Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -106 Airplanes and DHC-8-200, -300, and -400 Series Airplanes, 1164-1166 [E9-323]
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Federal Register / Vol. 74, No. 7 / Monday, January 12, 2009 / Proposed Rules
modification required by paragraph (a) of this
AD.
Alternative Methods of Compliance
(b)(1) An alternative method of compliance
or adjustment of the compliance time that
provides an acceptable level of safety may be
used if approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA.
Operators shall submit their requests through
an appropriate FAA Principal Maintenance
Inspector, who may add comments and then
send it to the Manager, Seattle ACO.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on
December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–322 Filed 1–9–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1361; Directorate
Identifier 2008–NM–140–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, and –106
Airplanes and DHC–8–200, –300, and
–400 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
dwashington3 on PROD1PC60 with PROPOSALS
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:
A fuselage spoiler cable disconnect sensing
device was installed in production on later
DHC–8 Series 100/200/300 aircraft, and on
all DHC–8 Series 400 aircraft. On earlier
DHC–8 Series 100/200/300 aircraft, its
installation was mandated by [Canadian]
Airworthiness Directive CF–2006–13 [which
corresponds to FAA AD 2007–21–16].
However, several incorrectly assembled
spoiler cable disconnect sensing devices have
recently been discovered on in-service
VerDate Nov<24>2008
14:08 Jan 09, 2009
Jkt 217001
aircraft. A pulley and plastic spacer had been
inadvertently interchanged during assembly
of the device in production, resulting in the
spoiler cable sliding on the spacer rather than
on the pulley, as designed.
Continued operation with an incorrectly
assembled spoiler cable disconnect sensing
device could result in impaired operation of
the sensing device and/or an eventual
fuselage spoiler cable disconnect, with
possible reduced controllability of the
aircraft.
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 11, 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
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: Dan
Parrillo, Aerospace Engineer, Airframe
and Propulsion Branch, ANE–171, FAA,
New York Aircraft Certification Office,
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7305; 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–2008–1361; Directorate Identifier
2008–NM–140–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–2008–28,
dated July 10, 2008 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
A fuselage spoiler cable disconnect sensing
device was installed in production on later
DHC–8 Series 100/200/300 aircraft, and on
all DHC–8 Series 400 aircraft. On earlier
DHC–8 Series 100/200/300 aircraft, its
installation was mandated by [Canadian]
Airworthiness Directive CF–2006–13 [which
corresponds to FAA AD 2007–21–16].
However, several incorrectly assembled
spoiler cable disconnect sensing devices have
recently been discovered on in-service
aircraft. A pulley and plastic spacer had been
inadvertently interchanged during assembly
of the device in production, resulting in the
spoiler cable sliding on the spacer rather than
on the pulley, as designed.
Continued operation with an incorrectly
assembled spoiler cable disconnect sensing
device could result in impaired operation of
the sensing device and/or an eventual
fuselage spoiler cable disconnect, with
possible reduced controllability of the
aircraft.
Required actions include inspecting the
fuselage spoiler cable disconnect
sensing device and, if necessary,
inspecting components for wear and
damage, replacing worn or damaged
components, and correctly reassembling the sensing device. You may
obtain further information by examining
the MCAI in the AD docket.
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Federal Register / Vol. 74, No. 7 / Monday, January 12, 2009 / Proposed Rules
Relevant Service Information
Bombardier has issued Service
Bulletins 84–27–34, dated October 3,
2007, and 8–27–107, dated October 16,
2007. 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 145 products of U.S.
registry. We also estimate that it would
take about 1 work-hour per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$11,600, or $80 per product.
dwashington3 on PROD1PC60 with PROPOSALS
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.
VerDate Nov<24>2008
14:08 Jan 09, 2009
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1165
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.
Comments Due Date
(a) We must receive comments by February
11, 2009.
Regulatory Findings
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
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:
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2008–1361;
Directorate Identifier 2008–NM–140–AD.
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
Bombardier Model DHC–8 airplanes,
certificated in any category.
