Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 50288-50290 [E7-17282]
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50288
Federal Register / Vol. 72, No. 169 / Friday, August 31, 2007 / Proposed Rules
thereafter accomplish dye penetrant
inspections at intervals not to exceed 12
months or 2,500 landings, whichever occurs
earlier. For airplane categories 3 and 4, repeat
at this interval until the inspection required
by paragraph (k) of this AD is accomplished.
(2) If an initial dye penetrant inspection is
accomplished, and no crack is found,
accomplish repetitive dye penetrant
inspections at intervals not to exceed 12
months or 2,500 landings, whichever occurs
earlier. For airplane categories 3 and 4, repeat
at this interval until the inspection required
by paragraph (k) of this AD is accomplished.
(3) If an initial special detailed inspection
is accomplished after the effective date of
this AD, and no crack is found, repeat the
inspection in accordance with paragraph (k)
of this AD.
Corrective Action
(h) Except as provided by paragraph (l) of
this AD: If any crack is detected during any
inspection required by paragraph (g) or (j) of
this AD, before further flight, remove and
replace the rudder pedal bracket assembly in
accordance with the service bulletin. Prior to
the accumulation of 40,000 total landings
after replacement with the new part, resume
the repetitive inspections in accordance with
paragraph (g) or (k) of this AD, as applicable.
Doing the action required by paragraph (l) of
this AD terminates the requirements of this
paragraph for airplane category 4.
Terminating Action for Certain Airplanes
(i) For airplane categories 3 and 4: Do the
actions in paragraphs (i)(1) and (i)(2) of this
AD in accordance with the Accomplishment
Instructions of the service bulletin.
(1) Before the accumulation of 75,000 total
landings on the captain’s rudder pedal
bracket assembly, P/N 5616067–501, or
within 60 months after May 16, 2006,
whichever occurs later: Remove the rudder
pedal bracket assembly and replace it with
new, improved P/N 5962903–501.
Accomplishment of the replacement
terminates the repetitive inspections of the
captain’s rudder pedal bracket assembly
required by paragraphs (g), (h), (j), (k), and (l)
of this AD.
(2) Before the accumulation of 75,000 total
landings on the first officer’s rudder pedal
bracket assembly, P/N 5616068–501, or
within 60 months after May 16, 2006,
whichever occurs later: Remove the rudder
pedal bracket assembly and replace it with
new, improved P/N 5962904–501.
Accomplishment of the replacement
terminates the repetitive inspections of the
first officer’s rudder pedal bracket assembly
required by paragraphs (g), (h), (j), (k), and (l)
of this AD.
yshivers on PROD1PC62 with PROPOSALS
New Requirements of This AD
Revised Initial Inspection at Reduced
Threshold for Certain Airplanes
(j) For airplane categories 2 and 4, at the
applicable time specified in paragraph (j)(1),
(j)(2) or (j)(3) of this AD: Do a special detailed
inspection for cracking of the captain’s and
first officer’s rudder pedal bracket, part
numbers (P/N) 5616067 and 5616068,
respectively, in accordance with the service
bulletin. Doing this inspection terminates the
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15:10 Aug 30, 2007
Jkt 211001
inspection requirements of paragraphs (g)
and (h) of this AD for airplane category 4.
(1) For category 2 airplanes: Before the
accumulation of 40,000 total landings or
within 30 days after the effective date of this
AD, whichever occurs later.
(2) For category 4 airplanes that have
accumulated fewer than 25,000 total landings
as of the effective date of this AD: Before the
accumulation of 25,000 total landings, or
within 3,000 landings after the effective date
of this AD, whichever occurs later.
(3) For category 4 airplanes that have
accumulated 25,000 or more total landings as
of the effective date of this AD, do the next
inspection at the applicable time in
paragraph (j)(3)(i) or (j)(3)(ii) of this AD.
(i) For category 4 airplanes on which the
corrective action specified in paragraph (h) of
this AD has not been accomplished, do the
inspection within 3,000 landings after the
effective date of this AD.
(ii) For category 4 airplanes on which the
corrective action required by paragraph (h) of
this AD has been accomplished, do the
inspection at the earlier of the following: The
next repetitive interval required by paragraph
(h) of this AD; 40,000 total landings after
doing the corrective action required by
paragraph (h) of this AD; or 3,000 landings
after the effective date of this AD.
Repetitive Inspections at Revised Interval for
Certain Airplanes
(k) For airplane categories 3 and 4: Repeat
the special detailed inspection required by
paragraph (g) or (j) of this AD thereafter at
intervals not to exceed 3,000 landings. Doing
the first repetitive inspection required by this
paragraph terminates the repetitive
inspection requirements of paragraph (g) of
this AD for airplane categories 3 and 4.
