Airworthiness Directives; Bombardier Model BD-100-1A10 Airplanes, 13053-13055 [E6-3567]
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Federal Register / Vol. 71, No. 49 / Tuesday, March 14, 2006 / Proposed Rules
would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I
certify that this proposed regulation (1)
is not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under the DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979); and (3) if
promulgated, 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. A copy of the draft
regulatory evaluation prepared for this
action is contained in the Rules Docket.
A copy of it may be obtained by
contacting the Rules Docket at the
location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(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. Section 39.13 is amended by
adding the following new airworthiness
directive:
McDonnell Douglas: Docket 2001–NM–387–
AD.
wwhite on PROD1PC65 with PROPOSAL
Applicability
Model DC–9–81 (MD–81), DC–9–82 (MD–
82), DC–9–83 (MD–83), DC–9–87 (MD–87),
and MD–88 airplanes; certificated in any
category; as identified in Boeing Alert
Service Bulletin MD80–29A070, Revision 1,
dated July 28, 2005.
Compliance
Required as indicated, unless
accomplished previously. To prevent shorted
wires or arcing at the auxiliary hydraulic
pump, which could result in loss of auxiliary
hydraulic power, or a fire in the wheel well
of the airplane; and to reduce the potential
of an ignition source adjacent to the fuel
tanks, which, in combination with flammable
fuel vapors, could result in a fuel tank
explosion and consequent loss of the
airplane; accomplish the following:
One-Time Inspection
(a) For airplanes in Configurations 1
through 3, as defined in Boeing Alert Service
Bulletin MD80–29A070, Revision 1, dated
VerDate Aug<31>2005
16:21 Mar 13, 2006
Jkt 208001
July 28, 2005: Within 18 months after the
effective date of this AD, do a one-time
general visual inspection for chafing or signs
of arcing of the wire bundle for the auxiliary
hydraulic pump, and do all applicable
corrective and other specified actions, in
accordance with the Accomplishment
Instructions of the service bulletin.
Accomplish all applicable corrective actions
before further flight after the inspection.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Installation of Additional Wiring Protection
(b) For airplanes in Configuration 4, as
defined in Boeing Alert Service Bulletin
MD80–29A070, Revision 1, dated July 28,
2005: Within 18 months after the effective
date of this AD, install additional protective
sleeving on the upper portion of the auxiliary
hydraulic pump wire assembly in accordance
with the procedures under Configuration 4 in
the Accomplishment Instructions of the
service bulletin.
Actions Accomplished Previously
(c) Actions accomplished before the
effective date of this AD in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin MD80–29A070, dated
August 3, 2004, are acceptable for
compliance with paragraph (a) of this AD,
except that the additional requirements of
paragraph (b) of this AD must be done on
airplanes in Configuration 4, as defined in
Boeing Alert Service Bulletin MD80–29A070,
Revision 1, dated July 28, 2005.
Alternative Methods of Compliance
(d)(1) In accordance with 14 CFR 39.19, the
Manager, Los Angeles Aircraft Certification
Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this
AD.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on March 7,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–3565 Filed 3–13–06; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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13053
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24118; Directorate
Identifier 2006–NM–034–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model BD–100–1A10 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model BD–100–
1A10 airplanes. This proposed AD
would require an inspection for signs of
arcing or heat damage of the electrical
connections of the terminal blocks,
ground studs, and the end of the wires
and surrounding insulation for the
windshield and side window anti-ice
systems; and repairing any arced or
damaged electrical connection. This
proposed AD also would require retorquing electrical connections of the
terminal blocks and ground studs for the
windshield and side window anti-ice
systems. This proposed AD results from
an in-service incident involving smoke
and odor in the cockpit. We are
proposing this AD to prevent loose
electrical connections that could arc and
overheat, and cause wiring damage of
the windshield and side window antiice systems. Such wiring damage could
result in smoke and/or fire in the flight
compartment.
DATES: We must receive comments on
this proposed AD by April 13, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
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13054
Federal Register / Vol. 71, No. 49 / Tuesday, March 14, 2006 / Proposed Rules
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
Wing Chan, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, New York Aircraft Certification
Office, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590;
telephone (516) 228–7311; fax (516)
794–5531.
SUPPLEMENTARY INFORMATION:
wwhite on PROD1PC65 with PROPOSAL
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24118; Directorate
Identifier 2006–NM–034–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
VerDate Aug<31>2005
16:21 Mar 13, 2006
Jkt 208001
Bombardier Model BD–100–1A10
airplanes. TCAA advises that an inservice incident occurred involving
smoke and odor in the cockpit.
