Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 63574-63576 [E9-28798]
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63574
Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
TABLE 1—MATERIAL INCORPORATED BY REFERENCE
Service bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Revision
40–25–11 .....................................................................................................
45–25–21. ....................................................................................................
40–52–07. ....................................................................................................
45–52–16. ....................................................................................................
Issued in Renton, Washington, on
November 19, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–28550 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
ADDRESSES:
[Docket No. FAA–2009–0784; Directorate
Identifier 2009–NM–109–AD; Amendment
39–16124; AD 2009–25–05]
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.
RIN 2120–AA64
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
jlentini on DSKJ8SOYB1PROD with RULES
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.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 8, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 8, 2010.
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 4, 2009 (74 FR
45783). That NPRM proposed 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
incorporating a modification to add a
filter/restrictor fitting to the spoiler lift
dump valve, which includes upgrading,
testing, and re-identifying the valve after
replacing the pressure port inlet fitting.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
PO 00000
Frm 00044
Fmt 4700
Sfmt 4700
Date
1
1
1
1
January 19, 2009.
January 19, 2009.
July 21, 2008.
July 21, 2008.
Change to Corrective Action Statement
We have added information to the
corrective action statement in the
preamble and paragraph (e) of the AD
for clarity.
Change to Alternative Methods of
Compliance (AMOC) Paragraph
We have updated paragraph (g)(1) of
this AD to provide the appropriate
contact information to use when
submitting requests for approval of an
AMOC.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We also determined that these changes
will not increase the economic burden
on any operator or increase the scope of
the AD.
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 required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 61 products of U.S. registry. We
also estimate that it will take about 6
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will 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 parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
E:\FR\FM\04DER1.SGM
04DER1
Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
figures, we estimate the cost of this AD
to the U.S. operators to be $29,280, or
$480 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.
jlentini on DSKJ8SOYB1PROD with RULES
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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 the NPRM, 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.
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
63575
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Bombardier Service Bulletin 84–27–43, dated
January 29, 2009.
FAA AD Differences
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–25–05 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–16124.
Docket No. FAA–2009–0784; Directorate
Identifier 2009–NM–109–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 8, 2010.
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 27: Flight controls.
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 incorporating a
modification to add a filter/restrictor fitting
to the spoiler lift dump valve, which
includes upgrading, testing, and reidentifying the valve 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
PO 00000
Frm 00045
Fmt 4700
Sfmt 4700
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), ANE–170, 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:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7300; 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
(44 U.S.C. et seq.), the Office of Management
and Budget (OMB) has approved the
information collection requirements and has
assigned OMB Control Number 2120–0056.
Related Information
(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.
Material Incorporated by Reference
(i) You must use Bombardier Service
Bulletin 84–27–43, dated January 29, 2009, to
do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
E:\FR\FM\04DER1.SGM
04DER1
63576
Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 23, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–28798 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0055; Directorate
Identifier 2008–NM–194–AD; Amendment
39–16125; AD 2009–25–06]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2–1C, A300 B2–203, A300 B2K–
3C, A300 B4–103, A300 B4–203, and
A300 B4–2C Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
jlentini on DSKJ8SOYB1PROD with RULES
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
* * * [T]he FAA has published SFAR 88
(Special Federal Aviation Regulation 88).
* * * Under this regulation, all holders of
type certificates for passenger transport
aeroplane * * * are required to conduct a
design review against explosion risks.
One of the consequences of the Airbus
design review is the modification of the fuel
pump wiring to provide protection against
chafing of the fuel pump cables. This
condition, if not corrected, could generate
short circuits leading to fuel pump failure
and arcing. These could become a potential
ignition source inside the fuel tank which, in
combination with flammable fuel vapours (if
present), could result in a fuel tank explosion
and consequent loss of the aeroplane.
To address this unsafe condition, EASA
[European Aviation Safety Agency] issued
AD 2007–0066 that required this
modification [of the fuel pump against short
circuit] in accordance with Airbus Service
Bulletin (SB) A300–24–0103 Revision 01.
Airbus subsequently introduced an
additional modification of the electrical
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
wiring of the outer fuel pump and the
landing lights of the left (LH) and the right
(RH) side in Revision 02 of the SB A300–24–
0103, leading to the issuance of EASA AD
2008–0188 which superseded EASA AD
2007–0066 and required the additional work.
More recently, Airbus introduced some
additional protection to routes 1P and 2P
harnesses in zone 571 and 671 of the
aeroplane.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 8, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 8, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (NPRM) to amend
14 CFR part 39 to include an AD that
would apply to the specified products.
