Airworthiness Directives; Airbus Model A330-200 and -300, and Model A340-200, -300, -500 and 600 Series Airplanes, 68737-68741 [E9-30649]
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Federal Register / Vol. 74, No. 248 / Tuesday, December 29, 2009 / Proposed Rules
load combination operations. There are
no specific requirements in the
airworthiness standards for this type of
pilot position. Therefore, if the auxiliary
control station is equipped with flight
controls—
(1) The rotorcraft must be safely
controllable by the auxiliary controls,
throughout the range of the auxiliary
controls.
(2) The auxiliary controls may not
interfere with the safe operation of the
rotorcraft by the pilot or copilot when
the station is not occupied.
(3) The auxiliary control station and
its associated equipment must allow the
operator to perform his or her duties
without unreasonable concentration or
fatigue.
(4) The vibration and noise
characteristics of the auxiliary control
station appurtenances must not interfere
with the operator’s assigned duties to an
extent that would make the operation
unsafe.
(5) The auxiliary control station must
be arranged to give the operator
sufficiently extensive, clear, and
undistorted view for safe operation. The
station must be free of glare and
reflection that could interfere with the
operator’s view.
(6) There must be provisions to
prevent unintentional movement of the
controls when the rear-facing aft-stick
operator’s seat is occupied by other than
essential crewmembers during other
than external-load operations.
(k) Quick-Release Devices. The S–64
is specifically designed for rotorcraft
load combination operations with
particular weight-specified hard points
designed into the airframe. Because of
this unusual design, when quick release
devices are required under 14 CFR part
133, it must enable the pilot to release
the external-load quickly during flight.
The quick-release system must comply
with the following:
(1) An activating control for the quickrelease system must be installed on one
of the pilot’s primary controls and must
be designed and located so it may be
operated by the pilot without
hazardously limiting his or her ability to
control the rotorcraft during an
emergency situation.
(2) An alternative independent
activating control for the quick-release
system must be provided and must be
readily accessible to the pilot or a
crewmember.
(3) The design of the quick-release
system must ensure that failure, which
could prevent the release of external
loads, is extremely improbable.
(4) The quick-release system must be
capable of functioning properly after
failure of all engines.
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(5) The quick-release system must
function properly with external loads
up to and including the maximum
weight for which certification is
requested.
(6) The quick-release system must
include a means to check for proper
operation of the system at established
intervals.
(l) Maximum Weight with External
Load. When establishing compliance
with § 29.25, the maximum weight of
the rotorcraft-load combination for
operations with external loads must be
established by the applicant and may
not exceed the weight at which
compliance with all applicable
requirements has been shown.
(m) External Load Jettisoning. The
external load must be jettisonable to the
maximum weight for which the
helicopter has been type certificated for
operation without external loads or with
Class A loads.
(n) Minimum Flight Crew. To meet the
requirements of § 29.1523, the minimum
flight crew consists of a pilot and a
copilot. For pick up of the external-load
and on-site maneuvering and release of
the external-load, the copilot may act as
the aft-facing hoist operator.
(o) Occupancy. When engaged in
operations other than external-load
operations under 14 CFR part 133, the
carriage of passengers in the two
observer seats and the rear-facing aftstick operator’s seat, when the aft-stick
operator’s controls are disengaged and
the collective guard is installed, will be
controlled by the FAA operating
requirements applicable to that
particular operation.
(p) Operations. The S–64 meets the
Category B fire protection requirements
for structures and controls in lieu of
Category A requirements. Therefore,
when operating over congested areas,
the rotorcraft must be operated at an
altitude and over routes that provide
suitable landing areas that can be
reached in no more than 5 minutes.
(q) Markings and Placards. For
purposes of rotorcraft load combination
operations, the following markings and
placards must be displayed
conspicuously and must be applied so
they cannot be easily erased, disfigured,
or obscured.
(1) A placard, plainly visible to
appropriate crewmembers, referring to
the helicopter flight manual limitations
and restrictions for rotorcraft load
combinations allowed under 14 CFR
part 133.
(2) A placard, marking, or instructions
(displayed next to the external-load
attaching means) stating the maximum
external-load prescribed as an operating
limitation for rotorcraft load
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68737
combinations allowed under 14 CFR
part 133.
(3) A placard in the cockpit
prescribing the occupancy limitation
during rotorcraft load combination
operations under 14 CFR part 133.
