Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) Airplanes and Model CL-600-2D24 (Regional Jet Series 900) Airplanes, 8715-8717 [E9-3364]
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Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations
Note 1: Boeing Special Attention Service
Bulletin 737–53–1268, dated August 25,
2006, refers to Boeing Service Bulletin 737–
53A1177, Revision 6, dated May 31, 2001, as
an additional source of service information
for doing an internal eddy current inspection
of the lap joint for certain airplane
configurations.
Note 2: The eddy current inspections along
the stringer tie clip radius to detect damage
and replacement, as applicable, specified in
paragraph 3.B.5. of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1268, dated August
25, 2006, are not required by this AD. The
actions are optional and can be done in
addition to and at the same time as the
actions required by paragraph (f) of this AD.
Inspection B: Temporary Alternative
External Inspections and Corrective Actions
(g) As a temporary alternative to doing the
actions required by paragraph (f) of this AD,
do repetitive external general visual
inspections of the skin and lap joints and
repetitive external eddy current sliding probe
inspections, as applicable, of the lap joints
for cracks and evidence of overload resulting
from cracked stringer tie clips, and
applicable corrective actions if necessary. Do
all applicable actions at the applicable
compliance times and repeat intervals
identified in Tables 9 through 12 inclusive of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 737–53–
1268, dated August 25, 2006 (‘‘the service
bulletin’’), but not to exceed the flight cycles
in the ‘‘Inspection Period Allowed’’ column
of the tables; except as provided by
paragraphs (h) and (k) of this AD. Do all
applicable actions in accordance with the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (l)
of this AD.
Note 3: Inspection B may be used on
affected airplanes having line numbers 1
through 999 inclusive on which the
terminating action (i.e., replacement of
stringer tie clips) specified in Boeing Service
Bulletin 737–53–1085, Revision 1, dated May
10, 1990, has been done; and on affected
airplanes having line numbers 1000 and
subsequent. Boeing Special Attention Service
Bulletin 737–53–1268, dated August 25,
2006, contains a similar note.
Exceptions to Service Information
(h) Where Boeing Special Attention Service
Bulletin 737–53–1268, dated August 25, 2006
(‘‘the service bulletin’’), specifies a
compliance time after the date of the service
bulletin, this AD requires compliance within
the specified compliance time after the
effective date of this AD.
(i) For Model 737–100, –200, and –200C
series airplanes, on which Boeing Service
Bulletin 737–53–1085, Revision 1, dated May
10, 1990, has not been done in accordance
with AD 93–08–04: As of the effective date
of this AD, do the applicable inspections
from station (STA) 559 to STA 887 in
accordance with paragraph (f) of this AD, at
the applicable compliance times specified in
paragraph (b) of AD 93–08–04.
(j) In the first row of Tables 5 and 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
VerDate Nov<24>2008
14:57 Feb 25, 2009
Jkt 217001
Special Attention Service Bulletin 737–53–
1268, dated August 25, 2006 (‘‘the service
bulletin’’), where the service bulletin
specifies a compliance time of before 25,000
total airplane flight cycles, this AD requires
a compliance time of before the accumulation
of 25,000 total flight cycles, or within 2 years
after the effective date of this AD, whichever
occurs later.
(k) Where Boeing Special Attention Service
Bulletin 737–53–1268, dated August 25,
2006, specifies no starting point (e.g., ‘‘after
the date on the service bulletin’’) for a grace
period, this AD requires compliance within
the specified grace period after the effective
date of this AD.
(l) Where Boeing Special Attention Service
Bulletin 737–53–1268, dated August 25,
2006, specifies to contact Boeing for
appropriate action: Before further flight,
repair the discrepancy using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
Certain Actions End Certain Requirements of
AD 93–08–04
(m) Accomplishment of the internal eddy
current and detailed inspections for STA 559
to STA 887 in accordance with paragraph (f)
of this AD constitutes compliance with the
inspections required by paragraph (a) of AD
93–08–04, as it pertains to Boeing Service
Bulletin 737–53–1085, Revision 1, dated May
10, 1990. Accomplishment of the internal
eddy current and detailed inspections does
not terminate the remaining requirements of
AD 93–08–04, as it applies to other service
bulletins. Operators are required to continue
to inspect and/or modify per the other
service bulletins listed in that AD.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6447; 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.
