Airworthiness Directives; Bombardier, Inc. Airplanes, 75906-75908 [2012-30925]
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75906
Proposed Rules
Federal Register
Vol. 77, No. 247
Wednesday, December 26, 2012
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1311; Directorate
Identifier 2011–NM–204–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–102,
–103, and –106 airplanes, and Model
DHC–8–200, –300, and –400 series
airplanes. This proposed AD was
prompted by reports of excessive wear
found in the clevis (bolt) hole where the
rod assembly attaches to the rudder/
brake pedal bellcrank, due to prolonged
fretting. This proposed AD would
require measuring the bellcrank clevis
holes, inspecting for cracking of the
bellcrank, and re-working the clevis
holes with steel bushings, or replacing
the bellcrank. We are proposing this AD
to detect and correct a worn or cracked
clevis hole, which could cause failure of
the bellcrank on one side, with
subsequent asymmetric braking and
consequent runway excursion.
DATES: We must receive comments on
this proposed AD by February 11, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• 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.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
ebenthall on DSK5TPTVN1PROD with
SUMMARY:
VerDate Mar<15>2010
06:27 Dec 22, 2012
Jkt 229001
W12–140, 1200 New Jersey Avenue SE.,
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 Bombardier,
Inc., Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email
thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains 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:
Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7363; 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–2012–1311; Directorate Identifier
2011–NM–204–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://
PO 00000
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Fmt 4702
Sfmt 4702
www.regulations.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 aviation authority
for Canada, has issued Canadian AD
CF–2011–32, dated August 15, 2011
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
There have been several in-service reports
of excessive wear found in the bolt [clevis]
hole where the rod assembly, Part Numbers
(P/N) 82710795–001 or 82710024–003, is
attached to the rudder/brake pedal bellcrank.
An investigation revealed that the wear was
attributed to prolonged fretting.
Failure of the bellcrank on one side could
lead to asymmetric braking and may lead to
runway excursion.
This directive mandates [measuring clevis
holes for length, and for certain bellcranks
doing a liquid penetrant inspection for
cracking, and] the re-work [by installing steel
bushings] or replacement of each bellcrank,
P/N 82710022–001/–002, 82710029–001/–
002, 82710813–001/–002 and 82710814–001/
–002, found with a worn [or cracked] bolt
hole.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Bombardier, Inc. has issued Service
Bulletins 8–27–111 and 84–27–55, both
dated June 15, 2011. 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.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules
4. 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.
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.
ebenthall on DSK5TPTVN1PROD with
affect about 178 products of U.S.
registry. We also estimate that it would
take about 5 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$75,650, or $425 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 16 work-hours and require parts
costing up to $2,532, for a cost of $3,892
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. We have no
way of determining the number of
products that may need these actions.
1. The authority citation for part 39
continues to read as follows:
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);
3. Will not affect intrastate aviation in
Alaska; and
VerDate Mar<15>2010
06:27 Dec 22, 2012
Jkt 229001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc.: Docket No. FAA–2012–
1311; Directorate Identifier 2011–NM–
204–AD.
(a) Comments Due Date
We must receive comments by February
11, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.
airplanes, certificated in any category, as
specified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 airplanes: Serial
numbers 003 through 672 inclusive.
(2) Model DHC–8–400, –401 and –402
airplanes: Serial numbers 4003 through 4372
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27: Flight controls.
(e) Reason
This AD was prompted by reports of
excessive wear found in the clevis (bolt) hole
where the rod assembly attaches to the
rudder/brake pedal bellcrank, due to
prolonged fretting. We are issuing this AD to
detect and correct a worn or cracked clevis
hole, which could cause failure of the
bellcrank on one side, with subsequent
asymmetric braking and consequent runway
excursion.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
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75907
compliance times specified, unless the
actions have already been done.
(g) Actions for Model DHC–8–100, –200, and
–300 Series Airplanes
For Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 airplanes: Within
6,000 flight hours or 24 months after the
effective date of this AD, whichever occurs
first, measure the edge-to-edge length of the
clevis holes of each bellcrank; and, if the
length is less than or equal to 0.218 inch,
inspect for cracking of each bellcrank using
liquid penetrant; in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–27–111, dated June 15,
2011.
(1) If no cracking is found: Before further
flight, rework the bellcrank, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 8–27–111, dated
June 15, 2011.
(2) If any clevis hole is greater than 0.218
inch, or if any cracking is found: Before
further flight, replace the bellcrank with a
new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–27–111, dated June 15,
2011.
(h) Actions for Certain Model DHC–8–400
Series Airplanes
For Model DHC–8–400, –401, and –402
airplanes that have accumulated less than or
equal to 15,000 total flight hours as of the
effective date of this AD: Within 6,000 flight
hours after the effective date of this AD, but
not to exceed 15,600 total flight hours,
measure the edge-to-edge length of the clevis
holes of each bellcrank, and inspect for
cracking of each bellcrank using liquid
penetrant; in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: Within 6,000 flight
hours after the effective date of this AD, but
not to exceed 15,600 total flight hours,
rework or replace the bellcrank, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, dated June 15, 2011.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.218
inch but less than or equal to 0.248 inch:
Within 6,000 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch but less than or equal to 0.278 inch:
Within 1,200 flight hours after doing the
measurement/inspection required by
paragraph (h) of this AD, replace the
bellcrank with a new bellcrank, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, dated June 15, 2011.
