Airworthiness Directives; Airbus Model A330-243, -341, -342, and -343 Airplanes Equipped with Rolls-Royce Trent 700 Engines, 19196-19199 [2010-8181]
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19196
Federal Register / Vol. 75, No. 71 / Wednesday, April 14, 2010 / Rules and Regulations
Material Incorporated by Reference
(i) You must use the applicable service
information specified in Table 3 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise. If you
accomplish the optional actions specified by
this AD, you must use EMBRAER Service
Bulletin 190–29–0021, dated December 22,
2008; or EMBRAER Service Bulletin 170–29–
0024, dated December 22, 2008; as
applicable; to perform those actions, unless
the AD specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED BY THIS AD
EMBRAER Service Bulletin—
Revision—
Dated—
170–29–0013
170–29–0013
190–29–0008
190–29–0008
Original ................................................................................
01 ........................................................................................
Original ................................................................................
01 ........................................................................................
December 13, 2006.
July 24, 2007.
December 13, 2006.
July 24, 2007.
........................................................................
........................................................................
........................................................................
........................................................................
EMBRAER Service Bulletin 170–29–0013,
Revision 01, contains the following effective
pages:
Page
number
1–5, 10
6–9 .....
Revision
level
shown on
page
01 ............
Original ....
Date shown on page
Page
number
jlentini on DSKJ8SOYB1PROD with RULES
1–5, 10
6–9 .....
01 ............
Original ....
[FR Doc. 2010–7804 Filed 4–13–10; 8:45 am]
BILLING CODE 4910–13–P
July 24, 2007.
December 13, 2006.
EMBRAER Service Bulletin 190–29–0008,
Revision 01, contains the following effective
pages:
Revision
level
shown on
page
Issued in Renton, Washington, on March
25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Date shown on page
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0391; Directorate
Identifier 2010–NM–073–AD; Amendment
39–16263; AD 2010–08–08]
RIN 2120–AA64
July 24, 2007.
December 13, 2006.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—BRASIL; telephone:
+55 12 3927–5852 or +55 12 3309–0732; fax:
+55 12 3927–7546; e-mail:
distrib@embraer.com.br; Internet: https://
www.flyembraer.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Airworthiness Directives; Airbus Model
A330–243, –341, –342, and –343
Airplanes Equipped with Rolls-Royce
Trent 700 Engines
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During a recent in-service event the flight
crew of a Trent 700 powered A330 aircraft
reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the takeoff phase of the flight.* * *
Data analysis confirmed a temporary fuel
flow restriction and subsequent recovery, and
indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after
the initial event on engine 2. * * *
Based on previous industry-wide
experience, the investigation of the event has
focused on the possibility for ice to
temporarily restrict the fuel flow.* * *
*
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*
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*
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The scenario of ice being shed and causing
a temporary blockage in the engine fuel
system may lead to a temporary fuel flow
restriction to the engine. This may result in
a possible engine surge or stall condition,
and in the engine not being able to provide
the commanded thrust.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective April
29, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 29, 2010.
We must receive comments on this
AD by June 1, 2010.
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
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, 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 https://
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 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,
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Federal Register / Vol. 75, No. 71 / Wednesday, April 14, 2010 / Rules and Regulations
This AD also requires revising the
Limitations section of the airplane flight
manual to advise the flight crew of the
dispatch prohibition. You may obtain
further information by examining the
MCAI in the AD docket.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Emergency Airworthiness Directive
2010–0042–E, dated March 12, 2010
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
jlentini on DSKJ8SOYB1PROD with RULES
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Relevant Service Information
Airbus has issued All Operators Telex
A330–28A3114, Revision 1, dated
March 24, 2010. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
During a recent in-service event the flight
crew of a Trent 700 powered A330 aircraft
reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the takeoff phase of the flight. The ENG STALL
warning was set. The flight crew followed the
standard procedures which included
reducing throttle to idle. The engine
recovered and provided the demanded thrust
level for the remainder of the flight.
Data analysis confirmed a temporary fuel
flow restriction and subsequent recovery, and
indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after
the initial event on engine 2, again followed
by a full recovery. The engine 1 EPR shortfall
was insufficient to trigger any associated
warning and was only noted through analysis
of the flight data. No flight crew action was
necessary to recover normal performance on
this engine. The remainder of the flight was
uneventful.
Based on previous industry-wide
experience, the investigation of the event has
focused on the possibility for ice to
temporarily restrict the fuel flow. While no
direct fuel system fault has been identified,
the operation of the water scavenge system at
Rib 3 cannot be excluded as being a
contributory factor.