Issued in Fort Worth, TX, on December 17,
2009.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service, ASW–100.
[FR Doc. E9–30794 Filed 12–28–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1215; Directorate
Identifier 2009–NM–126–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and –300, and Model A340–
200, –300, –500 and 600 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
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:
* * * [P]artial blockage of the water
absorbing filter element P/N (part number)
QA06123 was observed several times. The
blockage was created by carbon debris from
the cartridge and from the burst disc of the
Halon bottle.
This water absorbing filter element is part
of Halon Dual-Filter Assembly installed also
in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing
System used in the A330 and A340
aeroplanes.
Blockage of the water absorbing filter
element could lead to reduction of Halon
outflow, leading to incapacity to maintain
fire extinguishing agent concentration.
Combined with fire, this could result in an
uncontrolled fire in the affected
compartment, which would constitute an
unsafe condition.
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by February 12, 2010.
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Federal Register / Vol. 74, No. 248 / Tuesday, December 29, 2009 / Proposed Rules
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.
For service information identified in
this proposed AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221 or 425–227–1152.
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 have lengthened the 30-day
comment period for proposed ADs that
address MCAI originated by aviation
authorities of other countries to provide
adequate time for interested parties to
submit comments. The comment period
for these proposed ADs is now typically
45 days, which is consistent with the
comment period for domestic transport
ADs.
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.
Examining the AD Docket
During the qualification test campaign at
the supplier site of the prototype Flow
Metering Compact Unit (FMCU) Part Number
(P/N) QA07907–03, partial blockage of the
water absorbing filter element P/N QA06123
was observed several times. The blockage
was created by carbon debris from the
cartridge and from the burst disc of the Halon
bottle.
This water absorbing filter element is part
of Halon Dual-Filter Assembly installed also
in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing
System used in the A330 and A340
aeroplanes.
Blockage of the water absorbing filter
element could lead to reduction of Halon
outflow, leading to incapacity to maintain
fire extinguishing agent concentration.
Combined with fire, this could result in an
uncontrolled fire in the affected
compartment, which would constitute an
unsafe condition.
To avoid water absorbing filter element
blockage, this AD requires replacement [with
improved dual-filter assemblies] or
modification of the Halon dual-filter
assemblies of the lower deck cargo
compartment fire extinguishing system:
—In the forward cargo compartment for
aeroplanes fitted with Lower Deck Cargo
Compartment (LDCC) and
—In the bulk cargo compartment for
aeroplanes fitted with Bulk Cargo Rest
Compartment (BCRC) fire extinguishing
system.
ADDRESSES:
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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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; 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–2009–1215; Directorate Identifier
2009–NM–126–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
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Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0064,
dated March 12, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
You may obtain further information by
examining the MCAI in the AD docket.
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Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A330–26–3040, Revision 02,
dated August 6, 2008; Mandatory
Service Bulletin A340–26–4038,
Revision 02, dated August 6, 2008; and
Mandatory Service Bulletin A340–26–
5019, Revision 03, dated May 19, 2009.
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.
Differences Between This 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 proposed
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
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 32 products of U.S. registry.
We also estimate that it would take
about 13 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $708 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these costs. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of the
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Federal Register / Vol. 74, No. 248 / Tuesday, December 29, 2009 / Proposed Rules
proposed AD on U.S. operators to be
$55,936, or $1,748 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
cprice-sewell on DSK2BSOYB1PROD with PROPOSALS-1
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); 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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2009–1215;
Directorate Identifier 2009–NM–126–AD.
Comments Due Date
(a) We must receive comments by February
12, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to airplanes certificated
in any category, identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342 and –343 airplanes, all
serial numbers, except those on which
Airbus modification 55590 has been
embodied in production.
(2) Airbus Model A340–211, –212, –213,
–311, –312 –313, –541, and –642 airplanes,
all serial numbers fitted with lower deck
cargo compartment (LDCC), except those on
which Airbus modification 55590 has been
embodied in production.
(3) Airbus Model A340–311, –312 –313,
–541, and –642 airplanes, all serial numbers
fitted with bulk cargo rest compartment
(BCRC), except those on which Airbus
modification 56047 has been embodied in
production.
Note 1: The BCRC is embodied in
production on Airbus Model A340–300,
A340–500, and A340–600 airplanes through
the following Airbus modification (including
but not limited to): 47198, 47884, 48895,
48710, 49136, 50107, 50900, 50901, or 51320.