(4) If any cracking is found, or if any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
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75908
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules
with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
ebenthall on DSK5TPTVN1PROD with
(i) Actions for Certain Other Model DHC–8–
400 Series Airplanes
For Model DHC–8–400, –401, and –402
airplanes that have accumulated more than
15,000 total flight hours as of the effective
date of this AD: Within 600 flight hours after
the effective date of this AD, measure the
edge-to-edge length of the clevis holes of
each bellcrank, and inspect for cracking of
each bellcrank using liquid penetrant; in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, dated June 15, 2011.
(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: At the later of the
compliance times specified in paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD, rework or
replace the bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(i) Within 6,000 flight hours after the
effective date of this AD, but not to exceed
15,600 total flight hours.
(ii) Within 1,200 flight hours after the
effective date of this AD.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.218
inch but less than or equal to 0.248 inch:
Within 6,000 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch but less than or equal to 0.278 inch:
Within 1,200 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(4) If any cracking is found, or any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7300; fax (516)
794–5531. Before using any approved AMOC,
VerDate Mar<15>2010
06:27 Dec 22, 2012
Jkt 229001
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(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.
(k) Related Information
(1) Refer to MCAI Canadian Airworthiness
Directive CF–2011–32, dated August 15,
2011, and the service bulletins specified in
paragraphs (k)(1) (i) and (k)(1)(ii) of this AD,
for related information.
(i) Bombardier Service Bulletin 8–27–111,
dated June 15, 2011.
(ii) Bombardier Service Bulletin 84–27–55,
dated June 15, 2011.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q–Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com. You
may review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–30925 Filed 12–21–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1313; Directorate
Identifier 2012–NM–080–AD]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace Corporation
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Gulfstream Aerospace Corporation
Model GV and GV–SP airplanes. This
proposed AD was prompted by reports
of two failures of the fuel boost pump
and over-heat damage found on the
internal components and external
SUMMARY:
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
housing. This proposed AD would
require doing an inspection to
determine if fuel boost pumps having a
certain part number are installed,
replacing the fuel boost pumps having
a certain part number, and revising the
airplane maintenance program to
include revised instructions for
continued airworthiness. We are
proposing this AD to prevent fuel
leakage into the dry cavity of the boost
pump and outside of the fuel pump, and
to prevent capacitor clearance issues in
the dry cavity, which together could
result in an uncontrolled fire in the
wheel well.
DATES: We must receive comments on
this proposed AD by February 11, 2013.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• 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.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Gulfstream, Triumph
Aerostructures, and GE Aviation service
information identified in this proposed
AD, contact Gulfstream Aerospace
Corporation, Technical Publications
Dept., P.O. Box 2206, Savannah, GA
31402–2206; telephone 800–810–4853;
fax 912–965–3520; email
pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
E:\FR\FM\26DEP1.SGM
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]]>Agencies
[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Proposed Rules]
[Pages 75906-75908]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30925]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 /
Proposed Rules
[[Page 75906]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1311; Directorate Identifier 2011-NM-204-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes, and
Model DHC-8-200, -300, and -400 series airplanes. This proposed AD was
prompted by reports of excessive wear found in the clevis (bolt) hole
where the rod assembly attaches to the rudder/brake pedal bellcrank,
due to prolonged fretting. This proposed AD would require measuring the
bellcrank clevis holes, inspecting for cracking of the bellcrank, and
re-working the clevis holes with steel bushings, or replacing the
bellcrank. We are proposing this AD to detect and correct a worn or
cracked clevis hole, which could cause failure of the bellcrank on one
side, with subsequent asymmetric braking and consequent runway
excursion.
DATES: We must receive comments on this proposed AD by February 11,
2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
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.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., 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
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains 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: Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7363; 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-2012-1311;
Directorate Identifier 2011-NM-204-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://www.regulations.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 aviation
authority for Canada, has issued Canadian AD CF-2011-32, dated August
15, 2011 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
There have been several in-service reports of excessive wear
found in the bolt [clevis] hole where the rod assembly, Part Numbers
(P/N) 82710795-001 or 82710024-003, is attached to the rudder/brake
pedal bellcrank. An investigation revealed that the wear was
attributed to prolonged fretting.
Failure of the bellcrank on one side could lead to asymmetric
braking and may lead to runway excursion.
This directive mandates [measuring clevis holes for length, and
for certain bellcranks doing a liquid penetrant inspection for
cracking, and] the re-work [by installing steel bushings] or
replacement of each bellcrank, P/N 82710022-001/-002, 82710029-001/-
002, 82710813-001/-002 and 82710814-001/-002, found with a worn [or
cracked] bolt hole.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier, Inc. has issued Service Bulletins 8-27-111 and 84-27-
55, both dated June 15, 2011. 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.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would
[[Page 75907]]
affect about 178 products of U.S. registry. We also estimate that it
would take about 5 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $75,650, or $425 per product.