Testing and analysis are continuing to
identify the root cause of the event.
The scenario of ice being shed and causing
a temporary blockage in the engine fuel
system may lead to a temporary fuel flow
restriction to the engine. This may result in
a possible engine surge or stall condition,
and in the engine not being able to provide
the commanded thrust.
Therefore, as a precautionary measure to
reduce the possibility of ingesting ice into the
engine fuel feed system, this AD requires to:
—Deactivate the automatic Standby Fuel
Pump Scavenge System, which operates
during Taxi and Take-off by removing
relays Functional Item Numbers (FIN)
80QA1 and 80QA2 (this will not affect
normal standby pump operation) for
aeroplanes identified in the applicability
section of this AD and on which this
deactivation has not been performed in
production through the modification
200801, and
—Prohibit the dispatch with * * * [a] MAIN
Fuel Pump inoperative on all aeroplanes
identified in the applicability section of
this AD.
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16:13 Apr 13, 2010
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FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between the AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because ice being shed and causing
a temporary blockage in the engine fuel
system could lead to a temporary fuel
flow restriction to the engine, which
could result in a possible engine surge
or stall condition, and in the engine not
being able to provide the commanded
thrust. Therefore, we determined that
notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
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19197
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2010–0391;
Directorate Identifier 2010–NM–073–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Federal Register / Vol. 75, No. 71 / Wednesday, April 14, 2010 / Rules and Regulations
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. 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.
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
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 AD:
■
2010–08–08 Airbus: Amendment 39–
16263. Docket No. FAA–2010–0391;
Directorate Identifier 2010–NM–073–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 29, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330–
243, –341, –342, and –343 airplanes,
certificated in any category, all manufacturer
serial numbers equipped with Rolls-Royce
Trent 700 engines, on which Airbus
modification 56966MP16199 has been
embodied in production or Airbus Service
Bulletin A330–28–3105 has been embodied
in service.
jlentini on DSKJ8SOYB1PROD with RULES
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
During a recent in-service event the flight
crew of a Trent 700 powered A330 aircraft
reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the takeoff phase of the flight. The ENG STALL
warning was set. The flight crew followed the
standard procedures which included
reducing throttle to idle. The engine
recovered and provided the demanded thrust
level for the remainder of the flight.
VerDate Nov<24>2008
16:13 Apr 13, 2010
Jkt 220001
Data analysis confirmed a temporary fuel
flow restriction and subsequent recovery, and
indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after
the initial event on engine 2, again followed
by a full recovery. The engine 1 EPR shortfall
was insufficient to trigger any associated
warning and was only noted through analysis
of the flight data. No flight crew action was
necessary to recover normal performance on
this engine. The remainder of the flight was
uneventful.
Based on previous industry-wide
experience, the investigation of the event has
focused on the possibility for ice to
temporarily restrict the fuel flow. While no
direct fuel system fault has been identified,
the operation of the water scavenge system at
Rib 3 cannot be excluded as being a
contributory factor.
Testing and analysis are continuing to
identify the root cause of the event.
The scenario of ice being shed and causing
a temporary blockage in the engine fuel
system may lead to a temporary fuel flow
restriction to the engine. This may result in
a possible engine surge or stall condition,
and in the engine not being able to provide
the commanded thrust.
Therefore, as a precautionary measure to
reduce the possibility of ingesting ice into the
engine fuel feed system, this AD requires to:
—Deactivate the automatic Standby Fuel
Pump Scavenge System, which operates
during Taxi and Take-off by removing
relays Functional Item Numbers (FIN)
80QA1 and 80QA2 (this will not affect
normal standby pump operation) for
aeroplanes identified in the applicability
section of this AD and on which this
deactivation has not been performed in
production through the modification
200801, and
—Prohibit the dispatch with * * * [a] MAIN
Fuel Pump inoperative on all aeroplanes
identified in the applicability section of
this AD.
This AD also requires revising the
Limitations section of the airplane flight
manual to advise the flight crew of the
dispatch prohibition.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Actions
(g) For airplanes on which Airbus
modification 200801 has not been embodied
in production as of the effective date of this
AD: Within 10 days after the effective date
of this AD, deactivate the water scavenge
automatic operation by removing relays FIN
80QA1 (left-hand) and 80QA2 (right-hand),
in accordance with the instructions in Airbus
All Operators Telex A330–28A3114, Revision
1, dated March 24, 2010.
