Airworthiness Directives; Bombardier Model DHC-8-400, -401 and -402 Airplanes, 30005-30007 [E8-11566]
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Federal Register / Vol. 73, No. 101 / Friday, May 23, 2008 / Proposed Rules
the forward lower flange of the flap tracks of
the trailing edge flaps by doing all the actions
specified in Parts 1 and 3 of the
Accomplishment Instructions of the service
bulletin; except as provided by paragraph (i)
of this AD. Do all applicable corrective
actions before further flight. Repeat the
applicable inspection at the applicable time
specified in paragraph 1.E. of the service
bulletin.
Issued in Renton, Washington, on May 16,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–11565 Filed 5–22–08; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
(g) For Groups 1, 2, and 3 airplanes: Within
24 months after the effective date of this AD,
replace the fail-safe links, pins, and
attachment hardware in accordance with Part
2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2323,
dated February 21, 2008.
14 CFR Part 39
(h) Where Boeing Alert Service Bulletin
747–57A2323, dated February 21, 2008,
specifies counting the compliance time from
‘‘* * * the date on this service bulletin,’’ this
AD requires counting the compliance time
from the effective date of this AD.
Exception to Corrective Actions
(i) If any fractured support fitting is found
during any inspection required by this AD,
and Boeing Alert Service Bulletin 747–
57A2323, dated February 21, 2008, specifies
to contact Boeing for appropriate action:
Before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
dwashington3 on PRODPC61 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN: Gary
Oltman, Aerospace Engineer, Airframe
Branch, ANM–120S, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6443; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
VerDate Aug<31>2005
15:17 May 22, 2008
Jkt 214001
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Modification of Fail Safe Links of Main
Carriage
Exception to Compliance Times
30005
[Docket No. FAA–2008–0586; Directorate
Identifier 2008–NM–043–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400, –401 and –402
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 was one reported failure of the
elevator centering torsion spring.
Investigation revealed that the tangs on the
torsion spring had been bent due to difficulty
encountered during installation of the
elevator centering torsion spring on the
horizontal stabilizer torque tube. The
bending of the tangs on the torsion spring
would degrade its durability and could lead
to premature failure of the elevator centering
torsion spring. A control rod disconnect
between the elevator aft quadrant and the
elevator Power Control Unit input torque
tube, in combination with the loss or
reduction in elevator centering capability,
could result in a significant reduction in
aircraft pitch 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 June 23, 2008.
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.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
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:
Fabio Buttitta, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7303; 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–2008–0586; Directorate Identifier
2008–NM–043–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–2008–05R1,
dated February 27, 2008. (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
There was one reported failure of the
elevator centering torsion spring.
Investigation revealed that the tangs on the
E:\FR\FM\23MYP1.SGM
23MYP1
30006
Federal Register / Vol. 73, No. 101 / Friday, May 23, 2008 / Proposed Rules
torsion spring had been bent due to difficulty
encountered during installation of the
elevator centering torsion spring on the
horizontal stabilizer torque tube. The
bending of the tangs on the torsion spring
would degrade its durability and could lead
to premature failure of the elevator centering
torsion spring. A control rod disconnect
between the elevator aft quadrant and the
elevator Power Control Unit input torque
tube, in combination with the loss or
reduction in elevator centering capability,
could result in a significant reduction in
aircraft pitch control.
Corrective actions include replacing
all elevator centering torsion springs
with new elevator centering torsion
springs. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Bombardier has issued Service
Bulletin 84–27–31, dated April 27,
2007. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
dwashington3 on PRODPC61 with PROPOSALS
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 42 products of U.S. registry.
VerDate Aug<31>2005
15:17 May 22, 2008
Jkt 214001
We also estimate that it would take
about 7 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 $1,746 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
$96,852, or $2,306 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
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, 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–2008–0586;
Directorate Identifier 2008–NM–043–AD.
Comments Due Date
(a) We must receive comments by June 23,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400, –401 and –402 airplanes,
certificated in any category, having serial
numbers 4001, 4003, 4004, and 4006 through
4081.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight Controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
There was one reported failure of the
elevator centering torsion spring.
Investigation revealed that the tangs on the
torsion spring had been bent due to difficulty
encountered during installation of the
elevator centering torsion spring on the
horizontal stabilizer torque tube. The
bending of the tangs on the torsion spring
would degrade its durability and could lead
to premature failure of the elevator centering
torsion spring. A control rod disconnect
between the elevator aft quadrant and the
elevator Power Control Unit input torque
tube, in combination with the loss or
reduction in elevator centering capability,
could result in a significant reduction in
aircraft pitch control.
Corrective actions include replacing all
elevator centering torsion springs with new
elevator centering torsion springs.
Actions and Compliance
(f) Prior to the accumulation of 22,000 total
flight hours, or within 5,000 flight hours after
the effective date of this AD, whichever
comes later, unless already done: Replace all
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23MYP1
Federal Register / Vol. 73, No. 101 / Friday, May 23, 2008 / Proposed Rules
elevator centering torsion springs with new
elevator centering torsion springs by
incorporating Modsum 4–113482, in
accordance with Bombardier Service Bulletin
84–27–31, dated April 27, 2007.
DEPARTMENT OF TRANSPORTATION
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
[Docket No. FAA–2008–0585; Directorate
Identifier 2008–NM–027–AD]
RIN 2120–AA64
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: Fabio
Buttitta, Aerospace Engineer, Systems and
Flight Test Branch, ANE–172, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516)
228–7303; 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–2008–05R1, dated February 27,
2008, and Bombardier Service Bulletin 84–
27–31, dated April 27, 2007, for related
information.