Material Incorporated by Reference
(o) You must use Boeing Special Attention
Service Bulletin 737–53–1268, dated August
25, 2006, to perform the actions that are
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8715
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
(1) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(2) You may review copies of the service
information that is incorporated by reference
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.
(3) You may also review copies of the
service information 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 January
30, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–3621 Filed 2–25–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1115; Directorate
Identifier 2008–NM–134–AD; Amendment
39–15801; AD 2009–02–11]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702) Airplanes and
Model CL–600–2D24 (Regional Jet
Series 900) 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:
Bombardier Aerospace has completed a
system safety review of the CL–600–2C10/
CL–600–2D24 aircraft fuel system against the
new fuel tank safety standards. * * *
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8716
Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations
The assessment showed that a single
failure due to chafing of fuel system wiring
with high power wiring at the centre fuel
tank front spar could result in overheating of
the fuel boost pump. The assessment also
showed that chafing of the high power wiring
with the centre fuel tank front spar structures
could result in overheating of the fuel tank
wall. Overheating of * * * the fuel tank wall
could lead to hot surface ignition resulting in
a fuel tank explosion.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
2, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 2, 2009.
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:
Rocco Viselli, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7331; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
To correct the unsafe condition, this
directive mandates separation of the high
power wiring from the fuel system wiring at
the centre fuel tank front spar area and the
installation of additional clamping and
support for the high power wiring [i.e.,
modifying the routing and support of
electrical wires in the center fuel tank front
spar area].
Required actions also include an
inspection to determine if pins have a
minimum of one thread above the nuts,
and a visual inspection for damage of
the sealant. Corrective actions include
replacing pins and nuts and applying
sealant. 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.
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 October 23, 2008 (73 FR
63094). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
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.
Bombardier Aerospace has completed a
system safety review of the CL–600–2C10/
CL–600–2D24 aircraft fuel system against the
new fuel tank safety standards, introduced in
Chapter 525 of the Airworthiness Manual
through Notice of Proposed Amendment
(NPA) 2002–043. The identified noncompliances were assessed using Transport
Canada Policy Letter No. 525–001 to
determine if mandatory corrective action was
required.
The assessment showed that a single
failure due to chafing of fuel system wiring
with high power wiring at the centre fuel
tank front spar could result in overheating of
the fuel boost pump. The assessment also
showed that chafing of the high power wiring
with the centre fuel tank front spar structures
could result in overheating of the fuel tank
wall. Overheating of the fuel boost pump or
the fuel tank wall could lead to hot surface
ignition resulting in a fuel tank explosion.
Costs of Compliance
We estimate that this AD will affect
about 159 products of U.S. registry. We
also estimate that it will take about 102
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 $7,646
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
$2,513,154, or $15,806 per product.
Discussion
VerDate Nov<24>2008
14:57 Feb 25, 2009
Jkt 217001
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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.
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Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations
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:
■
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:
■
2009–02–11 Bombardier Inc. (Formerly
Canadair): Amendment 39–15801.
Docket No. FAA–2008–1115; Directorate
Identifier 2008–NM–134–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 2, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) Bombardier Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, serial numbers 10003 through
10169 inclusive.
(2) Bombardier Model CL–600–2D24
(Regional Jet Series 900) airplanes, serial
numbers 15001 through 15030 inclusive.
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Bombardier Aerospace has completed a
system safety review of the CL–600–2C10/
CL–600–2D24 aircraft fuel system against the
new fuel tank safety standards, introduced in
Chapter 525 of the Airworthiness Manual
through Notice of Proposed Amendment
(NPA) 2002–043. The identified noncompliances were assessed using Transport
Canada Policy Letter No. 525–001 to
determine if mandatory corrective action was
required.