(h) Deactivation before the effective date of
this AD in accordance with Airbus All
Operators Telex A330–28A3114, dated
March 10, 2010, is considered acceptable for
compliance with the corresponding action
required by paragraph (g) of this AD.
(i) For airplanes on which Airbus
modification 200801 has not been embodied
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in production as of the effective date of this
AD: Before further flight after
accomplishment of the requirements of
paragraph (g) of this AD, dispatch of an
airplane with any inoperative main fuel
pump is prohibited.
(j) For airplanes on which Airbus
modification 200801 has been embodied in
production as of the effective date of this AD:
Dispatch of an airplane with any inoperative
main fuel pump is prohibited as of the
effective date of this AD.
(k) For all airplanes: At the applicable time
specified in paragraph (k)(1) or (k)(2) of this
AD, revise the Limitations section of the
airplane flight manual (AFM) to include the
following statement. This may be done by
inserting a copy of this AD into the AFM.
‘‘Dispatch with any inoperative main fuel
pump is prohibited.’’
(1) For airplanes on which Airbus
modification 200801 has not been embodied
in production as of the effective date of this
AD: Revise the AFM before further flight after
accomplishment of the requirements of
paragraph (g) of this AD.
(2) For airplanes on which Airbus
modification 200801 has been embodied in
production as of the effective date of this AD:
Revise the AFM before further flight after the
effective date of this AD.
Note 1: When a statement identical to that
in paragraph (k) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(l) 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.
Send information to ATTN: 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 (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
refer to 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.
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Federal Register / Vol. 75, No. 71 / Wednesday, April 14, 2010 / Rules and Regulations
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(m) Refer to MCAI European Aviation
Safety Agency (EASA) Emergency
Airworthiness Directive 2010–0042–E, dated
March 12, 2010; and Airbus All Operators
Telex A330–28A3114, Revision 1, dated
March 24, 2010; for related information.
Material Incorporated by Reference
(n) You must use Airbus All Operators
Telex A330–28A3114, Revision 1, dated
March 24, 2010, as applicable, to do the
actions required by this AD, unless the AD
specifies otherwise. (The document number,
revision level, and date of this document are
indicated only on the first page of the
document; no other page of the document
contains this information.)
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(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; e-mail
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on April 1,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–8181 Filed 4–13–10; 8:45 am]
jlentini on DSKJ8SOYB1PROD with RULES
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VerDate Nov<24>2008
16:13 Apr 13, 2010
Jkt 220001
19199
Federal Aviation Administration
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Discussion
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2009–1108; Directorate
Identifier 2009–NM–131–AD; Amendment
39–16260; AD 2010–08–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, and A340–300
Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
It was noticed in production that in the
area between frame (FR) C53.9 and FR C55
RH [right-hand], the distance between the
route 9R of the In-Flight Entertainment
system and the wire harness for the Lower
Deck-Mobile Crew Rest system provisions is
too small.
This limited distance may cause chafing
between the affected electrical harness
6581VB and the harness 5495VB or 6938VB.
This condition, if not corrected, could lead
to the short circuit of wires dedicated to
oxygen, which, in case of emergency, could
result in a large number of passenger oxygen
masks not being supplied with oxygen,
possibly causing personal injuries.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective May
19, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 19, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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,
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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 December 1, 2009 (74 FR
62711). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
It was noticed in production that in the
area between frame (FR) C53.9 and FR C55
RH [right-hand], the distance between the
route 9R of the In-Flight Entertainment
system and the wire harness for the Lower
Deck-Mobile Crew Rest system provisions is
too small.
This limited distance may cause chafing
between the affected electrical harness
6581VB and the harness 5495VB or 6938VB.
This condition, if not corrected, could lead
to the short circuit of wires dedicated to
oxygen, which, in case of emergency, could
result in a large number of passenger oxygen
masks not being supplied with oxygen,
possibly causing personal injuries.
For the reasons described above, this AD
requires the installation of a stirrup on the
terminal block 5507VT between FR53.9 and
FR54, and the re-routing of the wiring route
9R.
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
considered the comments received.
Support for the NPRM
Northwest Airlines states that it has
reviewed the NPRM and supports the
action.
Request To Correct Paragraph
Identifier
Airbus requests that we correct the
paragraph identifiers specified in the
applicability statement of the NPRM,
changing ‘‘* * * paragraphs (c)(1)(i) and
(c)(1)(ii) * * *’’ of the NPRM to ‘‘* * *
paragraphs (c)(1) and (c)(2) * * *’’ in
this final rule.
We have corrected the paragraph
identifiers in this final rule.
