Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 35902-35904 [E8-13921]
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35902
Federal Register / Vol. 73, No. 123 / Wednesday, June 25, 2008 / Rules and Regulations
(4) For engines with 2,500 or less hours of
operating time, before it accumulates 4,000
hours of operating time, but not later than
September 30, 2008, inspect LP compressor
fan blades and replace any blade that is
found to be under-minimum material
condition.
Issued in Burlington, Massachusetts, on
June 13, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–13854 Filed 6–24–08; 8:45 am]
BILLING CODE 4910–13–P
Previous Credit
(f) Inspection of the fan blades for an
under-minimum material condition done
before the effective date of this AD that used
P&WC ASB PW300–72–A24588, dated
August 24, 2007; or Revision 1, dated
October 26, 2007; or P&WC SB PW300–72–
24595, dated October 26, 2007; or Revision
1, dated November 28, 2007, comply with the
requirements specified in this AD.
DEPARTMENT OF TRANSPORTATION
Other FAA AD Provisions
RIN 2120–AA64
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) Special Flight Permits: We are limiting
Special Flight Permits to one repositioning
maintenance flight to facilitate the subject
inspection.
Related Information
(h) Refer to Transport Canada
Airworthiness Directive CF–2008–08R1,
dated March 18, 2008; P&WC ASB PW300–
72–A24588, Revision 2, dated November 27,
2007; and P&WC SB PW300–72–24595,
Revision 1, dated November 28, 2007, for
related information.
(i) Contact Ian Dargin, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; email: ian.dargin@faa.gov; telephone (781)
238–7178; fax (781) 238–7199, for more
information about this AD.
jlentini on PROD1PC65 with RULES
Material Incorporated by Reference
(j) You must use Pratt & Whitney Canada
Corp. Alert Service Bulletin PW300–72–
A24588, Revision 2, dated November 27,
2007, 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 Pratt & Whitney Canada
Corp., 1000 Marie-Victorin, Longueuil,
Quebec, Canada J4G 1A1, telephone: (800)
268–8000.
(3) You may review copies at the FAA,
New England Region, 12 New England
Executive Park, Burlington, MA; or 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/cfr/ibrlocations.html.
VerDate Aug<31>2005
18:16 Jun 24, 2008
Jkt 214001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0360; Directorate
Identifier 2007–NM–368–AD; Amendment
39–15570; AD 2008–13–07]
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:
Several production aircraft have been
found with the elevator overload bungees
installed in reverse orientation: i.e., larger
end outboard rather than inboard. This
bungee reversal does not impact normal
operation of the elevator, and would not
increase the probability of an elevator
disconnect. However, if a bungee became
disconnected at the inboard side, the
corresponding side of the elevator may not
center, and this could adversely affect the
pitch control of the aircraft.
Loss of elevator pitch control could
result in reduced controllability of the
airplane. We are issuing this AD to
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July
30, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 30, 2008.
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.
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
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:
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 March 28, 2008 (73 FR
16577). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Several production aircraft have been
found with the elevator overload
bungees installed in reverse orientation:
i.e., larger end outboard rather than
inboard. This bungee reversal does not
impact normal operation of the elevator,
and would not increase the probability
of an elevator disconnect. However, if a
bungee became disconnected at the
inboard side, the corresponding side of
the elevator may not center, and this
could adversely affect the pitch control
of the aircraft.
Loss of elevator pitch control could
result in reduced controllability of the
airplane. Corrective action includes a
visual inspection for correct installation
of the elevator overload bungees,
reinstallation if necessary, and
installation of labels to the elevator
overload bungees. 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.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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
E:\FR\FM\25JNR1.SGM
25JNR1
Federal Register / Vol. 73, No. 123 / Wednesday, June 25, 2008 / Rules and Regulations
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
38 products of U.S. registry. We also
estimate that it will take 1 work-hour
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 $36 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
figures, we estimate the cost of this AD
to the U.S. operators to be $4,408, or
$116 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 PROD1PC65 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;
VerDate Aug<31>2005
18:16 Jun 24, 2008
Jkt 214001
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–13–07 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–15570.