In addition, we estimate that any necessary follow-on actions would
take about 16 work-hours and require parts costing up to $2,532, for a
cost of $3,892 per product. Where the service information lists
required parts costs that are covered under warranty, we have assumed
that there will be no charge for these parts. As we do not control
warranty coverage for affected parties, some parties may incur costs
higher than estimated here. We have no way of determining the number of
products that may need these actions.
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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.: Docket No. FAA-2012-1311; Directorate Identifier
2011-NM-204-AD.
(a) Comments Due Date
We must receive comments by February 11, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. airplanes, certificated in
any category, as specified in paragraphs (c)(1) and (c)(2) of this
AD.
(1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Serial numbers 003 through 672 inclusive.
(2) Model DHC-8-400, -401 and -402 airplanes: Serial numbers
4003 through 4372 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27: Flight
controls.
(e) Reason
This AD was prompted by reports of excessive wear found in the
clevis (bolt) hole where the rod assembly attaches to the rudder/
brake pedal bellcrank, due to prolonged fretting. We are issuing
this AD to detect and correct a worn or cracked clevis hole, which
could cause failure of the bellcrank on one side, with subsequent
asymmetric braking and consequent runway excursion.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Actions for Model DHC-8-100, -200, and -300 Series Airplanes
For Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Within 6,000 flight hours or 24 months after the
effective date of this AD, whichever occurs first, measure the edge-
to-edge length of the clevis holes of each bellcrank; and, if the
length is less than or equal to 0.218 inch, inspect for cracking of
each bellcrank using liquid penetrant; in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-27-111,
dated June 15, 2011.
(1) If no cracking is found: Before further flight, rework the
bellcrank, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
(2) If any clevis hole is greater than 0.218 inch, or if any
cracking is found: Before further flight, replace the bellcrank with
a new bellcrank, in accordance with the Accomplishment Instructions
of Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
(h) Actions for Certain Model DHC-8-400 Series Airplanes
For Model DHC-8-400, -401, and -402 airplanes that have
accumulated less than or equal to 15,000 total flight hours as of
the effective date of this AD: Within 6,000 flight hours after the
effective date of this AD, but not to exceed 15,600 total flight
hours, measure the edge-to-edge length of the clevis holes of each
bellcrank, and inspect for cracking of each bellcrank using liquid
penetrant; in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
(1) If no cracking is found, and the edge-to-edge length of all
clevis holes is less than or equal to 0.218 inch: Within 6,000
flight hours after the effective date of this AD, but not to exceed
15,600 total flight hours, rework or replace the bellcrank, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-27-55, dated June 15, 2011.
(2) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.218 inch but less than or equal to 0.248
inch: Within 6,000 flight hours after the effective date of this AD,
replace the bellcrank with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
dated June 15, 2011.
(3) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.248 inch but less than or equal to 0.278
inch: Within 1,200 flight hours after doing the measurement/
inspection required by paragraph (h) of this AD, replace the
bellcrank with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
dated June 15, 2011.
(4) If any cracking is found, or if any clevis hole edge-to-edge
length exceeds 0.278 inch: Before further flight, replace the
bellcrank
[[Page 75908]]
with a new bellcrank, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-27-55, dated June 15,
2011.
(i) Actions for Certain Other Model DHC-8-400 Series Airplanes
For Model DHC-8-400, -401, and -402 airplanes that have
accumulated more than 15,000 total flight hours as of the effective
date of this AD: Within 600 flight hours after the effective date of
this AD, measure the edge-to-edge length of the clevis holes of each
bellcrank, and inspect for cracking of each bellcrank using liquid
penetrant; in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
(1) If no cracking is found, and the edge-to-edge length of all
clevis holes is less than or equal to 0.218 inch: At the later of
the compliance times specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD, rework or replace the bellcrank, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-27-55, dated June 15, 2011.
(i) Within 6,000 flight hours after the effective date of this
AD, but not to exceed 15,600 total flight hours.
(ii) Within 1,200 flight hours after the effective date of this
AD.
(2) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.218 inch but less than or equal to 0.248
inch: Within 6,000 flight hours after the effective date of this AD,
replace the bellcrank with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
dated June 15, 2011.
(3) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.248 inch but less than or equal to 0.278
inch: Within 1,200 flight hours after the effective date of this AD,
replace the bellcrank with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
dated June 15, 2011.
(4) If any cracking is found, or any clevis hole edge-to-edge
length exceeds 0.278 inch: Before further flight, replace the
bellcrank with a new bellcrank, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
dated June 15, 2011.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the ACO, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, New York 11590; telephone (516) 228-7300; fax (516)
794-5531. Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(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.
(k) Related Information
(1) Refer to MCAI Canadian Airworthiness Directive CF-2011-32,
dated August 15, 2011, and the service bulletins specified in
paragraphs (k)(1) (i) and (k)(1)(ii) of this AD, for related
information.
(i) Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
(ii) Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
(2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-30925 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P