The assessment showed that a single
failure due to chafing of fuel system wiring
with high power wiring at the centre fuel
tank front spar could result in overheating of
the fuel boost pump. The assessment also
showed that chafing of the high power wiring
with the centre fuel tank front spar structures
could result in overheating of the fuel tank
wall. Overheating of the fuel boost pump or
the fuel tank wall could lead to hot surface
ignition resulting in a fuel tank explosion.
14:57 Feb 25, 2009
Jkt 217001
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 4,500 flight hours after the
effective date of this AD, modify the routing
and support of the electrical wires in the
center fuel tank front spar area (including an
inspection to determine if pins have a
minimum of one thread above the nuts, and
a visual inspection for damage of the sealant,
and applicable corrective actions) in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
670BA–24–012, Revision B, dated July 25,
2007. Do all applicable related investigative
and corrective actions before further flight.
(2) Actions done before the effective date
of this AD in accordance with Bombardier
Service Bulletin 670BA–24–012, dated April
18, 2005; or Revision A, dated October 25,
2006; are acceptable for compliance with the
corresponding requirements of this AD.
FAA AD Differences
Subject
(d) Air Transport Association (ATA) of
America Code 24: Electrical Power.
VerDate Nov<24>2008
To correct the unsafe condition, this
directive mandates separation of the high
power wiring from the fuel system wiring at
the centre fuel tank front spar area and the
installation of additional clamping and
support for the high power wiring [i.e.,
modifying the routing and support of
electrical wires in the center fuel tank front
spar area].
Required actions also include an inspection
to determine if pins have a minimum of one
thread above the nuts, and a visual
inspection for damage of the sealant.
Corrective actions include replacing pins and
nuts and applying sealant.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Airframe and
Propulsion Branch, ANE–171, New York
Aircraft Certification Office, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Rocco
Viselli, Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228–7331; 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 FAAapproved 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
PO 00000
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Fmt 4700
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8717
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–2008–24, dated July 3, 2008,
and Bombardier Service Bulletin 670BA–24–
012, Revision B, dated July 25, 2007, for
related information.
Material Incorporated by Reference
(i) You must use Bombardier Service
Bulletin 670BA–24–012, Revision B, dated
July 25, 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
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.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information that is incorporated by reference
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 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 January
15, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–3364 Filed 2–25–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0150; Directorate
Identifier 2007–NM–325–AD; Amendment
39–15818; AD 2009–04–12]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200, –300, and –400ER
Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
E:\FR\FM\26FER1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 37 (Thursday, February 26, 2009)]
[Rules and Regulations]
[Pages 8715-8717]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3364]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1115; Directorate Identifier 2008-NM-134-AD;
Amendment 39-15801; AD 2009-02-11]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional
Jet Series 700, 701 & 702) Airplanes and Model CL-600-2D24 (Regional
Jet Series 900) 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:
Bombardier Aerospace has completed a system safety review of the
CL-600-2C10/CL-600-2D24 aircraft fuel system against the new fuel
tank safety standards. * * *
[[Page 8716]]
The assessment showed that a single failure due to chafing of
fuel system wiring with high power wiring at the centre fuel tank
front spar could result in overheating of the fuel boost pump. The
assessment also showed that chafing of the high power wiring with
the centre fuel tank front spar structures could result in
overheating of the fuel tank wall. Overheating of * * * the fuel
tank wall could lead to hot surface ignition resulting in a fuel
tank explosion.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 2, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 2,
2009.
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: Rocco Viselli, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7331; 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 October 23, 2008 (73
FR 63094). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Bombardier Aerospace has completed a system safety review of the
CL-600-2C10/CL-600-2D24 aircraft fuel system against the new fuel
tank safety standards, introduced in Chapter 525 of the
Airworthiness Manual through Notice of Proposed Amendment (NPA)
2002-043. The identified non-compliances were assessed using
Transport Canada Policy Letter No. 525-001 to determine if mandatory
corrective action was required.
