Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 64651-64653 [E6-18573]
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mstockstill on PROD1PC61 with PROPOSALS
Federal Register / Vol. 71, No. 213 / Friday, November 3, 2006 / Proposed Rules
any cervids. The gradual escalation of
the Federal standard in the CWD rule to
5 years was intended to achieve the
desired level of risk control represented
by 5 years of program participation and
disease-free surveillance and
monitoring, but to do so in a gradual
manner that would not cause
widespread economic harm to
producers by making it impossible for
some of them to move animals interstate
until 5 years after they join the CWD
Herd Certification Program.
The petitioners raised two points with
regard to this Federal standard for
interstate movement. First, they cited it
as an unexpected and unnecessary
Federal preemption of existing State
standards. They stated that during
development of the CWD proposed rule
they believed that any Federal interstate
movement requirement would serve as
a minimum standard, and would apply
only if States did not set their own
standards for length-of-time. Second,
the petitioners questioned whether the
Federal standard provided adequate
protection, especially during the first 2
years of program implementation. The
petitioners suggested that sound science
and the known epidemiology of CWD
require that animals be monitored for
CWD for more than 1 or 2 years before
they can be considered safe to move
interstate.
The public is invited to comment on
any of the issues raised by the petitions.
To aid our evaluation of these issues, we
particularly invite comments in the
following areas.
• Consider the alternatives of
implementing a Federal interstate
movement standard versus allowing
individual State standards to apply.
What hardships or benefits would each
alternative impose? Please provide
details where possible.
• With respect to the spread of CWD,
in addition to the requirements
established by the APHIS CWD rule,
what additional safeguards do States
need to mitigate or reduce risk of
disease transmission, and why are they
needed?
• What practical or operational
problems may be expected from the
final rule and from the alternatives
suggested by the petitions? How could
they be alleviated?
• Are there any alternatives that
could address the petitioners’ concerns,
other than allowing the movement
requirements of individual States to take
precedence over the Federal standard?
After evaluating the petitions and any
public comments received in response
to this document, APHIS will publish a
document in the Federal Register
VerDate Aug<31>2005
12:59 Nov 02, 2006
Jkt 211001
announcing what action, if any, we will
take in response to the petitions.
Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22,
2.80, and 371.4.
Done in Washington, DC, this 31st day of
October 2006.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E6–18564 Filed 11–2–06; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26241; Directorate
Identifier 2006–NM–155–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–400
series airplanes. This proposed AD
would require inspecting to determine
the manufacturer’s date of certain Vband clamps on the engine exhaust
shroud assembly, and doing related
investigative/corrective actions if
necessary. This proposed AD results
from a report of a discrepancy found
during a maintenance inspection on a Vband clamp located on the engine
exhaust duct shroud. The clamp ends
were touching (although the correct
fastener torque had been applied),
resulting in reduced clamp force on the
flanges. We are proposing this AD to
prevent vibration in the duct shroud
and fretting of the V-band clamp and
flanges, which could result in cracking
of the flanges and consequent release of
hot exhaust gases from the engine
tailpipe and damage to adjacent
structure. This situation could trigger
the fire warning system and result in an
in-flight emergency, such as the
flightcrew shutting down the engine and
activating the fire suppression system.
DATES: We must receive comments on
this proposed AD by December 4, 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
SUMMARY:
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64651
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
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
Richard Fiesel, 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) 228–7304; 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–2006–26241; Directorate
Identifier 2006–NM–155–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.
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Federal Register / Vol. 71, No. 213 / Friday, November 3, 2006 / Proposed Rules
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 DHC–8–400 series
airplanes. TCCA advises of a report of
a discrepancy found during a
maintenance inspection on a V-band
clamp located on the engine exhaust
duct shroud. The clamp ends were
touching (although the correct fastener
torque had been applied), resulting in
reduced clamp force on the flanges.