Docket No. FAA–2008–0360; Directorate
Identifier 2007–NM–368–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 30, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400, DHC–8–401, and DHC–8–402
airplanes; certificated in any category; having
serial numbers 4003 and subsequent.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
35903
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Several production aircraft have been found
with the elevator overload bungees installed
in reverse orientation: i.e., larger end
outboard rather than inboard. This bungee
reversal does not impact normal operation of
the elevator, and would not increase the
probability of an elevator disconnect.
However, if a bungee became disconnected at
the inboard side, the corresponding side of
the elevator may not center, and this could
adversely affect the pitch control of the
aircraft.
Loss of elevator pitch control could result in
reduced controllability of the airplane.
Corrective action includes a visual inspection
for correct installation of the elevator
overload bungees, reinstallation if necessary,
and installation of labels to the elevator
overload bungees.
Actions and Compliance
(f) For airplanes having serial numbers
4003, 4004, 4006, and 4008 through 4159:
unless already done, do the following
actions.
(1) Within 5,000 flight hours after the
effective date of this AD: Visually inspect
both left and right elevator overload bungees,
part number (P/N) FE289000000, to
determine if they are correctly installed, in
accordance with Bombardier Service Bulletin
84–27–30, Revision ‘C,’ dated October 31,
2007. If any bungee is found installed
incorrectly, remove the bungee and re-install
it correctly before the next flight in
accordance with the service bulletin.
(2) Within 5,000 flight hours after the
effective date of this AD: Attach label, P/N
FE289006200, to both left and right elevator
overload bungees to show the correct
orientation of the outboard end in accordance
with Bombardier Service Bulletin 84–27–30,
Revision ‘C,’ dated October 31, 2007.
(3) Within 5,000 flight hours after the
effective date of this AD: Re-identify the P/
N to read ‘‘FE289000001’’ on the
identification plate of both the left and right
elevator overload bungees in accordance with
Bombardier Service Bulletin 84–27–30,
Revision ‘C,’ dated October 31, 2007.
(4) Actions accomplished before the
effective date of this AD in accordance with
Bombardier Service Bulletin 84–27–27, dated
May 24, 2005, are acceptable for compliance
with the corresponding actions specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(5) Actions accomplished before the
effective date of this AD in accordance with
Bombardier Service Bulletin 84–27–30, dated
February 8, 2007; Revision ‘A,’ dated March
2, 2007; or Revision ‘B,’ dated May 3, 2007;
are acceptable for compliance with the
corresponding actions specified in this AD.
Note 1: Paragraphs (f)(2) and (f)(3) of this
AD constitute Modsum 4–113537.
(g) For all airplanes: As of the effective
date of this AD, no replacement/spare
elevator overload bungees, P/N
FE289000000, are permitted to be installed
on any airplane. Only elevator overload
bungees identified with new P/N
E:\FR\FM\25JNR1.SGM
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35904
Federal Register / Vol. 73, No. 123 / Wednesday, June 25, 2008 / Rules and Regulations
‘‘FE289000001’’ on the identification plate
are permitted to be installed.
Issued in Renton, Washington, on June 7,
2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–13921 Filed 6–24–08; 8:45 am]
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
BILLING CODE 4910–13–P
Other FAA AD Provisions
(h) 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
(i) Refer to MCAI Canadian Airworthiness
Directive CF–2007–30, dated November 28,
2007; and Bombardier Service Bulletin 84–
27–30, Revision ‘C,’ dated October 31, 2007;
for related information.
jlentini on PROD1PC65 with RULES
Material Incorporated by Reference
(j) You must use Bombardier Service
Bulletin 84–27–30, Revision ‘C,’ dated
October 31, 2007, 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.,
Bombardier Regional Aircraft Division, 123
Garratt Boulevard, Downsview, Ontario M3K
1Y5, Canada.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html.