(1) Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 airplanes, serial
numbers 003 through 644 inclusive.
(2) Model DHC–8–400, –401 and –402
airplanes, serial numbers 4003, 4004, 4006,
and 4008 through 4164 inclusive.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A fuselage spoiler cable disconnect sensing
device was installed in production on later
DHC–8 Series 100/200/300 aircraft, and on
all DHC–8 Series 400 aircraft. On earlier
DHC–8 Series 100/200/300 aircraft, its
installation was mandated by [Canadian]
Airworthiness Directive CF–2006–13 [which
corresponds to FAA AD 2007–21–16].
However, several incorrectly assembled
spoiler cable disconnect sensing devices have
recently been discovered on in-service
aircraft. A pulley and plastic spacer had been
inadvertently interchanged during assembly
of the device in production, resulting in the
spoiler cable sliding on the spacer rather than
on the pulley, as designed.
Continued operation with an incorrectly
assembled spoiler cable disconnect sensing
device could result in impaired operation of
the sensing device and/or an eventual
fuselage spoiler cable disconnect, with
possible reduced controllability of the
aircraft.
Required actions include inspecting the
fuselage spoiler cable disconnect sensing
device and, if necessary, inspecting
components for wear and damage, replacing
worn or damaged components, and correctly
re-assembling the sensing device.
Actions and Compliance
(f) Unless already done, do the following.
(1) For Bombardier Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and –315
airplanes, serial numbers 003 through 561
inclusive: Do the actions required by
paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as
applicable, in accordance with paragraph
3.B., Part A, of Bombardier Service Bulletin
8–27–107, dated October 16, 2007.
(i) For airplanes on which fuselage spoiler
cable disconnect sensing device, Modsum
8Q100898, has been installed as of the
effective date of this AD: Within 1,000 flight
hours after the effective date of this AD,
inspect the fuselage spoiler cable disconnect
sensing device for correct assembly.
(ii) For airplanes on which fuselage spoiler
cable disconnect sensing device, Modsum
8Q100898, has not been installed as of the
effective date of this AD: Concurrently with
E:\FR\FM\12JAP1.SGM
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1166
Federal Register / Vol. 74, No. 7 / Monday, January 12, 2009 / Proposed Rules
the installation of Modsum 8Q100898,
inspect the fuselage spoiler cable disconnect
sensing device for correct assembly.
Note 1: AD 2007–21–16 requires the
installation of Modsum 8Q100898.
(2) For Bombardier Model –102, –103,
–106, –201, –202, –301, –311, and –315
airplanes, serial numbers 562 through 644
inclusive: Within 1,000 flight hours after the
effective date of this AD, inspect the fuselage
spoiler cable disconnect sensing device for
correct assembly in accordance with
paragraph 3.B., Part A, of Bombardier Service
Bulletin 8–27–107, dated October 16, 2007.
Note 2: The fuselage spoiler cable
disconnect sensing device was installed in
production on the airplanes identified in
paragraph (f)(2) of this AD.
(3) For Bombardier Model DHC 8–400,
–401, and –402 airplanes, serial numbers
4003, 4004, 4006, and 4008 through 4164
inclusive: Within 1,000 flight hours after the
effective date of this AD, inspect the fuselage
spoiler cable disconnect sensing device for
correct assembly in accordance with
paragraph 3.B., Part A, of Bombardier Service
Bulletin 84–27–34 dated October 3, 2007.
dwashington3 on PROD1PC60 with PROPOSALS
Note 3: The fuselage spoiler cable
disconnect sensing device was installed in
production on the airplanes identified in
paragraph (f)(3) of this AD.
VerDate Nov<24>2008
14:08 Jan 09, 2009
Jkt 217001
(4) For all airplanes: If an incorrectly
assembled sensing device is detected during
any inspection required by paragraphs (f)(1),
(f)(2), or (f)(3) of this AD, before further flight,
inspect the components, replace worn or
damaged components, and correctly reassemble the sensing device. Do the actions
in accordance with paragraph 3.B., Part B, of
Bombardier Service Bulletin 8–27–107, dated
October 16, 2007; or Bombardier Service
Bulletin 84–27–34, dated October 3, 2007; as
applicable.