Investigation revealed that a batch of Vband clamps were not manufactured to
the drawing specifications. These
clamps may cause vibration and fretting
of the V-band clamp flanges to occur,
leading to flange cracking and local area
overheating. These conditions, if not
corrected, could result in cracking of the
flanges and consequent release of hot
exhaust gases from the engine tailpipe
and damage to adjacent structure. This
situation could trigger the fire warning
system and result in an in-flight
emergency, such as the flightcrew
shutting down the engine and activating
the fire suppression system.
mstockstill on PROD1PC61 with PROPOSALS
Relevant Service Information
Bombardier has issued Service
Bulletin 84–78–01, Revision ‘A,’ dated
September 15, 2005. The service
bulletin describes procedures for
inspecting to determine the
manufacturer’s date of certain V-band
clamps on the engine exhaust shroud
assembly, and doing related
investigative and corrective actions if
necessary. The related investigative
action is measuring the gap between the
clamp loops at the T-bolt and trunnion.
The related corrective actions are as
follows:
• If both clamp loops touch when the
clamp is tightened to the specified
torque value: Replace the V-band clamp
with a serviceable clamp.
• If the gap between the clamp loops
is less than 0.050 inch when the clamp
is tightened to the specified torque
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12:59 Nov 02, 2006
Jkt 211001
value: Replace the V-band clamp on or
before the next C-check.
The corrective actions also include
inspecting the flange of the shroud
assemblies for any of the following
discrepancies:
• Indication(s) of exhaust gas leakage.
• Damage to surrounding structure or
adjacent assemblies as a result of gas
leakage.
• Indication(s) of chafing, fretting, or
cracking at the flanges of the related
shrouds.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. TCCA mandated the service
information and issued Canadian
airworthiness directive CF–2006–06,
dated April 4, 2006, to ensure the
continued airworthiness of these
airplanes in Canada.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in Canada and are 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, TCCA has
kept the FAA informed of the situation
described above. We have examined
TCCA’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 ‘‘Differences
Between the Proposed AD and Service
Information.’’
Differences Between the Proposed AD
and Service Information
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions using
a method that we or TCCA (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair we or TCCA approve would be
acceptable for compliance with this
proposed AD.
The service bulletin specifies
replacing the V-band clamp ‘‘on or
before the next C-check’’ as part of the
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corrective actions. This proposed AD
would require doing all corrective
actions before further flight.
Costs of Compliance
This proposed AD would affect about
21 airplanes of U.S. registry. The
proposed actions would take about 3
work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts cost would be minimal.
Based on these figures, the estimated
cost of the proposed AD for U.S.
operators is $5,040, or $240 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;
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
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Federal Register / Vol. 71, No. 213 / Friday, November 3, 2006 / Proposed Rules
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. (Formerly de Havilland,
Inc.): Docket No. FAA–2006–26241;
Directorate Identifier 2006–NM–155–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by December 4, 2006.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400 series airplanes, certificated in
any category; as identified in Bombardier
Service Bulletin 84–78–01, Revision ‘A,’
dated September 15, 2005.
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Unsafe Condition
(d) This AD results from a report of a
discrepancy found during a maintenance
inspection on a V-band clamp located on the
engine exhaust duct shroud. The clamp ends
were touching (although the correct fastener
torque had been applied), resulting in
reduced clamp force on the flanges. We are
issuing this AD to prevent vibration in the
duct shroud and fretting of the V-band clamp
and flanges, which could result in cracking
of the flanges and consequent release of hot
exhaust gases from the engine tailpipe and
damage to adjacent structure. This situation
could trigger the fire warning system and
result in an in-flight emergency, such as the
flightcrew shutting down the engine and
activating the fire suppression system.
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.
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13:43 Nov 02, 2006
Jkt 211001
Actions Accomplished According to
Previous Issue of Service Bulletin
(h) Actions accomplished before the
effective date of this AD according to
Bombardier Service Bulletin 84–78–01, dated
March 22, 2005, are considered acceptable
for compliance with the corresponding
actions specified in paragraph (f) of this AD.
Affected ADs
(b) None.