Request To Clarify the Proposed
Applicability
Airbus requests that we clarify the
applicability in paragraph (c)(ii)(A) of
the NPRM (now paragraph (c)(2)(i) of
this final rule), to specify the Model
A330 airplanes.
We agree to clarify the applicability.
We have clarified the applicability
statement from ‘‘For all models, except
E:\FR\FM\14APR1.SGM
14APR1
]]>Agencies
[Federal Register Volume 75, Number 71 (Wednesday, April 14, 2010)]
[Rules and Regulations]
[Pages 19196-19199]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-8181]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0391; Directorate Identifier 2010-NM-073-AD;
Amendment 39-16263; AD 2010-08-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-243, -341, -342, and
-343 Airplanes Equipped with Rolls-Royce Trent 700 Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
During a recent in-service event the flight crew of a Trent 700
powered A330 aircraft reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the take-off phase of the
flight.* * *
Data analysis confirmed a temporary fuel flow restriction and
subsequent recovery, and indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after the initial event on
engine 2. * * *
Based on previous industry-wide experience, the investigation of
the event has focused on the possibility for ice to temporarily
restrict the fuel flow.* * *
* * * * *
The scenario of ice being shed and causing a temporary blockage
in the engine fuel system may lead to a temporary fuel flow
restriction to the engine. This may result in a possible engine
surge or stall condition, and in the engine not being able to
provide the commanded thrust.
* * * * *
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective April 29, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of April 29,
2010.
We must receive comments on this AD by June 1, 2010.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, 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 https://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 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,
[[Page 19197]]
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency Airworthiness Directive 2010-0042-E, dated March 12, 2010
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
During a recent in-service event the flight crew of a Trent 700
powered A330 aircraft reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the take-off phase of the flight.
The ENG STALL warning was set. The flight crew followed the standard
procedures which included reducing throttle to idle. The engine
recovered and provided the demanded thrust level for the remainder
of the flight.
Data analysis confirmed a temporary fuel flow restriction and
subsequent recovery, and indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after the initial event on
engine 2, again followed by a full recovery. The engine 1 EPR
shortfall was insufficient to trigger any associated warning and was
only noted through analysis of the flight data. No flight crew
action was necessary to recover normal performance on this engine.
The remainder of the flight was uneventful.
Based on previous industry-wide experience, the investigation of
the event has focused on the possibility for ice to temporarily
restrict the fuel flow. While no direct fuel system fault has been
identified, the operation of the water scavenge system at Rib 3
cannot be excluded as being a contributory factor.
Testing and analysis are continuing to identify the root cause
of the event.
The scenario of ice being shed and causing a temporary blockage
in the engine fuel system may lead to a temporary fuel flow
restriction to the engine. This may result in a possible engine
surge or stall condition, and in the engine not being able to
provide the commanded thrust.
Therefore, as a precautionary measure to reduce the possibility
of ingesting ice into the engine fuel feed system, this AD requires
to:
--Deactivate the automatic Standby Fuel Pump Scavenge System, which
operates during Taxi and Take-off by removing relays Functional Item
Numbers (FIN) 80QA1 and 80QA2 (this will not affect normal standby
pump operation) for aeroplanes identified in the applicability
section of this AD and on which this deactivation has not been
performed in production through the modification 200801, and
--Prohibit the dispatch with * * * [a] MAIN Fuel Pump inoperative on
all aeroplanes identified in the applicability section of this AD.
This AD also requires revising the Limitations section of the airplane
flight manual to advise the flight crew of the dispatch prohibition.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued All Operators Telex A330-28A3114, Revision 1,
dated March 24, 2010. 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 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because ice
being shed and causing a temporary blockage in the engine fuel system
could lead to a temporary fuel flow restriction to the engine, which
could result in a possible engine surge or stall condition, and in the
engine not being able to provide the commanded thrust. Therefore, we
determined that notice and opportunity for public comment before
issuing this AD are impracticable and that good cause exists for making
this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2010-0391; Directorate
Identifier 2010-NM-073-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 19198]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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:
2010-08-08 Airbus: Amendment 39-16263. Docket No. FAA-2010-0391;
Directorate Identifier 2010-NM-073-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
29, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-243, -341, -342, and -
343 airplanes, certificated in any category, all manufacturer serial
numbers equipped with Rolls-Royce Trent 700 engines, on which Airbus
modification 56966MP16199 has been embodied in production or Airbus
Service Bulletin A330-28-3105 has been embodied in service.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
During a recent in-service event the flight crew of a Trent 700
powered A330 aircraft reported a temporary Engine Pressure Ratio
(EPR) shortfall on engine 2 during the take-off phase of the flight.