The assessment showed that a single failure due to chafing of
fuel system wiring with high power wiring at the centre fuel tank
front spar could result in overheating of the fuel boost pump. The
assessment also showed that chafing of the high power wiring with
the centre fuel tank front spar structures could result in
overheating of the fuel tank wall. Overheating of the fuel boost
pump or the fuel tank wall could lead to hot surface ignition
resulting in a fuel tank explosion.
To correct the unsafe condition, this directive mandates
separation of the high power wiring from the fuel system wiring at
the centre fuel tank front spar area and the installation of
additional clamping and support for the high power wiring [i.e.,
modifying the routing and support of electrical wires in the center
fuel tank front spar area].
Required actions also include an inspection to determine if pins have a
minimum of one thread above the nuts, and a visual inspection for
damage of the sealant. Corrective actions include replacing pins and
nuts and applying sealant. 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
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 159 products of U.S.
registry. We also estimate that it will take about 102 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 $7,646
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 $2,513,154, or $15,806 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.
[[Page 8717]]
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:
2009-02-11 Bombardier Inc. (Formerly Canadair): Amendment 39-15801.
Docket No. FAA-2008-1115; Directorate Identifier 2008-NM-134-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April 2,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category.
(1) Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701,
& 702) airplanes, serial numbers 10003 through 10169 inclusive.
(2) Bombardier Model CL-600-2D24 (Regional Jet Series 900)
airplanes, serial numbers 15001 through 15030 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical Power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Bombardier Aerospace has completed a system safety review of the
CL-600-2C10/CL-600-2D24 aircraft fuel system against the new fuel
tank safety standards, introduced in Chapter 525 of the
Airworthiness Manual through Notice of Proposed Amendment (NPA)
2002-043. The identified non-compliances were assessed using
Transport Canada Policy Letter No. 525-001 to determine if mandatory
corrective action was required.
The assessment showed that a single failure due to chafing of
fuel system wiring with high power wiring at the centre fuel tank
front spar could result in overheating of the fuel boost pump. The
assessment also showed that chafing of the high power wiring with
the centre fuel tank front spar structures could result in
overheating of the fuel tank wall. Overheating of the fuel boost
pump or the fuel tank wall could lead to hot surface ignition
resulting in a fuel tank explosion.
To correct the unsafe condition, this directive mandates
separation of the high power wiring from the fuel system wiring at
the centre fuel tank front spar area and the installation of
additional clamping and support for the high power wiring [i.e.,
modifying the routing and support of electrical wires in the center
fuel tank front spar area].
Required actions also include an inspection to determine if pins
have a minimum of one thread above the nuts, and a visual inspection
for damage of the sealant. Corrective actions include replacing pins
and nuts and applying sealant.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 4,500 flight hours after the effective date of this
AD, modify the routing and support of the electrical wires in the
center fuel tank front spar area (including an inspection to
determine if pins have a minimum of one thread above the nuts, and a
visual inspection for damage of the sealant, and applicable
corrective actions) in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-24-012, Revision
B, dated July 25, 2007. Do all applicable related investigative and
corrective actions before further flight.
(2) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 670BA-24-012, dated
April 18, 2005; or Revision A, dated October 25, 2006; are
acceptable for compliance with the corresponding requirements of
this AD.
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,
Airframe and Propulsion Branch, ANE-171, New York Aircraft
Certification Office, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Send information to ATTN: Rocco Viselli, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7331; 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-2008-24,
dated July 3, 2008, and Bombardier Service Bulletin 670BA-24-012,
Revision B, dated July 25, 2007, for related information.
Material Incorporated by Reference
(i) You must use Bombardier Service Bulletin 670BA-24-012,
Revision B, dated July 25, 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., 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.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service information that is
incorporated by reference 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 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 January 15, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-3364 Filed 2-25-09; 8:45 am]
BILLING CODE 4910-13-P