VerDate Aug<31>2005
18:16 Jun 24, 2008
Jkt 214001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0182; Directorate
Identifier 2007–NM–262–AD; Amendment
39–15577; AD 2008–13–14]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135ER,
–135KE, –135KL, and –135LR
Airplanes, and Model EMB–145,
–145ER, –145MR, –145LR, –145XR,
–145MP, and –145EP 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:
Fuel system reassessment, performed
according to RBHA–E88/SFAR–88
(Regulamento Brasileiro de Homologacao
Aeronautica 88/Special Federal Aviation
Regulation No. 88), requires the inclusion of
new maintenance tasks in the Critical Design
Configuration Control Limitations (CDCCL)
and in the Fuel System Limitations (FSL),
necessary to preclude ignition sources in the
fuel system. * * *
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
30, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 30, 2008.
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.
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1405; 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
May 7, 2008 (73 FR 25609). That
supplemental NPRM proposed to
correct an unsafe condition for the
specified products. The MCAI states:
Fuel system reassessment, performed
according to RBHA–E88/SFAR–88, requires
the inclusion of new maintenance tasks in
the Critical Design Configuration Control
Limitations (CDCCL) and in the Fuel System
Limitations (FSL), necessary to preclude
ignition sources in the fuel system. * * *
The corrective action is revising the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness (ICA) to incorporate new
limitations for fuel tank systems. 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 comments received.
Request To Revise Inspections
ExpressJet requests that we revise two
tasks, ‘‘28–41–01–720–001–A00 and 28–
41–01–720–A00,’’ specified in Table 1
of the supplemental NPRM. The
commenter states that these tasks are
related to a functional check of the
component rather than the aircraft
system. The commenter suggests that we
identify these two components by part
number and require the inspections be
done before the part accumulates 10,000
flight hours since new or 10,000 flight
hours since the last functional check.
We agree with the commenter that
tasks 28–41–01–720–001–A00 and 28–
41–04–720–001–A00 are related to a
functional check of the component
rather than the aircraft system (the
commenter referred to task 28–41–01–
720–A00, which is not listed in Table 1;
we infer that the commenter intended to
refer to task 28–41–04–720–001–A00).
Prior to the commenter submitting its
comment, the commenter raised the
issue during a visit by the FAA. Since
then we have discussed the issue with
ˆ
the manufacturer and with the Agencia
Nacional de Aviacao Civil (ANAC),
¸˜
E:\FR\FM\25JNR1.SGM
25JNR1
]]>Agencies
[Federal Register Volume 73, Number 123 (Wednesday, June 25, 2008)]
[Rules and Regulations]
[Pages 35902-35904]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-13921]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0360; Directorate Identifier 2007-NM-368-AD;
Amendment 39-15570; AD 2008-13-07]
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 production aircraft have been found with the elevator
overload bungees installed in reverse orientation: i.e., larger end
outboard rather than inboard. This bungee reversal does not impact
normal operation of the elevator, and would not increase the
probability of an elevator disconnect. However, if a bungee became
disconnected at the inboard side, the corresponding side of the
elevator may not center, and this could adversely affect the pitch
control of the aircraft.
Loss of elevator pitch control could result in reduced controllability
of the airplane. We are issuing this AD to require actions to correct
the unsafe condition on these products.
DATES: This AD becomes effective July 30, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 30,
2008.
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: 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:
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 March 28, 2008 (73
FR 16577). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Several production aircraft have been found with the elevator
overload bungees installed in reverse orientation: i.e., larger end
outboard rather than inboard. This bungee reversal does not impact
normal operation of the elevator, and would not increase the
probability of an elevator disconnect. However, if a bungee became
disconnected at the inboard side, the corresponding side of the
elevator may not center, and this could adversely affect the pitch
control of the aircraft.