FAA AD Differences
Note 4: This AD differs from the MCAI
and/or service information as follows: No
difference.
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, 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: Dan Parrillo,
Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228–7305; fax
(516) 794–5531. Before using any approved
AMOC on any airplane to which the AMOC
applies, notify your appropriate principal
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your
local FSDO.
(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–2008–28, dated July 10, 2008;
Bombardier Service Bulletin 84–27–34, dated
October 3, 2007; and Bombardier Service
Bulletin 8–27–107 dated October 16, 2007;
for related information.
Issued in Renton, Washington, on
December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–323 Filed 1–9–09; 8:45 am]
BILLING CODE 4910–13–P
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12JAP1
]]>Agencies
[Federal Register Volume 74, Number 7 (Monday, January 12, 2009)]
[Proposed Rules]
[Pages 1164-1166]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-323]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1361; Directorate Identifier 2008-NM-140-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes and DHC-8-200, -300, and -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
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:
A fuselage spoiler cable disconnect sensing device was installed
in production on later DHC-8 Series 100/200/300 aircraft, and on all
DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300
aircraft, its installation was mandated by [Canadian] Airworthiness
Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].
However, several incorrectly assembled spoiler cable disconnect
sensing devices have recently been discovered on in-service
aircraft. A pulley and plastic spacer had been inadvertently
interchanged during assembly of the device in production, resulting
in the spoiler cable sliding on the spacer rather than on the
pulley, as designed.
Continued operation with an incorrectly assembled spoiler cable
disconnect sensing device could result in impaired operation of the
sensing device and/or an eventual fuselage spoiler cable disconnect,
with possible reduced controllability of the aircraft.
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 11,
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: Dan Parrillo, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7305; 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-2008-1361;
Directorate Identifier 2008-NM-140-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-
2008-28, dated July 10, 2008 (referred to after this as ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
A fuselage spoiler cable disconnect sensing device was installed
in production on later DHC-8 Series 100/200/300 aircraft, and on all
DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300
aircraft, its installation was mandated by [Canadian] Airworthiness
Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].
However, several incorrectly assembled spoiler cable disconnect
sensing devices have recently been discovered on in-service
aircraft. A pulley and plastic spacer had been inadvertently
interchanged during assembly of the device in production, resulting
in the spoiler cable sliding on the spacer rather than on the
pulley, as designed.
Continued operation with an incorrectly assembled spoiler cable
disconnect sensing device could result in impaired operation of the
sensing device and/or an eventual fuselage spoiler cable disconnect,
with possible reduced controllability of the aircraft.
Required actions include inspecting the fuselage spoiler cable
disconnect sensing device and, if necessary, inspecting components for
wear and damage, replacing worn or damaged components, and correctly
re-assembling the sensing device. You may obtain further information by
examining the MCAI in the AD docket.
[[Page 1165]]
Relevant Service Information
Bombardier has issued Service Bulletins 84-27-34, dated October 3,
2007, and 8-27-107, dated October 16, 2007. 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 145 products of U.S. registry. We also estimate that
it would take about 1 work-hour per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $11,600, or $80 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:
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2008-
1361; Directorate Identifier 2008-NM-140-AD.
Comments Due Date
(a) We must receive comments by February 11, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following Bombardier Model DHC-8
airplanes, certificated in any category.
(1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes, serial numbers 003 through 644 inclusive.
(2) Model DHC-8-400, -401 and -402 airplanes, serial numbers
4003, 4004, 4006, and 4008 through 4164 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A fuselage spoiler cable disconnect sensing device was installed
in production on later DHC-8 Series 100/200/300 aircraft, and on all
DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300
aircraft, its installation was mandated by [Canadian] Airworthiness
Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].