Note 2: The fire extinguishing system for
the BCRC is embodied in production on
Model A340–500 and A340–600 airplanes
through Mod 47197, (partial BCRC); on
Model A340–500 and A340–600 airplanes
through Mod 47883 (full BCRC); and on
Model A340–300 airplanes through Mod
50108 (partial BCRC).
Subject
(d) Air Transport Association (ATA) of
America Code 26: Fire protection.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During the qualification test campaign at
the supplier site of the prototype Flow
Metering Compact Unit (FMCU) Part Number
(P/N) QA07907–03, partial blockage of the
water absorbing filter element P/N QA06123
was observed several times. The blockage
was created by carbon debris from the
cartridge and from the burst disc of the Halon
bottle.
This water absorbing filter element is part
of Halon Dual-Filter Assembly installed also
in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing
System used in the A330 and A340
aeroplanes.
Blockage of the water absorbing filter
element could lead to reduction of Halon
outflow, leading to incapacity to maintain
fire extinguishing agent concentration.
Combined with fire, this could result in an
uncontrolled fire in the affected
compartment, which would constitute an
unsafe condition.
To avoid water absorbing filter element
blockage, this AD requires replacement [with
improved dual-filter assemblies] or
modification of the Halon dual-filter
assemblies of the lower deck cargo
compartment fire extinguishing system:
—In the forward cargo compartment for
aeroplanes fitted with Lower Deck Cargo
Compartment (LDCC) and
—In the bulk cargo compartment for
aeroplanes fitted with Bulk Cargo Rest
Compartment (BCRC) fire extinguishing
system.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Replace or modify the Halon dual-filter
assemblies of the flow metering fire
extinguishing system in the forward and bulk
cargo compartments, as applicable, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in Table 1 of this AD, at the
applicable time specified in paragraphs
(f)(1)(i), (f)(1)(ii), and (f)(1)(iii) of this AD.
TABLE 1—SERVICE BULLETINS
Airbus Mandatory
Service Bulletin—
Airbus model—
A330–200 and –300 airplanes .........................................................................
A340–200 and –300 airplanes .........................................................................
A340–500 and –600 airplanes .........................................................................
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68739
Revision—
A330–26–3040
A340–26–4038
A340–26–5019
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Dated—
02
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03
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August 6, 2008.
August 6, 2008.
May 19, 2009.
68740
Federal Register / Vol. 74, No. 248 / Tuesday, December 29, 2009 / Proposed Rules
(i) For airplanes fitted with Halon dualfilter assemblies part number (P/N) QA06753:
Within 18 months after the effective date of
this AD.
(ii) For Model A340–642 series airplanes,
weight variant 101, 102, and 103 fitted with
Halon dual-filter assembly P/N QA06753–01
or P/N QA06753–02: Within 18 months after
the effective date of this AD.
(iii) For airplanes other than those
identified in paragraph (f)(1)(ii) of this AD
and fitted with Halon dual-filter assembly P/
N QA06753–01 or P/N QA06753–02: Within
24 months after the effective date of this AD.
Note 3: The Halon dual-filter assembly
P/N QA06753 is embodied in production
through Airbus modification 40041. The
Halon dual-filter assembly P/N QA06753–01
is only embodied in service through Airbus
Service Bulletin A330–26–3030 or Airbus
Service Bulletin A340–26–4030. The Halon
dual-filter assembly P/N QA06753–02 is
embodied in production through
modification 47197 or 47883 or 50108
(BCRC) and 51065 or 51329 (LDCC) or in
service through Airbus Service Bulletin
A330–26–3030 or Airbus Service Bulletin
A340–26–4030.
(2) Actions accomplished before the
effective date of this AD according to the
service bulletins listed in Table 2 of this AD
are considered acceptable for compliance
with the corresponding actions specified in
this AD.
TABLE 2—CREDIT SERVICE BULLETINS
Airbus—
Revision—
Dated—
Mandatory Service Bulletin A340–26–5019 ......................................................................
Service Bulletin A330–26–3040 ........................................................................................
Service Bulletin A330–26–3040 ........................................................................................
Service Bulletin A340–26–4038 ........................................................................................
Service Bulletin A340–26–4038 ........................................................................................
Service Bulletin A340–26–5019 ........................................................................................
