this
proposed AD would require identification of the part number, serial
number, and standard of the RAT pump, RAT module, RAT actuator, and RAT
lower gearbox assembly; replacement of the balance weight screw,
modification of the actuator coil spring, modification of the actuator,
an inspection of the anti-stall valve for correct installation in the
RAT pump housing; and corrective actions if necessary. For certain
other airplanes, this proposed AD would require re-identification or
replacement of the RAT module. We are proposing this AD to prevent loss
of the impeller function and RAT pump pressurization capability, which,
if preceded by a total engine flame-out, could result in the loss of
control of the airplane.
DATES: We must receive comments on this proposed AD by March 9, 2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 Airbus 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.A330A-340@airbus.com; Internet
https://www.airbus.com. For Hamilton Sundstrand service information
identified in this proposed AD, contact Hamilton Sundstrand, Technical
Publications, Mail Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002,
Rockford, IL 61125-7002; telephone 860-654-3575; fax 860-998-4564;
email tech.solutions@hs.utc.com; Internet https://www.hamiltonsundstrand.com. You may view the 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0076; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM 116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0076;
Directorate Identifier 2013-NM-246-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 https://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 Union, has issued EASA
Airworthiness Directive 2013-0274, dated November 15, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus
Model A340-200, A340-300, A340-500, and A340-600 series airplanes. The
MCAI states:
During a production flight test of an A330-300 aeroplane, the
Ram Air Turbine (RAT) did not pressurize the green hydraulic system.
Investigation revealed that the impeller drive (hex) shaft had a
reduced length of engagement with the pump drive shaft. This caused
the impeller drive shaft to disengage from the pump and disconnect
the impeller. It was determined that the disconnection was the
result of internal hex dimensions on the pump impeller shaft, which
had been changed in a manufacturing drawing. From the investigation
analysis, it was possible to identify a list of affected parts.
[[Page 3514]]
This condition, if not detected and corrected, could lead to the
loss of impeller function and RAT pump pressurization capability,
possibly resulting, in case of total engine flame out, to the loss
of control of the aeroplane.
To address this unsafe condition, a new design RAT pump shaft
has been developed with a decreased hexagonal shaft housing depth,
which increases the hexagonal drive shaft engagement in the impeller
shaft to carry the impeller torque. Airbus issued Service Bulletin
(SB) A330-29-3122, SB A340-29-4093 and SB A340-29-5021 to provide
instructions for in-service replacement of the affected RAT
hydraulic pumps, or re-identification of the RAT pump and complete
RAT module, as applicable.
For the reasons described above, this [EASA] AD requires
identification and replacement [modification] or re-identification
of all affected RAT hydraulic pumps on A330 and A340-200/300
aeroplanes, and replacement [modification] of all affected RAT
modules on A340-500/-600 aeroplanes.
For affected pumps, the required actions also include concurrent
actions, as applicable, including replacement of the balance weight
screw, modification of the actuator coil spring, modification of the
actuator, an inspection of the anti-stall valve for correct
installation in the RAT pump housing and re-installation if necessary.
For affected pumps, corrective actions include replacement of the RAT
hydraulic pump, and re-identification of the part number of the RAT
module. You may examine the MCAI in the AD docket on the Internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2015-0076.
Related ADs
EASA and the FAA have issued additional ADs related to the RAT. FAA
AD 2012-21-19, Amendment 39-17235 (77 FR 65812, October 31, 2012),
which corresponds to EASA AD 2011-0197, dated October 10, 2011,
requires an inspection of the RAT anti-stall valve in the pump housing
for correct setting, re-identification of the RAT pump, performing a
functional ground test of the RAT, and replacement of the RAT pump or
the RAT assembly with a serviceable part if necessary. FAA AD 2012-21-
19 is applicable to all Airbus Model A330-200 freighter series
airplanes; Model A330-200 and -300 series airplanes; and Model A340-200
and -300 series airplanes.
