Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 45783-45785 [E9-21337]
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Federal Register / Vol. 74, No. 171 / Friday, September 4, 2009 / Proposed Rules
A340–541 and –642 airplanes; all serial
numbers; certificated in any category.
which would all constitute unsafe conditions
at speeds above 30 knots.
‘‘As a precautionary measure, this AD
requires detailed inspections under the bogie
stop pad of both MLG bogie beams and, in
case deformation or damage is detected, to
apply the associated repair.’’
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing gear.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
‘‘During a scheduled maintenance
inspection on the MLG [main landing gear],
the bogie stop pad was found deformed and
cracked. Upon removal of the bogie stop pad
for replacement, the bogie beam was also
found cracked.
‘‘Laboratory investigation indicates that an
overload event has occurred and no fatigue
propagation of the crack was evident. An
investigation is still underway to establish
the root cause of this overload.
‘‘A second bogie beam crack has
subsequently been found on another aircraft,
located under a bogie stop pad which only
had superficial paint damage.
‘‘This condition, if not detected and
corrected, could result in the aircraft
departing the runway or to the bogie
detaching from the aircraft or gear collapses,
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) At the applicable compliance time
specified in paragraph (f)(1)(i), (f)(1)(ii),
(f)(1)(iii), (f)(1)(iv), (f)(1)(v), or (f)(1)(vi) of this
AD, perform one-time detailed inspections of
both main landing gear bogie beams in the
region of the bogie stop pad for detection of
deformation and damage, and apply the
applicable corrective actions, in accordance
with instructions defined in the Airbus
mandatory service bulletins listed in Table 1
of this AD, as applicable. Do all applicable
corrective actions before further flight.
(i) Airplanes with 22 months or less and
2,500 flight cycles or less from the first flight
with the original bogie beam as of the
effective date of this AD: Not earlier than
2,500 flight cycles or 22 months on the
original bogie beam, whichever occurs first,
but not later than 40 months from first flight.
45783
(ii) Airplanes with 22 months or less and
2,500 flight cycles or less on a new bogie
beam installed in service as of the effective
date of this AD: Not earlier than 2,500 flight
cycles or 22 months on the new bogie beam,
whichever occurs first, but no later than 40
months from the installation of a new bogie
beam in service.
(iii) Airplanes with 22 months or less and
2,500 flight cycles or less on an overhauled
bogie beam as of the effective date of this AD:
Not earlier than 2,500 flight cycles or 22
months on the overhauled bogie beam,
whichever occurs first, but no later than 40
months from the last overhaul.
(iv) Airplanes with more than 22 months
or more than 2,500 flight cycles from the first
flight with the original bogie beam, as of the
effective date of this AD: Within 18 months
after the effective date of this AD.
(v) Airplanes with more than 22 months or
more than 2,500 flight cycles on a new bogie
beam installed in service, as of the effective
date of this AD: Within 18 months after the
effective date of this AD.
(vi) Airplanes with more than 22 months
or more than 2,500 flight cycles on an
overhauled bogie beam, as of the effective
date of this AD: Within 18 months after the
effective date of this AD.
TABLE 1—SERVICE BULLETINS
For model—
Use Airbus Mandatory Service
Bulletin—
Dated—
A330–201, –202, –203, –223, –243, –301, –302, –303, –321,
–322, –323, –341, –342, –343 series airplanes.
A340–211, –212, –213, –311, –312, –313 series airplanes ...........
A340–541, –642 airplanes ...............................................................
A330–32–3220 ...........................
October 10, 2008.
A340–32–4264 ...........................
A340–32–5087 ...........................
October 10, 2008.
October 10, 2008.
(2) Report the results, including no
findings of the inspection required by
paragraph (f)(1) of this AD, to Airbus,
Customer Services Directorate,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex France; Attn: SEDCC1
Technical Data and Documentation Services;
Fax (+33) 5 61 93 28 06; e-mail
sb.reporting@airbus.com; at the applicable
time specified in paragraph (f)(2)(i) or
(f)(2)(ii) of this AD.