However, several incorrectly assembled spoiler cable disconnect
sensing devices have recently been discovered on in-service
aircraft. A pulley and plastic spacer had been inadvertently
interchanged during assembly of the device in production, resulting
in the spoiler cable sliding on the spacer rather than on the
pulley, as designed.
Continued operation with an incorrectly assembled spoiler cable
disconnect sensing device could result in impaired operation of the
sensing device and/or an eventual fuselage spoiler cable disconnect,
with possible reduced controllability of the aircraft.
Required actions include inspecting the fuselage spoiler cable
disconnect sensing device and, if necessary, inspecting components
for wear and damage, replacing worn or damaged components, and
correctly re-assembling the sensing device.
Actions and Compliance
(f) Unless already done, do the following.
(1) For Bombardier Model DHC-8-102, -103, -106, -201, -202, -
301, -311, and -315 airplanes, serial numbers 003 through 561
inclusive: Do the actions required by paragraph (f)(1)(i) or
(f)(1)(ii) of this AD, as applicable, in accordance with paragraph
3.B., Part A, of Bombardier Service Bulletin 8-27-107, dated October
16, 2007.
(i) For airplanes on which fuselage spoiler cable disconnect
sensing device, Modsum 8Q100898, has been installed as of the
effective date of this AD: Within 1,000 flight hours after the
effective date of this AD, inspect the fuselage spoiler cable
disconnect sensing device for correct assembly.
(ii) For airplanes on which fuselage spoiler cable disconnect
sensing device, Modsum 8Q100898, has not been installed as of the
effective date of this AD: Concurrently with
[[Page 1166]]
the installation of Modsum 8Q100898, inspect the fuselage spoiler
cable disconnect sensing device for correct assembly.
Note 1: AD 2007-21-16 requires the installation of Modsum
8Q100898.
(2) For Bombardier Model -102, -103, -106, -201, -202, -301, -
311, and -315 airplanes, serial numbers 562 through 644 inclusive:
Within 1,000 flight hours after the effective date of this AD,
inspect the fuselage spoiler cable disconnect sensing device for
correct assembly in accordance with paragraph 3.B., Part A, of
Bombardier Service Bulletin 8-27-107, dated October 16, 2007.
Note 2: The fuselage spoiler cable disconnect sensing device was
installed in production on the airplanes identified in paragraph
(f)(2) of this AD.
(3) For Bombardier Model DHC 8-400, -401, and -402 airplanes,
serial numbers 4003, 4004, 4006, and 4008 through 4164 inclusive:
Within 1,000 flight hours after the effective date of this AD,
inspect the fuselage spoiler cable disconnect sensing device for
correct assembly in accordance with paragraph 3.B., Part A, of
Bombardier Service Bulletin 84-27-34 dated October 3, 2007.
Note 3: The fuselage spoiler cable disconnect sensing device was
installed in production on the airplanes identified in paragraph
(f)(3) of this AD.
(4) For all airplanes: If an incorrectly assembled sensing
device is detected during any inspection required by paragraphs
(f)(1), (f)(2), or (f)(3) of this AD, before further flight, inspect
the components, replace worn or damaged components, and correctly
re-assemble the sensing device. Do the actions in accordance with
paragraph 3.B., Part B, of Bombardier Service Bulletin 8-27-107,
dated October 16, 2007; or Bombardier Service Bulletin 84-27-34,
dated October 3, 2007; as applicable.
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information
as follows: No difference.
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, 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: Dan Parrillo, Aerospace
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516) 228-7305; fax (516) 794-
5531. Before using any approved AMOC on any airplane to which the
AMOC applies, notify your appropriate principal inspector (PI) in
the FAA Flight Standards District Office (FSDO), or lacking a PI,
your local FSDO.
(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-2008-28,
dated July 10, 2008; Bombardier Service Bulletin 84-27-34, dated
October 3, 2007; and Bombardier Service Bulletin 8-27-107 dated
October 16, 2007; for related information.
Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-323 Filed 1-9-09; 8:45 am]
BILLING CODE 4910-13-P