The FAA also issued AD 2012-21-20, Amendment 39-17236 (77 FR 65799,
October 31, 2012), which corresponds to EASA AD 2011-0204, dated
October 14, 2011. FAA AD 2012-21-20 requires identification of the
supplier, part number, and serial number of the RAT actuator, and re-
identification of the RAT actuator and RAT, or replacement of the RAT
actuator with a serviceable unit and re-identification of the RAT, if
necessary. FAA AD 2012-21-20 is applicable to 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.
Related Service Information
Airbus has issued the following service information, which
describes procedures for modification of the RAT pump hex shaft.
Airbus Service Bulletin A330-29-3122, dated October 25,
2012 (for Model A330-200, -200 Freighter, and -300 series airplanes).
Airbus Service Bulletin A340-29-4093, dated October 25,
2012 (for Model A340-200 and -300 series airplanes).
Airbus Service Bulletin A340-29-5021, dated October 2,
2012 (for Model A340-500 and -600 series airplanes.
Hamilton Sundstrand has issued Service Bulletin ERPS06M-29-19,
dated August 6, 2012, which describes procedures for checking and
replacing the RAT hydraulic pump.
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.
Clarification of Service Information
Airbus Service Bulletin A330-29-3122, dated October 25, 2012 (for
Model A330-200, -200 Freighter, and -300 series airplanes), contains a
typographical error in the vendor service bulletin reference. The
Airbus service information in some instances references Hamilton
Sundstrand Service Bulletin ``EPRS06M-29-13,'' but the correct
reference is ERPS06M-29-19. Airbus is aware of the error and plans to
correct it when Service Bulletin A330-29-3122 is revised.
Costs of Compliance
We estimate that this proposed AD affects 66 airplanes of U.S.
registry.
We also estimate that it would take about 14 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $78,540, or $1,190
per product.
In addition, we estimate that any necessary follow-on actions would
take up to 18 work-hours and require parts costing up to $427,301, for
a cost of $428,831 per product. We have no way of determining the
number of aircraft that might need this action.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 3515]]
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):
Airbus: Docket No. FAA-2015-0076; Directorate Identifier 2013-NM-
246-AD.
(a) Comments Due Date
We must receive comments by March 9, 2015.
(b) Affected ADs
This AD affects AD 2012-21-19, Amendment 39-17235 (77 FR 65812,
October 31, 2012); and AD 2012-21-20, Amendment 39-17236 (77 FR
65799, October 31, 2012).
(c) Applicability
This AD applies to all airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
Power.
(e) Reason
This AD was prompted by a report that, during a production
flight test, the ram air turbine (RAT) did not pressurize the green
hydraulic system. We are issuing this AD to prevent loss of the
impeller function and RAT pump pressurization capability, which, if
preceded by a total engine flame-out, could result in the loss of
control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of RAT Components
For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes;
and Model A340-211, -212, -213, -311, -312, and -313 airplanes:
Except as provided by paragraph (i) of this AD, within 36 months
after the effective date of this AD, identify the part number,
serial number, and standard (through the mod-dots) of the RAT pump,
RAT module, RAT actuator, and RAT lower gearbox assembly, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraphs (g)(1) and (g)(2)
of this AD. A review of airplane maintenance records is acceptable
in lieu of this identification if the part number, serial number,
and standard can be conclusively determined from that review.
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes: Airbus Service Bulletin A330-29-3122, dated October 25,
2012.
(2) For Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-29-4093, dated October 25,
2012.
(h) Corrective and Concurrent Actions
If the serial number of the RAT hydraulic pump is included in
table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012:
Within 36 months after the effective date of this AD, do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of the applicable Airbus service information specified
in paragraphs (g)(1) and (g)(2) of this AD. Prior to or concurrently
with doing the corrective actions required by this paragraph, do the
actions specified in paragraphs (h)(1) through (h)(4) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-29-3122, dated October 25, 2012 (for Model A330-200, -
200 Freighter, and -300 series airplanes); or Airbus Service
Bulletin A340-29-4093, dated October 25, 2012 (for Airbus Model
A340-211, -212, -213, -311, -312, and -313 airplanes).