(i) If the inspection is done on or after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(ii) If the inspection was accomplished
prior to the effective date of this AD: Submit
the report within 30 days after the effective
date of this AD.
FAA AD Differences
pwalker on DSK8KYBLC1PROD with PROPOSALS
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, 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,
VerDate Nov<24>2008
16:07 Sep 03, 2009
Jkt 217001
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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0223, dated December 15,
2008, and the Airbus mandatory service
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
bulletins listed in Table 1 of this AD, for
related information.
Issued in Renton, Washington, on August
26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21317 Filed 9–3–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0784; Directorate
Identifier 2009–NM–109–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 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
E:\FR\FM\04SEP1.SGM
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45784
Federal Register / Vol. 74, No. 171 / Friday, September 4, 2009 / Proposed Rules
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:
Several operators have reported cases of
inadvertent single spoiler deployment during
flight on the DHC–8 Series 400 aircraft.
Investigation has revealed that the probable
cause for this deployment is internal
contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve
armature.
This condition, if not corrected, could
cause uncommanded deployment of the
spoilers resulting in increased drag and in
combination with a loss of aileron, could
result in a significant reduction in aircraft
roll control.
pwalker on DSK8KYBLC1PROD with PROPOSALS
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 October 5, 2009.
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 Bombardier,
ˆ
Inc., 400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email thd.qseries@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.
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
VerDate Nov<24>2008
16:07 Sep 03, 2009
Jkt 217001
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:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7318; 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–2009–0784; Directorate Identifier
2009–NM–109–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2009–26,
dated May 21, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Several operators have reported cases of
inadvertent single spoiler deployment during
flight on the DHC–8 Series 400 aircraft.
Investigation has revealed that the probable
cause for this deployment is internal
contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve
armature.
This condition, if not corrected, could
cause uncommanded deployment of the
spoilers resulting in increased drag and in
combination with a loss of aileron, could
result in a significant reduction in aircraft
roll control.
Corrective actions include upgrading,
testing, and re-identifying the spoiler lift
dump valves after replacing the pressure
port inlet fitting. You may obtain further
information by examining the MCAI in
the AD docket.
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
Relevant Service Information
Bombardier has issued Service
Bulletin 84–27–43, dated January 29,
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 61 products of U.S. registry.
We also estimate that it would take
about 6 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 $0 per product.
Where the service information lists
required parts costs that are covered
under warranty, we have assumed that
there will be no charge for these costs.
As we do not control warranty coverage
for affected parties, some parties may
incur costs higher than estimated here.
Based on these figures, we estimate the
cost of the proposed AD on U.S.
operators to be $29,280, or $480 per
product.
E:\FR\FM\04SEP1.SGM
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Federal Register / Vol. 74, No. 171 / Friday, September 4, 2009 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
pwalker on DSK8KYBLC1PROD with PROPOSALS
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:
VerDate Nov<24>2008
16:07 Sep 03, 2009
Jkt 217001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2009–0784;
Directorate Identifier 2009–NM–109–AD.
Comments Due Date
(a) We must receive comments by October
5, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400, DHC–8–401, and DHC–8–402
series airplanes, certificated in any category,
serial numbers 4001 through 4237 inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 24: Electrical power.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Several operators have reported cases of
inadvertent single spoiler deployment during
flight on the DHC–8 Series 400 aircraft.
Investigation has revealed that the probable
cause for this deployment is internal
contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve
armature.
This condition, if not corrected, could
cause uncommanded deployment of the
spoilers resulting in increased drag and in
combination with a loss of aileron, could
result in a significant reduction in aircraft
roll control.
Corrective actions include upgrading,
testing, and re-identifying the spoiler lift
dump valves after replacing the pressure port
inlet fitting.
Actions and Compliance
(f) Unless already done, within 5,000 flight
hours after the effective date of this AD,
incorporate Bombardier Modsum 4–113554
to add a filter/restrictor fitting to the spoiler
lift dump valve, in accordance with
Bombardier Service Bulletin 84–27–43, dated
January 29, 2009.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), 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: Cesar
Gomez, Aerospace Engineer, Airframe and
Mechanical Systems Branch, ANE–171, FAA,
New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, New York 11590; telephone
(516) 228–7318; fax (516) 794–5531. Before
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
45785
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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Canadian Airworthiness
Directive CF–2009–26, dated May 21, 2009;
and Bombardier Service Bulletin 84–27–43,
dated January 29, 2009; for related
information.