The ENG STALL warning was set. The flight crew followed the standard
procedures which included reducing throttle to idle. The engine
recovered and provided the demanded thrust level for the remainder
of the flight.
Data analysis confirmed a temporary fuel flow restriction and
subsequent recovery, and indicated that also engine 1 experienced a
temporary fuel flow restriction shortly after the initial event on
engine 2, again followed by a full recovery. The engine 1 EPR
shortfall was insufficient to trigger any associated warning and was
only noted through analysis of the flight data. No flight crew
action was necessary to recover normal performance on this engine.
The remainder of the flight was uneventful.
Based on previous industry-wide experience, the investigation of
the event has focused on the possibility for ice to temporarily
restrict the fuel flow. While no direct fuel system fault has been
identified, the operation of the water scavenge system at Rib 3
cannot be excluded as being a contributory factor.
Testing and analysis are continuing to identify the root cause
of the event.
The scenario of ice being shed and causing a temporary blockage
in the engine fuel system may lead to a temporary fuel flow
restriction to the engine. This may result in a possible engine
surge or stall condition, and in the engine not being able to
provide the commanded thrust.
Therefore, as a precautionary measure to reduce the possibility
of ingesting ice into the engine fuel feed system, this AD requires
to:
--Deactivate the automatic Standby Fuel Pump Scavenge System, which
operates during Taxi and Take-off by removing relays Functional Item
Numbers (FIN) 80QA1 and 80QA2 (this will not affect normal standby
pump operation) for aeroplanes identified in the applicability
section of this AD and on which this deactivation has not been
performed in production through the modification 200801, and
--Prohibit the dispatch with * * * [a] MAIN Fuel Pump inoperative on
all aeroplanes identified in the applicability section of this AD.
This AD also requires revising the Limitations section of the
airplane flight manual to advise the flight crew of the dispatch
prohibition.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) For airplanes on which Airbus modification 200801 has not
been embodied in production as of the effective date of this AD:
Within 10 days after the effective date of this AD, deactivate the
water scavenge automatic operation by removing relays FIN 80QA1
(left-hand) and 80QA2 (right-hand), in accordance with the
instructions in Airbus All Operators Telex A330-28A3114, Revision 1,
dated March 24, 2010.
(h) Deactivation before the effective date of this AD in
accordance with Airbus All Operators Telex A330-28A3114, dated March
10, 2010, is considered acceptable for compliance with the
corresponding action required by paragraph (g) of this AD.
(i) For airplanes on which Airbus modification 200801 has not
been embodied in production as of the effective date of this AD:
Before further flight after accomplishment of the requirements of
paragraph (g) of this AD, dispatch of an airplane with any
inoperative main fuel pump is prohibited.
(j) For airplanes on which Airbus modification 200801 has been
embodied in production as of the effective date of this AD: Dispatch
of an airplane with any inoperative main fuel pump is prohibited as
of the effective date of this AD.
(k) For all airplanes: At the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD, revise the Limitations
section of the airplane flight manual (AFM) to include the following
statement. This may be done by inserting a copy of this AD into the
AFM.
``Dispatch with any inoperative main fuel pump is prohibited.''
(1) For airplanes on which Airbus modification 200801 has not
been embodied in production as of the effective date of this AD:
Revise the AFM before further flight after accomplishment of the
requirements of paragraph (g) of this AD.
(2) For airplanes on which Airbus modification 200801 has been
embodied in production as of the effective date of this AD: Revise
the AFM before further flight after the effective date of this AD.
Note 1: When a statement identical to that in paragraph (k) of
this AD has been included in the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the AFM.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(l) 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. Send information to ATTN:
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 (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically refer to 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.
[[Page 19199]]
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(m) Refer to MCAI European Aviation Safety Agency (EASA)
Emergency Airworthiness Directive 2010-0042-E, dated March 12, 2010;
and Airbus All Operators Telex A330-28A3114, Revision 1, dated March
24, 2010; for related information.
Material Incorporated by Reference
(n) You must use Airbus All Operators Telex A330-28A3114,
Revision 1, dated March 24, 2010, as applicable, to do the actions
required by this AD, unless the AD specifies otherwise. (The
document number, revision level, and date of this document are
indicated only on the first page of the document; no other page of
the document contains this information.)
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(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; e-mail airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 1, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-8181 Filed 4-13-10; 8:45 am]
BILLING CODE 4910-13-P