That supplemental NPRM was
published in the Federal Register on
July 6, 2009 (74 FR 31896), and
proposed to supersede AD 2007–18–02,
Amendment 39–15182 (72 FR 49175,
August 28, 2007). That supplemental
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states:
Further to the accident of a Boeing 747–
131 (flight TWA800), the FAA has published
SFAR 88 (Special Federal Aviation
Regulation 88). Subsequently, the Joint
Aviation Authorities (JAA) recommended the
application of a similar regulation to the
National Aviation Authorities (NAA) of its
member countries. Under this regulation, all
holders of type certificates for passenger
transport aeroplane with either a passenger
capacity of 30 or more, or a payload capacity
of 3,402 kg (7,500 lbs) or more which have
received their certification after 01 January
1958, are required to conduct a design review
against explosion risks.
One of the consequences of the Airbus
design review is the modification of the fuel
pump wiring to provide protection against
chafing of the fuel pump cables. This
PO 00000
Frm 00046
Fmt 4700
Sfmt 4700
condition, if not corrected, could generate
short circuits leading to fuel pump failure
and arcing. These could become a potential
ignition source inside the fuel tank which, in
combination with flammable fuel vapours (if
present), could result in a fuel tank explosion
and consequent loss of the aeroplane.
To address this unsafe condition, EASA
[European Aviation Safety Agency] issued
AD 2007–0066 that required this
modification in accordance with Airbus
Service Bulletin (SB) A300–24–0103
Revision 01. Airbus subsequently introduced
an additional modification of the electrical
wiring of the outer fuel pump and the
landing lights of the left (LH) and the right
(RH) side in Revision 02 of the SB A300–24–
0103, leading to the issuance of EASA AD
2008–0188 which superseded EASA AD
2007–0066 and required the additional work.
More recently, Airbus introduced some
additional protection to routes 1P and 2P
harnesses in zone 571 and 671 of the
aeroplane.
For the reason described above, this new
AD retains the requirements of EASA AD
2008–0188, which is superseded, and
requires the additional work as specified in
Revision 03 of Airbus SB A300–24–0103.
The additional modification will
provide additional protection from
chafing and will prevent intermittent
operation of the fuel pump and landing
lights, as well as failure of the power
supply. The modification of the wiring
of the outer fuel pump and the landing
light on the LH side route 1P harness
and RH side route 2P harness includes
additional mechanical protection that
includes procedures for installing new
splicing on the wires, a new cable type,
shrink sleeve installation on the new
wiring, and an additional braided
conduit sleeve (Halar), as applicable, for
the fuel pumps and the landing lights.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Refer to Updated MCAI
Airbus requests that we refer to the
latest EASA AD 2009–0157, dated July
17, 2009 (which was issued after the
FAA supplemental NPRM was
published), to require the additional
work provided in Airbus Mandatory
Service Bulletin A300–24–0103,
Revision 03, dated February 18, 2009.
The supplemental NPRM referred to
Airbus Mandatory Service Bulletin
A300–24–0103, Revision 03, dated
February 18, 2009, as the appropriate
source of service information for the
required actions. Airbus further requests
that we review the supplemental NPRM
in light of the new EASA AD to qualify
current requirements depending on the
E:\FR\FM\04DER1.SGM
04DER1
Agencies
[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63574-63576]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28798]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0784; Directorate Identifier 2009-NM-109-AD;
Amendment 39-16124; AD 2009-25-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
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.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 8, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 8,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 4, 2009
(74 FR 45783). That NPRM proposed 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 incorporating a modification to add a
filter/restrictor fitting to the spoiler lift dump valve, which
includes upgrading, testing, and re-identifying the valve after
replacing the pressure port inlet fitting. You may obtain further
information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Change to Corrective Action Statement
We have added information to the corrective action statement in the
preamble and paragraph (e) of the AD for clarity.
Change to Alternative Methods of Compliance (AMOC) Paragraph
We have updated paragraph (g)(1) of this AD to provide the
appropriate contact information to use when submitting requests for
approval of an AMOC.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 61 products of U.S.
registry. We also estimate that it will take about 6 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will 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 parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these
[[Page 63575]]
figures, we estimate the cost of this AD to the U.S. operators to be
$29,280, or $480 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2009-25-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-16124. Docket No. FAA-2009-0784; Directorate Identifier 2009-NM-
109-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
8, 2010.
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 27: Flight
controls.
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 incorporating a modification to add a
filter/restrictor fitting to the spoiler lift dump valve, which
includes upgrading, testing, and re-identifying the valve 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), ANE-170, 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: Program
Manager, Continuing Operational Safety, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516)
228-7300; 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 (44
U.S.C. et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(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.
Material Incorporated by Reference
(i) You must use Bombardier Service Bulletin 84-27-43, dated
January 29, 2009, to do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
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.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by
[[Page 63576]]
reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 23, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-28798 Filed 12-3-09; 8:45 am]
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