(1) Replace the balance weight screw.
(2) Modify the actuator coil spring.
(3) Modify the actuator.
(4) Do a general visual inspection of the anti-stall valve for
correct installation in the RAT pump housing, and if any incorrect
installation is found, before further flight, correctly install the
anti-stall valve.
(i) Exception to Service Information Specifications
Where Airbus Service Bulletin A330-29-3122, dated October 25,
2012 (for Model A330-200, -200 Freighter, and -300 series
airplanes), refers to Hamilton Sundstrand Service Bulletin
``EPRS06M-29-13'' as an additional source of guidance for doing
certain actions required by paragraph (h) of this AD, the correct
reference should be to Hamilton Sundstrand Service Bulletin ERPS06M-
29-19.
(j) Re-identification of Part Numbers
If the serial number of the RAT hydraulic pump is not included
in table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012:
Within 36 months after the effective date of this AD, re-identify
the part numbers of the RAT hydraulic pump and RAT module, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraphs (g)(1) and (g)(2)
of this AD.
(k) RAT Module Replacement (Modification)
For Airbus Model A340-541 and -642 airplanes having RAT module
P/N 772722D, 772722E, 772722F, or 772722G: Within 36 months after
the effective date of this AD, replace (modify) the RAT module, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A340-29-5021, dated October 2, 2012.
(l) Exception to Paragraphs (g), (h), and (j) of This AD
The actions required by paragraph (g), (h) and (j) of this AD
are not required for airplanes on which Airbus Modification 202537
was embodied in production, provided it can be determined that,
since the airplane's first flight, no RAT hydraulic pump or RAT
module having a part number identified in paragraph (n) of this AD
is installed on that airplane.
(m) Terminating Action for Certain Requirements of Other ADs
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and A340-211, -212, -213, -311, -312, and -313 airplanes:
Accomplishment of the actions required by paragraphs (g), (h), and
(j) of this AD constitutes compliance with the requirements of
paragraphs (g)(1) and (g)(2) of AD 2012-21-19, Amendment 39-17235
(77 FR 65812, October 31, 2012); and paragraphs (g)(1) and (g)(2) of
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).
(2) For Airbus Model A340-541 and -642 airplanes: Accomplishment
of the actions required by paragraph (k) of this AD constitutes
compliance with the requirements of paragraphs (h)(1) and (h)(2) of
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).
(n) Parts Installation Prohibition
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and A340-211, -212, -213, -311, -312, and -313 airplanes:
After modification of the RAT module as required by paragraph (h) of
this AD, no person may install any complete RAT module having a part
number (P/N) identified in paragraph (n)(1)(i) of this AD, or any
RAT hydraulic pump having the part number identified in paragraph
(n)(1)(ii) of this AD, on any airplane.
(i) RAT module P/N 766351, 768084, 770379, 770952, 770952A,
770952B, 1702934, 1702934A, or 1702934B.
(ii) RAT hydraulic pump P/N 5909522 (Parker P/N 4207902).
(2) For Airbus Model A340-541 and -642 airplanes: After
modification of the RAT module as required by paragraph (k) of this
AD, no person may install any complete RAT module having P/N
772722D, 772722E, 772722F, or 772722G, on any airplane.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
[[Page 3516]]
(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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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) Contacting the Manufacturer: 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0274, dated November 15,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0076.
(2) 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 airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. For Hamilton Sundstrand service
information identified in this AD, contact Hamilton Sundstrand,
Technical Publications, Mail Stop 302-9, 4747 Harrison Avenue, P.O.
Box 7002, Rockford, IL 61125-7002; telephone 860-654-3575; fax 860-
998-4564; email tech.solutions@hs.utc.com; Internet https://www.hamiltonsundstrand.com. You may view the 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.
Issued in Renton, Washington, on January 14, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-00961 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P