Investigation revealed that the electrical
connections for the terminal blocks and
ground studs of the windshield and side
window anti-ice systems may not have
been torqued to the required value
during production of certain airplanes.
Loose electrical connections, if not
corrected, could arc and overheat,
which could result in wiring damage of
the windshield and side window antiice systems and consequent smoke and/
or fire in the flight compartment.
Relevant Service Information
Bombardier has issued Alert Service
Bulletin A100–30–03, Revision 01,
dated December 21, 2005. The service
bulletin describes procedures for doing
a special check for signs of arcing or
heat damage of the electrical
connections of the terminal blocks,
ground studs, and the ends of the wires
and surrounding insulation for the
windshield and side window anti-ice
systems; and repairing any arced or
damaged electrical connection. The
service bulletin also describes
procedures for re-torquing electrical
connections of the terminal blocks and
ground studs for the windshield and
side window anti-ice systems.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. TCAA mandated the service
information and issued Canadian
airworthiness directive CF–2006–01,
dated January 20, 2006, to ensure the
continued airworthiness of these
airplanes in Canada.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in Canada and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
TCAA has kept the FAA informed of the
situation described above. We have
examined TCAA’s findings, evaluated
all pertinent information, and
determined that we need to issue an AD
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Clarification
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
of the Proposed AD, Service Bulletin,
and Canadian Airworthiness Directive.’’
Clarification of the Proposed AD,
Service Bulletin, and Canadian
Airworthiness Directive
Although the service bulletin
specifies a ‘‘special check’’ and the
Canadian airworthiness directive
specifies to ‘‘visually inspect,’’ this
proposed AD would require a detailed
inspection for signs of arcing or heat
damage of the electrical connections of
the terminal blocks, ground studs, and
the ends of the wires and surrounding
insulation for the windshield and side
window anti-ice systems.
Costs of Compliance
This proposed AD would affect about
31 airplanes of U.S. registry. The
proposed actions would take about 4
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$9,920, or $320 per airplane.
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 have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
E:\FR\FM\14MRP1.SGM
14MRP1
Federal Register / Vol. 71, No. 49 / Tuesday, March 14, 2006 / Proposed Rules
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Bombardier, Inc.: Docket No. FAA–2006–
24118; Directorate Identifier 2006–NM–
034–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 13, 2006.
Applicability
(c) This AD applies to Bombardier Model
BD–100–1A10 airplanes, serial numbers
20006 through 20046 inclusive, 20048,
20051, and 20052; certificated in any
category.
wwhite on PROD1PC65 with PROPOSAL
Unsafe Condition
(d) This AD results from an in-service
incident involving smoke and odor in the
cockpit. We are issuing this AD to prevent
loose electrical connections that could arc
and overheat, and cause wiring damage of the
windshield and side window anti-ice
systems. Such wiring damage could result in
smoke and/or fire in the flight compartment.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspection, Repair, and Re-Torque
(f) Within 90 days after the effective date
of this AD, do the actions specified in
16:21 Mar 13, 2006
Jkt 208001
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(2) Re-torque the electrical connections of
the terminal blocks and ground studs for the
windshield and side window anti-ice
systems.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(h) Canadian airworthiness directive CF–
2006–01, issue date January 20, 2006, also
addresses the subject of this AD.
Affected ADs
(b) None.
VerDate Aug<31>2005
paragraphs (f)(1) and (f)(2) of this AD in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A100–30–03, Revision 01, dated
December 21, 2005.
(1) Do a detailed inspection for signs of
arcing or heat damage of the electrical
connections of the terminal blocks, ground
studs, and the end of the wires and
surrounding insulation for the windshield
and side window anti-ice systems. If any sign
of arcing or heat damage is detected, before
further flight, repair the arced or damaged
electrical connection.
Issued in Renton, Washington, on March 3,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–3567 Filed 3–13–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24119; Directorate
Identifier 2005–NM–100–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
13055
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 747 airplanes.
This proposed AD would require
repetitive mid- and low-frequency eddy
current inspections for cracks in the
overlapped skin panels in the fuselage
skin lap joints in sections 41, 42, 44,
and 46, and corrective actions if
necessary. This proposed AD is
prompted by a report indicating that an
operator found multiple small cracks in
the overlapped skin panels in the
fuselage skin lap joints. We are
proposing this AD to detect and correct
cracks in the overlapped skin panels,
which could join together and result in
reduced structural capability in the skin
and consequent rapid decompression of
the airplane.
DATES: We must receive comments on
this proposed AD by April 28, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2006–
24119; the directorate identifier for this
docket is 2005–NM–100–AD.