Corrective Action Including Reduced
Inspection Threshold for Certain Airplanes
(l) For airplane category 4: If any crack is
detected during any inspection required by
paragraph (g), (j), or (k) of this AD: Before
further flight, remove and replace the rudder
pedal bracket assembly in accordance with
the service bulletin. Before the accumulation
of 25,000 total landings after replacement
with the new part, resume the repetitive
inspections in accordance with paragraph (k)
of this AD. Doing the action in this paragraph
terminates the requirements of paragraph (h)
of this AD for airplane category 4.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Los Angeles Aircraft
Certification Office, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with 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) AMOCs, approved previously in
accordance with AD 2006–07–25,
amendment 39–14552; and AD 89–14–02,
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amendment 39–6245; are approved as
AMOCs for the corresponding requirements
of this AD.
Issued in Renton, Washington, on August
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–17287 Filed 8–30–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29066; Directorate
Identifier 2007–NM–147–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 Airplanes
Federal Aviation
Administration (FAA), 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)
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:
It has been discovered in several cases that
clamp bolts of the elevator spring tab
mechanism were not installed in the correct
orientation. Bolts have been found installed
with bolt heads on the lower position and in
two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing.
Detachment of an elevator spring tab
mechanism clamp bolt could lead to jamming
of the elevator control system and reduced
controllability of the aircraft.
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 October 1, 2007.
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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
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Federal Register / Vol. 72, No. 169 / Friday, August 31, 2007 / Proposed Rules
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
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 Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, 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.
FOR FURTHER INFORMATION CONTACT: Dan
Parrillo, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7305; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–29066; Directorate Identifier
2007–NM–147–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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 we receive
about this proposed AD.
yshivers on PROD1PC62 with PROPOSALS
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2007–08, dated June 4, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
It has been discovered in several cases that
clamp bolts of the elevator spring tab
mechanism were not installed in the correct
VerDate Aug<31>2005
15:10 Aug 30, 2007
Jkt 211001
orientation. Bolts have been found installed
with bolt heads on the lower position and in
two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing.
Detachment of an elevator spring tab
mechanism clamp bolt could lead to jamming
of the elevator control system and reduced
controllability of the aircraft.
The MCAI requires a one-time
inspection of the left- and right-hand
elevator spring tab mechanism hardware
for correct installation, and prior to
further flight, installing new hardware
for any hardware that is incorrectly
installed. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Bombardier has issued Service
Bulletin 8–27–106, dated February 7,
2006. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
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 proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a Note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 150 products of U.S.
registry. We also estimate that it would
take about 3 work-hours per product to
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Sfmt 4702
50289
comply with the basic requirements of
this proposed AD. Required parts would
cost about $0 per product. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. The average
labor rate is $80 per work-hour. Based
on these figures, we estimate the cost of
the proposed AD on U.S. operators to be
$36,000, or $240 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 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 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. 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.
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50290
Federal Register / Vol. 72, No. 169 / Friday, August 31, 2007 / Proposed Rules
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:
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2007–29066;
Directorate Identifier 2007–NM–147–AD.
Comments Due Date
(a) We must receive comments by October
1, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes; certificated in any
category; serial numbers 003 through 611
inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
yshivers on PROD1PC62 with PROPOSALS
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
It has been discovered in several cases that
clamp bolts of the elevator spring tab
mechanism were not installed in the correct
orientation. Bolts have been found installed
with bolt heads on the lower position and in
two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing.
Detachment of an elevator spring tab
mechanism clamp bolt could lead to jamming
of the elevator control system and reduced
controllability of the aircraft.
The MCAI requires a one-time inspection
of the left- and right-hand elevator spring tab
mechanism hardware for correct installation,
and prior to further flight, installing new
hardware for any hardware that is incorrectly
installed.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 12 months after the effective
date of this AD: Carry out a one-time
inspection of the left- and right-hand elevator
spring tab mechanism hardware for correct
installation according to the
Accomplishment Instructions of Bombardier
Service Bulletin 8–27–106, dated February 7,
2006.
VerDate Aug<31>2005
15:10 Aug 30, 2007
Jkt 211001
DEPARTMENT OF TRANSPORTATION
FAA AD Differences
RIN 2120–AA64
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(2) If any hardware is found incorrectly
installed during the inspection required by
paragraph (f)(1) of this AD, prior to further
flight, install new hardware according to the
Accomplishment Instructions of Bombardier
Service Bulletin 8–27–106, dated February 7,
2006.