Service Bulletin A340–26–5019 ........................................................................................
02 ......................................
Original .............................
01 ......................................
Original .............................
01 ......................................
Original .............................
01 ......................................
August 6, 2008.
March 29, 2007.
December 19, 2007.
March 29, 2007.
December 19, 2007.
July 27, 2007.
January 23, 2008.
FAA AD Differences
Note 4: This AD differs from the MCAI
and/or service information as follows:
(1) The second paragraph of the
applicability of the MCAI specifies certain
models except those on which Modification
55590 has been done. Paragraph (c)(2) of this
AD specifies those models fitted with lower
deck cargo compartment (LDCC), except
those on which Modification 55590 has been
done.
(2) Although the MCAI tells you to submit
information to the manufacturer, this AD
does not require such a submittal.
Other FAA AD Provisions
(g) 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
reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2009–
0064, dated March 12, 2009; and the service
information identified in Table 3 of this AD
for related information.
TABLE 3—RELATED SERVICE INFORMATION
Airbus Mandatory Service Bulletin
Revision
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A330–26–3040 .....................................................................................................................................
A340–26–4038 .....................................................................................................................................
A340–26–5019 .....................................................................................................................................
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Date
02
02
03
29DEP1
August 6, 2008.
August 6, 2008.
May 19, 2009.
Federal Register / Vol. 74, No. 248 / Tuesday, December 29, 2009 / Proposed Rules
Issued in Renton, Washington, on
December 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–30649 Filed 12–28–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1214; Directorate
Identifier 2009–NM–091–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. (Type Certificate Previously Held
by Avro International Aerospace
Division; British Aerospace, PLC;
British Aerospace Commercial Aircraft
Limited; British Aerospace (England))
Model BD–100–1A10 (Challenger 300)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
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:
There has been an incident during a
production flight test where the proximitysensor electronic unit (PSEU) failed. This
resulted in unannunciated loss of:
• Wheel brakes below 10 knots;
• Thrust reverser;
• Nose wheel steering; and
• Auto-deployment of the multi-function
spoilers.
A similar condition, if not corrected, may
result in reduced controllability of the
aircraft upon landing and possible overrun of
the runway.
cprice-sewell on DSK2BSOYB1PROD with PROPOSALS-1
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by February 12, 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–
VerDate Nov<24>2008
15:17 Dec 28, 2009
Jkt 220001
68741
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.
For service information identified in
this proposed AD, contact Bombardier,
ˆ
Inc., 400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401;
e-mail thd.crj@aero.bombardier.com;
Internet https://www.bombardier.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221 or 425–227–1152.
authorities of other countries to provide
adequate time for interested parties to
submit comments. The comment period
for these proposed ADs is now typically
45 days, which is consistent with the
comment period for domestic transport
ADs.
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.
Examining the AD Docket
There has been an incident during a
production flight test where the proximitysensor electronic unit (PSEU) failed. This
resulted in unannunciated loss of:
• Wheel brakes below 10 knots;
• Thrust reverser;
• Nose wheel steering; and
• Auto-deployment of the multi-function
spoilers.
A similar condition, if not corrected, may
result in reduced controllability of the
aircraft upon landing and possible overrun of
the runway.
The original issue of this [Canadian]
directive mandated the introduction of nonnormal procedures to the airplane flight
manual (AFM) as an interim corrective action
to address PSEU failures.
Revision 1 of this directive amends the
aircraft applicability and introduces a note
providing terminating action, for use at
operator discretion, if the aircraft has
incorporated a PSEU with software version
12 in accordance with Bombardier Service
Bulletin (SB) 100–32–12.
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 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:
Bruce Valentine, Aerospace Engineer,
Avionics and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7328; fax
(516) 794–5531.
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–2009–1214; Directorate Identifier
2009–NM–091–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 have lengthened the 30-day
comment period for proposed ADs that
address MCAI originated by aviation
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2005–12R1,
dated December 23, 2008 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier has issued Temporary
Revision TR–39, dated March 2, 2005, to
the Bombardier Challenger 300 AFM,
CSP 100–1. 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
E:\FR\FM\29DEP1.SGM
29DEP1
]]>Agencies
[Federal Register Volume 74, Number 248 (Tuesday, December 29, 2009)]
[Proposed Rules]
[Pages 68737-68741]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-30649]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1215; Directorate Identifier 2009-NM-126-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200 and -300, and
Model A340-200, -300, -500 and 600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed 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:
* * * [P]artial blockage of the water absorbing filter element
P/N (part number) QA06123 was observed several times. The blockage
was created by carbon debris from the cartridge and from the burst
disc of the Halon bottle.