Issued in Renton, Washington, on May 8,
2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–11566 Filed 5–22–08; 8:45 am]
dwashington3 on PRODPC61 with PROPOSALS
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:17 May 22, 2008
Jkt 214001
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Boeing
Model 747SP Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
Boeing Model 747SP series airplanes.
This proposed AD would require
repetitive lubrication of the rudder tab
hinges and repetitive replacement of the
rudder tab control rods. This proposed
AD results from reports of freeplayinduced vibration of the control surfaces
on Boeing Model 727, 737, 757, and 767
airplanes. We are proposing this AD to
prevent damage to the control surface
structure during flight, which could
result in loss of control of the airplane.
DATES: We must receive comments on
this proposed AD by July 7, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
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Fmt 4702
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30007
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6426; fax (425) 917–6590.
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–2008–0585; Directorate Identifier
2008–NM–027–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of freeplayinduced vibration of control surfaces on
Boeing Model 727, 737, 757, and 767
airplanes. Excessive wear of
components or interfaces allows
excessive freeplay of the control
surfaces and can cause unacceptable
airframe vibration during flight. The
potential for vibration of the control
surface should be avoided because the
point of transition from vibration to
divergent flutter is unknown. Divergent
flutter can cause damage to the control
surface structure during flight. This
condition, if not corrected, could result
in loss of control of the airplane.
Although there have been no reports
of freeplay-induced vibration of the
rudder tabs for Model 747SP airplanes,
the affected control surfaces on Boeing
Model 727, 737, 757, and 767 airplanes
and Boeing Model 747SP airplanes are
similar in design. Therefore, all of these
models might be subject to the
identified unsafe condition.
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 747–27–
2447, dated January 17, 2008. The
service bulletin describes procedures for
repetitive lubrication of the rudder tab
E:\FR\FM\23MYP1.SGM
23MYP1
]]>Agencies
[Federal Register Volume 73, Number 101 (Friday, May 23, 2008)]
[Proposed Rules]
[Pages 30005-30007]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-11566]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0586; Directorate Identifier 2008-NM-043-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400, -401 and -
402 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:
There was one reported failure of the elevator centering torsion
spring. Investigation revealed that the tangs on the torsion spring
had been bent due to difficulty encountered during installation of
the elevator centering torsion spring on the horizontal stabilizer
torque tube. The bending of the tangs on the torsion spring would
degrade its durability and could lead to premature failure of the
elevator centering torsion spring. A control rod disconnect between
the elevator aft quadrant and the elevator Power Control Unit input
torque tube, in combination with the loss or reduction in elevator
centering capability, could result in a significant reduction in
aircraft pitch 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 June 23, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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: Fabio Buttitta, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7303; 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-2008-0586;
Directorate Identifier 2008-NM-043-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-
2008-05R1, dated February 27, 2008. (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
There was one reported failure of the elevator centering torsion
spring. Investigation revealed that the tangs on the
[[Page 30006]]
torsion spring had been bent due to difficulty encountered during
installation of the elevator centering torsion spring on the
horizontal stabilizer torque tube. The bending of the tangs on the
torsion spring would degrade its durability and could lead to
premature failure of the elevator centering torsion spring. A
control rod disconnect between the elevator aft quadrant and the
elevator Power Control Unit input torque tube, in combination with
the loss or reduction in elevator centering capability, could result
in a significant reduction in aircraft pitch control.
Corrective actions include replacing all elevator centering torsion
springs with new elevator centering torsion springs. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Bombardier has issued Service Bulletin 84-27-31, dated April 27,
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 42 products of U.S. registry. We also estimate that
it would take about 7 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 $1,746 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 $96,852, or $2,306 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, 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-
0586; Directorate Identifier 2008-NM-043-AD.
Comments Due Date
(a) We must receive comments by June 23, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, -401 and -402
airplanes, certificated in any category, having serial numbers 4001,
4003, 4004, and 4006 through 4081.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
Controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
There was one reported failure of the elevator centering torsion
spring. Investigation revealed that the tangs on the torsion spring
had been bent due to difficulty encountered during installation of
the elevator centering torsion spring on the horizontal stabilizer
torque tube. The bending of the tangs on the torsion spring would
degrade its durability and could lead to premature failure of the
elevator centering torsion spring. A control rod disconnect between
the elevator aft quadrant and the elevator Power Control Unit input
torque tube, in combination with the loss or reduction in elevator
centering capability, could result in a significant reduction in
aircraft pitch control.
Corrective actions include replacing all elevator centering
torsion springs with new elevator centering torsion springs.
Actions and Compliance
(f) Prior to the accumulation of 22,000 total flight hours, or
within 5,000 flight hours after the effective date of this AD,
whichever comes later, unless already done: Replace all
[[Page 30007]]
elevator centering torsion springs with new elevator centering
torsion springs by incorporating Modsum 4-113482, in accordance with
Bombardier Service Bulletin 84-27-31, dated April 27, 2007.
FAA AD Differences
Note: 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: Fabio Buttitta, Aerospace
Engineer, Systems and Flight Test Branch, ANE-172, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7303; 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-2008-05R1,
dated February 27, 2008, and Bombardier Service Bulletin 84-27-31,
dated April 27, 2007, for related information.
Issued in Renton, Washington, on May 8, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-11566 Filed 5-22-08; 8:45 am]
BILLING CODE 4910-13-P