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, 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: Dan Parrillo,
Aerospace Engineer, Systems and Flight Test
Branch, ANE–172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590;
telephone (516) 228–7305; 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–2007–08, dated June 4, 2007,
and Bombardier Service Bulletin 8–27–106,
dated February 7, 2006, for related
information.
Issued in Renton, Washington, on August
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–17282 Filed 8–30–07; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29067; Directorate
Identifier 2007–NM–148–AD]
Airworthiness Directives; Boeing
Model 757–200, –200CB, and –300
Series 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 Boeing Model 757–200, –200CB,
and –300 series airplanes. This
proposed AD would require doing a
detailed inspection for damage of the
wire bundle of the right recirculation
fan, and repair if necessary. This
proposed AD would also require rerouting the wire bundle of the right
recirculation fan. This proposed AD
results from a report indicating that,
during landing of a Model 757 airplane,
an overheat warning and smoke
occurred in the main cabin, and the
right recirculation fan stopped
operating. We are proposing this AD to
prevent damage of the wiring bundle of
the right recirculation fan. Such damage
could result in a short circuit and
possible fire in the mix bay or smoke in
the main cabin.
DATES: We must receive comments on
this proposed AD by October 15, 2007.
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
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]]>Agencies
[Federal Register Volume 72, Number 169 (Friday, August 31, 2007)]
[Proposed Rules]
[Pages 50288-50290]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-17282]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29066; Directorate Identifier 2007-NM-147-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
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) 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:
It has been discovered in several cases that clamp bolts of the
elevator spring tab mechanism were not installed in the correct
orientation. Bolts have been found installed with bolt heads on the
lower position and in two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing. Detachment of an
elevator spring tab mechanism clamp bolt could lead to jamming of
the elevator control system and reduced controllability of the
aircraft.
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 October 1, 2007.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
[[Page 50289]]
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., 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 Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, 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.
FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7305; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
29066; Directorate Identifier 2007-NM-147-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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 we
receive about this proposed AD.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, has issued Canadian Airworthiness Directive CF-
2007-08, dated June 4, 2007 (referred to after this as ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
It has been discovered in several cases that clamp bolts of the
elevator spring tab mechanism were not installed in the correct
orientation. Bolts have been found installed with bolt heads on the
lower position and in two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing. Detachment of an
elevator spring tab mechanism clamp bolt could lead to jamming of
the elevator control system and reduced controllability of the
aircraft.
The MCAI requires a one-time inspection of the left- and right-hand
elevator spring tab mechanism hardware for correct installation, and
prior to further flight, installing new hardware for any hardware that
is incorrectly installed. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Bombardier has issued Service Bulletin 8-27-106, dated February 7,
2006. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
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 proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 150 products of U.S. registry. We also estimate that
it would take about 3 work-hours per product to comply with the basic
requirements of this proposed AD. Required parts would cost about $0
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these costs. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. The average labor rate is $80 per work-hour. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $36,000, or $240 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 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 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. 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.
[[Page 50290]]
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 FAA amends Sec. 39.13 by adding the following new AD:
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2007-
29066; Directorate Identifier 2007-NM-147-AD.
Comments Due Date
(a) We must receive comments by October 1, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes; certificated in any
category; serial numbers 003 through 611 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
It has been discovered in several cases that clamp bolts of the
elevator spring tab mechanism were not installed in the correct
orientation. Bolts have been found installed with bolt heads on the
lower position and in two cases, some bolts, nuts and washers
[hardware] were found to be loose or missing. Detachment of an
elevator spring tab mechanism clamp bolt could lead to jamming of
the elevator control system and reduced controllability of the
aircraft.
The MCAI requires a one-time inspection of the left- and right-
hand elevator spring tab mechanism hardware for correct
installation, and prior to further flight, installing new hardware
for any hardware that is incorrectly installed.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 12 months after the effective date of this AD: Carry
out a one-time inspection of the left- and right-hand elevator
spring tab mechanism hardware for correct installation according to
the Accomplishment Instructions of Bombardier Service Bulletin 8-27-
106, dated February 7, 2006.
(2) If any hardware is found incorrectly installed during the
inspection required by paragraph (f)(1) of this AD, prior to further
flight, install new hardware according to the Accomplishment
Instructions of Bombardier Service Bulletin 8-27-106, dated February
7, 2006.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office, 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: Dan Parrillo, Aerospace
Engineer, Systems and Flight Test Branch, ANE-172, FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516) 228-7305; 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-2007-08,
dated June 4, 2007, and Bombardier Service Bulletin 8-27-106, dated
February 7, 2006, for related information.
Issued in Renton, Washington, on August 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-17282 Filed 8-30-07; 8:45 am]
BILLING CODE 4910-13-P