This water absorbing filter element is part of Halon Dual-Filter
Assembly installed also in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing System used in the A330 and
A340 aeroplanes.
Blockage of the water absorbing filter element could lead to
reduction of Halon outflow, leading to incapacity to maintain fire
extinguishing agent concentration. Combined with fire, this could
result in an uncontrolled fire in the affected compartment, which
would constitute an unsafe condition.
* * * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by February 12,
2010.
[[Page 68738]]
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.
For service information identified in this proposed AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80, e-mail airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221 or 425-227-1152.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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-2009-1215;
Directorate Identifier 2009-NM-126-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 have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
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 Community, has issued EASA
Airworthiness Directive 2009-0064, dated March 12, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During the qualification test campaign at the supplier site of
the prototype Flow Metering Compact Unit (FMCU) Part Number (P/N)
QA07907-03, partial blockage of the water absorbing filter element
P/N QA06123 was observed several times. The blockage was created by
carbon debris from the cartridge and from the burst disc of the
Halon bottle.
This water absorbing filter element is part of Halon Dual-Filter
Assembly installed also in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing System used in the A330 and
A340 aeroplanes.
Blockage of the water absorbing filter element could lead to
reduction of Halon outflow, leading to incapacity to maintain fire
extinguishing agent concentration. Combined with fire, this could
result in an uncontrolled fire in the affected compartment, which
would constitute an unsafe condition.
To avoid water absorbing filter element blockage, this AD
requires replacement [with improved dual-filter assemblies] or
modification of the Halon dual-filter assemblies of the lower deck
cargo compartment fire extinguishing system:
--In the forward cargo compartment for aeroplanes fitted with Lower
Deck Cargo Compartment (LDCC) and
--In the bulk cargo compartment for aeroplanes fitted with Bulk
Cargo Rest Compartment (BCRC) fire extinguishing system.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A330-26-3040, Revision
02, dated August 6, 2008; Mandatory Service Bulletin A340-26-4038,
Revision 02, dated August 6, 2008; and Mandatory Service Bulletin A340-
26-5019, Revision 03, dated May 19, 2009. 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.
Differences Between This 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 proposed 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 proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 32 products of U.S. registry. We also estimate that
it would take about 13 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $708 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the
[[Page 68739]]
proposed AD on U.S. operators to be $55,936, or $1,748 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify 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); 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2009-1215; Directorate Identifier 2009-NM-
126-AD.
Comments Due Date
(a) We must receive comments by February 12, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to airplanes certificated in any category,
identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342 and -343 airplanes, all serial
numbers, except those on which Airbus modification 55590 has been
embodied in production.
(2) Airbus Model A340-211, -212, -213, -311, -312 -313, -541,
and -642 airplanes, all serial numbers fitted with lower deck cargo
compartment (LDCC), except those on which Airbus modification 55590
has been embodied in production.
(3) Airbus Model A340-311, -312 -313, -541, and -642 airplanes,
all serial numbers fitted with bulk cargo rest compartment (BCRC),
except those on which Airbus modification 56047 has been embodied in
production.
Note 1: The BCRC is embodied in production on Airbus Model A340-
300, A340-500, and A340-600 airplanes through the following Airbus
modification (including but not limited to): 47198, 47884, 48895,
48710, 49136, 50107, 50900, 50901, or 51320.
Note 2: The fire extinguishing system for the BCRC is embodied
in production on Model A340-500 and A340-600 airplanes through Mod
47197, (partial BCRC); on Model A340-500 and A340-600 airplanes
through Mod 47883 (full BCRC); and on Model A340-300 airplanes
through Mod 50108 (partial BCRC).
Subject
(d) Air Transport Association (ATA) of America Code 26: Fire
protection.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During the qualification test campaign at the supplier site of
the prototype Flow Metering Compact Unit (FMCU) Part Number (P/N)
QA07907-03, partial blockage of the water absorbing filter element
P/N QA06123 was observed several times. The blockage was created by
carbon debris from the cartridge and from the burst disc of the
Halon bottle.