Loss of elevator pitch control could result in reduced controllability
of the airplane. Corrective action includes a visual inspection for
correct installation of the elevator overload bungees, reinstallation
if necessary, and installation of labels to the elevator overload
bungees. 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.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
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
[[Page 35903]]
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 38 products of U.S. registry.
We also estimate that it will take 1 work-hour 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 $36 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
figures, we estimate the cost of this AD to the U.S. operators to be
$4,408, or $116 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:
2008-13-07 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-15570. Docket No. FAA-2008-0360; Directorate Identifier 2007-NM-
368-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 30,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401,
and DHC-8-402 airplanes; certificated in any category; having serial
numbers 4003 and subsequent.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Several production aircraft have been found with the elevator
overload bungees installed in reverse orientation: i.e., larger end
outboard rather than inboard. This bungee reversal does not impact
normal operation of the elevator, and would not increase the
probability of an elevator disconnect. However, if a bungee became
disconnected at the inboard side, the corresponding side of the
elevator may not center, and this could adversely affect the pitch
control of the aircraft.
Loss of elevator pitch control could result in reduced
controllability of the airplane. Corrective action includes a visual
inspection for correct installation of the elevator overload
bungees, reinstallation if necessary, and installation of labels to
the elevator overload bungees.
Actions and Compliance
(f) For airplanes having serial numbers 4003, 4004, 4006, and
4008 through 4159: unless already done, do the following actions.
(1) Within 5,000 flight hours after the effective date of this
AD: Visually inspect both left and right elevator overload bungees,
part number (P/N) FE289000000, to determine if they are correctly
installed, in accordance with Bombardier Service Bulletin 84-27-30,
Revision `C,' dated October 31, 2007. If any bungee is found
installed incorrectly, remove the bungee and re-install it correctly
before the next flight in accordance with the service bulletin.
(2) Within 5,000 flight hours after the effective date of this
AD: Attach label, P/N FE289006200, to both left and right elevator
overload bungees to show the correct orientation of the outboard end
in accordance with Bombardier Service Bulletin 84-27-30, Revision
`C,' dated October 31, 2007.
(3) Within 5,000 flight hours after the effective date of this
AD: Re-identify the P/N to read ``FE289000001'' on the
identification plate of both the left and right elevator overload
bungees in accordance with Bombardier Service Bulletin 84-27-30,
Revision `C,' dated October 31, 2007.
(4) Actions accomplished before the effective date of this AD in
accordance with Bombardier Service Bulletin 84-27-27, dated May 24,
2005, are acceptable for compliance with the corresponding actions
specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(5) Actions accomplished before the effective date of this AD in
accordance with Bombardier Service Bulletin 84-27-30, dated February
8, 2007; Revision `A,' dated March 2, 2007; or Revision `B,' dated
May 3, 2007; are acceptable for compliance with the corresponding
actions specified in this AD.
Note 1: Paragraphs (f)(2) and (f)(3) of this AD constitute
Modsum 4-113537.
(g) For all airplanes: As of the effective date of this AD, no
replacement/spare elevator overload bungees, P/N FE289000000, are
permitted to be installed on any airplane. Only elevator overload
bungees identified with new P/N
[[Page 35904]]
``FE289000001'' on the identification plate are permitted to be
installed.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(h) 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
(i) Refer to MCAI Canadian Airworthiness Directive CF-2007-30,
dated November 28, 2007; and Bombardier Service Bulletin 84-27-30,
Revision `C,' dated October 31, 2007; for related information.
Material Incorporated by Reference
(j) You must use Bombardier Service Bulletin 84-27-30, Revision
`C,' dated October 31, 2007, 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., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-
locations.html.
Issued in Renton, Washington, on June 7, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-13921 Filed 6-24-08; 8:45 am]
BILLING CODE 4910-13-P