Inspection/Investigative and Corrective
Actions
(f) Within 5,000 flight hours after the
effective date of this AD: Inspect to
determine the part number (P/N) of the
V-band clamps on the engine exhaust duct
shroud in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–78–01, Revision ‘A,’
dated September 15, 2005. For any V-band
clamp having P/N VC1642A–2030–A or
VC1642A–1875–A, before further flight,
determine the manufacturer’s date and do all
applicable related investigative and
corrective actions (including inspecting the
flange of the shroud assemblies for
discrepancies), by accomplishing all the
actions specified in the Accomplishment
Instructions of the service bulletin; except as
provided by paragraph (g) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
(g) If, during the accomplishment of the
corrective actions required by paragraph (f) of
this AD, the service bulletin specifies
contacting the manufacturer for repair
instructions, before further flight, repair in
accordance with a method approved by
either the Manager, New York Aircraft
Certification Office (ACO), FAA; or Transport
Canada Civil Aviation (TCCA) (or its
delegated agent).
Parts Installation
(i) As of the effective date of this AD, no
person may install a V-band clamp, P/N
VC1642A–2030–A or VC1642A–1875–A,
with a manufacturer batch stamp dated
before ‘‘08–02,’’ on any airplane.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, New York ACO, 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
(k) Canadian airworthiness directive CF–
2006–06, dated April 4, 2006, also addresses
the subject of this AD.
Issued in Renton, Washington, on October
26, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–18573 Filed 11–2–06; 8:45 am]
BILLING CODE 4910–13–P
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64653
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25929; Directorate
Identifier 2006–CE–54–AD]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd., PC–6 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued 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 the discovery of exfoliation
corrosion in the fittings of some PC–6
airplanes. These fittings are installed
exterior to the bottom skin of the wing
skin. If not corrected, undetected
corrosion in this area could lead to
failure of the fitting and subsequent loss
of control of the airplane. The proposed
AD would require actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by December 4, 2006.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
E:\FR\FM\03NOP1.SGM
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]]>Agencies
[Federal Register Volume 71, Number 213 (Friday, November 3, 2006)]
[Proposed Rules]
[Pages 64651-64653]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-18573]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26241; Directorate Identifier 2006-NM-155-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
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 DHC-8-400 series airplanes. This proposed
AD would require inspecting to determine the manufacturer's date of
certain V-band clamps on the engine exhaust shroud assembly, and doing
related investigative/corrective actions if necessary. This proposed AD
results from a report of a discrepancy found during a maintenance
inspection on a V-band clamp located on the engine exhaust duct shroud.
The clamp ends were touching (although the correct fastener torque had
been applied), resulting in reduced clamp force on the flanges. We are
proposing this AD to prevent vibration in the duct shroud and fretting
of the V-band clamp and flanges, which could result in cracking of the
flanges and consequent release of hot exhaust gases from the engine
tailpipe and damage to adjacent structure. This situation could trigger
the fire warning system and result in an in-flight emergency, such as
the flightcrew shutting down the engine and activating the fire
suppression system.
DATES: We must receive comments on this proposed AD by December 4,
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 Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Richard Fiesel, 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) 228-7304; 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-
26241; Directorate Identifier 2006-NM-155-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.
[[Page 64652]]
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 DHC-8-400 series airplanes. TCCA advises of a
report of a discrepancy found during a maintenance inspection on a V-
band clamp located on the engine exhaust duct shroud. The clamp ends
were touching (although the correct fastener torque had been applied),
resulting in reduced clamp force on the flanges. Investigation revealed
that a batch of V-band clamps were not manufactured to the drawing
specifications. These clamps may cause vibration and fretting of the V-
band clamp flanges to occur, leading to flange cracking and local area
overheating. These conditions, if not corrected, could result in
cracking of the flanges and consequent release of hot exhaust gases
from the engine tailpipe and damage to adjacent structure. This
situation could trigger the fire warning system and result in an in-
flight emergency, such as the flightcrew shutting down the engine and
activating the fire suppression system.
Relevant Service Information
Bombardier has issued Service Bulletin 84-78-01, Revision `A,'
dated September 15, 2005. The service bulletin describes procedures for
inspecting to determine the manufacturer's date of certain V-band
clamps on the engine exhaust shroud assembly, and doing related
investigative and corrective actions if necessary. The related
investigative action is measuring the gap between the clamp loops at
the T-bolt and trunnion. The related corrective actions are as follows:
If both clamp loops touch when the clamp is tightened to
the specified torque value: Replace the V-band clamp with a serviceable
clamp.