This water absorbing filter element is part of Halon Dual-Filter
Assembly installed also in the Flow Metering System (FMS) of the
cargo compartment Fire Extinguishing System used in the A330 and
A340 aeroplanes.
Blockage of the water absorbing filter element could lead to
reduction of Halon outflow, leading to incapacity to maintain fire
extinguishing agent concentration. Combined with fire, this could
result in an uncontrolled fire in the affected compartment, which
would constitute an unsafe condition.
To avoid water absorbing filter element blockage, this AD
requires replacement [with improved dual-filter assemblies] or
modification of the Halon dual-filter assemblies of the lower deck
cargo compartment fire extinguishing system:
--In the forward cargo compartment for aeroplanes fitted with Lower
Deck Cargo Compartment (LDCC) and
--In the bulk cargo compartment for aeroplanes fitted with Bulk
Cargo Rest Compartment (BCRC) fire extinguishing system.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Replace or modify the Halon dual-filter assemblies of the
flow metering fire extinguishing system in the forward and bulk
cargo compartments, as applicable, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in Table 1 of this AD, at the applicable time specified
in paragraphs (f)(1)(i), (f)(1)(ii), and (f)(1)(iii) of this AD.
Table 1--Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory
Airbus model-- Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A330-200 and -300 airplanes........ A330-26-3040 02 August 6, 2008.
A340-200 and -300 airplanes........ A340-26-4038 02 August 6, 2008.
A340-500 and -600 airplanes........ A340-26-5019 03 May 19, 2009.
----------------------------------------------------------------------------------------------------------------
[[Page 68740]]
(i) For airplanes fitted with Halon dual-filter assemblies part
number (P/N) QA06753: Within 18 months after the effective date of
this AD.
(ii) For Model A340-642 series airplanes, weight variant 101,
102, and 103 fitted with Halon dual-filter assembly P/N QA06753-01
or P/N QA06753-02: Within 18 months after the effective date of this
AD.
(iii) For airplanes other than those identified in paragraph
(f)(1)(ii) of this AD and fitted with Halon dual-filter assembly P/N
QA06753-01 or P/N QA06753-02: Within 24 months after the effective
date of this AD.
Note 3: The Halon dual-filter assembly P/N QA06753 is embodied
in production through Airbus modification 40041. The Halon dual-
filter assembly P/N QA06753-01 is only embodied in service through
Airbus Service Bulletin A330-26-3030 or Airbus Service Bulletin
A340-26-4030. The Halon dual-filter assembly P/N QA06753-02 is
embodied in production through modification 47197 or 47883 or 50108
(BCRC) and 51065 or 51329 (LDCC) or in service through Airbus
Service Bulletin A330-26-3030 or Airbus Service Bulletin A340-26-
4030.
(2) Actions accomplished before the effective date of this AD
according to the service bulletins listed in Table 2 of this AD are
considered acceptable for compliance with the corresponding actions
specified in this AD.
Table 2--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A340-26- 02................................... August 6, 2008.
5019.
Service Bulletin A330-26-3040..... Original............................. March 29, 2007.
Service Bulletin A330-26-3040..... 01................................... December 19, 2007.
Service Bulletin A340-26-4038..... Original............................. March 29, 2007.
Service Bulletin A340-26-4038..... 01................................... December 19, 2007.
Service Bulletin A340-26-5019..... Original............................. July 27, 2007.
Service Bulletin A340-26-5019..... 01................................... January 23, 2008.
----------------------------------------------------------------------------------------------------------------
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information
as follows:
(1) The second paragraph of the applicability of the MCAI
specifies certain models except those on which Modification 55590
has been done. Paragraph (c)(2) of this AD specifies those models
fitted with lower deck cargo compartment (LDCC), except those on
which Modification 55590 has been done.
(2) Although the MCAI tells you to submit information to the
manufacturer, this AD does not require such a submittal.
Other FAA AD Provisions
(g) 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 reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(h) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0064, dated March 12, 2009; and the service
information identified in Table 3 of this AD for related
information.
Table 3--Related Service Information
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A330-26-3040................................. 02 August 6, 2008.
A340-26-4038................................. 02 August 6, 2008.
A340-26-5019................................. 03 May 19, 2009.
----------------------------------------------------------------------------------------------------------------
[[Page 68741]]
Issued in Renton, Washington, on December 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-30649 Filed 12-28-09; 8:45 am]
BILLING CODE 4910-13-P