Issued in Renton, Washington, on August
26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21337 Filed 9–3–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0783; Directorate
Identifier 2009–NM–081–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–90–30 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
McDonnell Douglas Model MD–90–30
airplanes. This proposed AD would
require repetitive inspections for
cracking of the overwing frames at
stations 883, 902, 924, 943, and 962, left
and right sides, and corrective actions if
necessary. This proposed AD results
from reports of cracked overwing
frames. We are proposing this AD to
detect and correct such cracking, which
could sever the frame, increase the
loading of adjacent frames, and result in
E:\FR\FM\04SEP1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 171 (Friday, September 4, 2009)]
[Proposed Rules]
[Pages 45783-45785]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-21337]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0784; Directorate Identifier 2009-NM-109-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 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
[[Page 45784]]
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:
Several operators have reported cases of inadvertent single
spoiler deployment during flight on the DHC-8 Series 400 aircraft.
Investigation has revealed that the probable cause for this
deployment is internal contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve armature.
This condition, if not corrected, could cause uncommanded
deployment of the spoilers resulting in increased drag and in
combination with a loss of aileron, could result in a significant
reduction in aircraft roll control.
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 October 5, 2009.
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
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail
thd.qseries@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.
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: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7318; 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-2009-0784;
Directorate Identifier 2009-NM-109-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-26, dated May 21, 2009 (referred to after this as ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
Several operators have reported cases of inadvertent single
spoiler deployment during flight on the DHC-8 Series 400 aircraft.
Investigation has revealed that the probable cause for this
deployment is internal contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve armature.
This condition, if not corrected, could cause uncommanded
deployment of the spoilers resulting in increased drag and in
combination with a loss of aileron, could result in a significant
reduction in aircraft roll control.
Corrective actions include upgrading, testing, and re-identifying
the spoiler lift dump valves after replacing the pressure port inlet
fitting. You may obtain further information by examining the MCAI in
the AD docket.
Relevant Service Information
Bombardier has issued Service Bulletin 84-27-43, dated January 29,
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 61 products of U.S. registry. We also estimate that
it would take about 6 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 $0 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $29,280, or $480 per product.
[[Page 45785]]
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:
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2009-
0784; Directorate Identifier 2009-NM-109-AD.
Comments Due Date
(a) We must receive comments by October 5, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401,
and DHC-8-402 series airplanes, certificated in any category, serial
numbers 4001 through 4237 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Several operators have reported cases of inadvertent single
spoiler deployment during flight on the DHC-8 Series 400 aircraft.
Investigation has revealed that the probable cause for this
deployment is internal contamination of the Lift/Dump (L/D) valve
and moisture ingress into the L/D valve armature.
This condition, if not corrected, could cause uncommanded
deployment of the spoilers resulting in increased drag and in
combination with a loss of aileron, could result in a significant
reduction in aircraft roll control.
Corrective actions include upgrading, testing, and re-
identifying the spoiler lift dump valves after replacing the
pressure port inlet fitting.
Actions and Compliance
(f) Unless already done, within 5,000 flight hours after the
effective date of this AD, incorporate Bombardier Modsum 4-113554 to
add a filter/restrictor fitting to the spoiler lift dump valve, in
accordance with Bombardier Service Bulletin 84-27-43, dated January
29, 2009.
FAA AD Differences
Note 1:
This AD differs from the MCAI and/or service information as
follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), 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: Cesar Gomez, Aerospace
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7318; fax (516) 794-5531. 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI Canadian Airworthiness Directive CF-2009-26,
dated May 21, 2009; and Bombardier Service Bulletin 84-27-43, dated
January 29, 2009; for related information.
Issued in Renton, Washington, on August 26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-21337 Filed 9-3-09; 8:45 am]
BILLING CODE 4910-13-P