If the gap between the clamp loops is less than 0.050 inch
when the clamp is tightened to the specified torque value: Replace the
V-band clamp on or before the next C-check.
The corrective actions also include inspecting the flange of the
shroud assemblies for any of the following discrepancies:
Indication(s) of exhaust gas leakage.
Damage to surrounding structure or adjacent assemblies as
a result of gas leakage.
Indication(s) of chafing, fretting, or cracking at the
flanges of the related shrouds.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. TCCA mandated the
service information and issued Canadian airworthiness directive CF-
2006-06, dated April 4, 2006, to ensure the continued airworthiness of
these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are 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, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA'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 ``Differences Between
the Proposed AD and Service Information.''
Differences Between the Proposed AD and Service Information
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or TCCA
(or its delegated agent) approve. In light of the type of repair that
would be required to address the unsafe condition, and consistent with
existing bilateral airworthiness agreements, we have determined that,
for this proposed AD, a repair we or TCCA approve would be acceptable
for compliance with this proposed AD.
The service bulletin specifies replacing the V-band clamp ``on or
before the next C-check'' as part of the corrective actions. This
proposed AD would require doing all corrective actions before further
flight.
Costs of Compliance
This proposed AD would affect about 21 airplanes of U.S. registry.
The proposed actions would take about 3 work hours per airplane, at an
average labor rate of $80 per work hour. Required parts cost would be
minimal. Based on these figures, the estimated cost of the proposed AD
for U.S. operators is $5,040, or $240 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;
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
[[Page 64653]]
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. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
26241; Directorate Identifier 2006-NM-155-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
4, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400 series
airplanes, certificated in any category; as identified in Bombardier
Service Bulletin 84-78-01, Revision `A,' dated September 15, 2005.
Unsafe Condition
(d) This AD results from a report of a discrepancy found during
a maintenance inspection on a V-band clamp located on the engine
exhaust duct shroud. The clamp ends were touching (although the
correct fastener torque had been applied), resulting in reduced
clamp force on the flanges. We are issuing this AD to prevent
vibration in the duct shroud and fretting of the V-band clamp and
flanges, which could result in cracking of the flanges and
consequent release of hot exhaust gases from the engine tailpipe and
damage to adjacent structure. This situation could trigger the fire
warning system and result in an in-flight emergency, such as the
flightcrew shutting down the engine and activating the fire
suppression system.
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/Investigative and Corrective Actions
(f) Within 5,000 flight hours after the effective date of this
AD: Inspect to determine the part number (P/N) of the V-band clamps
on the engine exhaust duct shroud in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-78-01,
Revision `A,' dated September 15, 2005. For any V-band clamp having
P/N VC1642A-2030-A or VC1642A-1875-A, before further flight,
determine the manufacturer's date and do all applicable related
investigative and corrective actions (including inspecting the
flange of the shroud assemblies for discrepancies), by accomplishing
all the actions specified in the Accomplishment Instructions of the
service bulletin; except as provided by paragraph (g) of this AD. Do
all applicable related investigative and corrective actions before
further flight.
(g) If, during the accomplishment of the corrective actions
required by paragraph (f) of this AD, the service bulletin specifies
contacting the manufacturer for repair instructions, before further
flight, repair in accordance with a method approved by either the
Manager, New York Aircraft Certification Office (ACO), FAA; or
Transport Canada Civil Aviation (TCCA) (or its delegated agent).
Actions Accomplished According to Previous Issue of Service Bulletin
(h) Actions accomplished before the effective date of this AD
according to Bombardier Service Bulletin 84-78-01, dated March 22,
2005, are considered acceptable for compliance with the
corresponding actions specified in paragraph (f) of this AD.
Parts Installation
(i) As of the effective date of this AD, no person may install a
V-band clamp, P/N VC1642A-2030-A or VC1642A-1875-A, with a
manufacturer batch stamp dated before ``08-02,'' on any airplane.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, New York ACO, 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
(k) Canadian airworthiness directive CF-2006-06, dated April 4,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on October 26, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-18573 Filed 11-2-06; 8:45 am]
BILLING CODE 4910-13-P