FOR FURTHER INFORMATION CONTACT:
Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6432; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\14MRP1.SGM
14MRP1
]]>Agencies
[Federal Register Volume 71, Number 49 (Tuesday, March 14, 2006)]
[Proposed Rules]
[Pages 13053-13055]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-3567]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24118; Directorate Identifier 2006-NM-034-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model BD-100-1A10 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model BD-100-1A10 airplanes. This proposed AD
would require an inspection for signs of arcing or heat damage of the
electrical connections of the terminal blocks, ground studs, and the
end of the wires and surrounding insulation for the windshield and side
window anti-ice systems; and repairing any arced or damaged electrical
connection. This proposed AD also would require re-torquing electrical
connections of the terminal blocks and ground studs for the windshield
and side window anti-ice systems. This proposed AD results from an in-
service incident involving smoke and odor in the cockpit. We are
proposing this AD to prevent loose electrical connections that could
arc and overheat, and cause wiring damage of the windshield and side
window anti-ice systems. Such wiring damage could result in smoke and/
or fire in the flight compartment.
DATES: We must receive comments on this proposed AD by April 13, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt
[[Page 13054]]
Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Wing Chan, Aerospace Engineer, Systems
and Flight Test Branch, ANE-172, New York Aircraft Certification
Office, FAA, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7311; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24118; Directorate Identifier 2006-NM-034-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Bombardier Model BD-100-1A10 airplanes. TCAA advises that an
in-service incident occurred involving smoke and odor in the cockpit.
Investigation revealed that the electrical connections for the terminal
blocks and ground studs of the windshield and side window anti-ice
systems may not have been torqued to the required value during
production of certain airplanes. Loose electrical connections, if not
corrected, could arc and overheat, which could result in wiring damage
of the windshield and side window anti-ice systems and consequent smoke
and/or fire in the flight compartment.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A100-30-03, Revision
01, dated December 21, 2005. The service bulletin describes procedures
for doing a special check for signs of arcing or heat damage of the
electrical connections of the terminal blocks, ground studs, and the
ends of the wires and surrounding insulation for the windshield and
side window anti-ice systems; and repairing any arced or damaged
electrical connection. The service bulletin also describes procedures
for re-torquing electrical connections of the terminal blocks and
ground studs for the windshield and side window anti-ice systems.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. TCAA mandated the
service information and issued Canadian airworthiness directive CF-
2006-01, dated January 20, 2006, to ensure the continued airworthiness
of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCAA has kept the FAA informed of
the situation described above. We have examined TCAA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Clarification of the
Proposed AD, Service Bulletin, and Canadian Airworthiness Directive.''
Clarification of the Proposed AD, Service Bulletin, and Canadian
Airworthiness Directive
Although the service bulletin specifies a ``special check'' and the
Canadian airworthiness directive specifies to ``visually inspect,''
this proposed AD would require a detailed inspection for signs of
arcing or heat damage of the electrical connections of the terminal
blocks, ground studs, and the ends of the wires and surrounding
insulation for the windshield and side window anti-ice systems.
Costs of Compliance
This proposed AD would affect about 31 airplanes of U.S. registry.
The proposed actions would take about 4 work hours per airplane, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $9,920, or $320
per airplane.
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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 13055]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Bombardier, Inc.: Docket No. FAA-2006-24118; Directorate Identifier
2006-NM-034-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 13,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model BD-100-1A10 airplanes,
serial numbers 20006 through 20046 inclusive, 20048, 20051, and
20052; certificated in any category.
Unsafe Condition
(d) This AD results from an in-service incident involving smoke
and odor in the cockpit. We are issuing this AD to prevent loose
electrical connections that could arc and overheat, and cause wiring
damage of the windshield and side window anti-ice systems. Such
wiring damage could result in smoke and/or fire in the flight
compartment.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection, Repair, and Re-Torque
(f) Within 90 days after the effective date of this AD, do the
actions specified in paragraphs (f)(1) and (f)(2) of this AD in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A100-30-03, Revision 01, dated December 21, 2005.
(1) Do a detailed inspection for signs of arcing or heat damage
of the electrical connections of the terminal blocks, ground studs,
and the end of the wires and surrounding insulation for the
windshield and side window anti-ice systems. If any sign of arcing
or heat damage is detected, before further flight, repair the arced
or damaged electrical connection.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(2) Re-torque the electrical connections of the terminal blocks
and ground studs for the windshield and side window anti-ice
systems.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, New York Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(h) Canadian airworthiness directive CF-2006-01, issue date
January 20, 2006, also addresses the subject of this AD.
Issued in Renton, Washington, on March 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-3567 Filed 3-13-06; 8:45 am]
BILLING CODE 4910-13-P
