Airworthiness Directives; Bombardier, Inc. Airplanes, 34874-34876 [2012-14212]
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34874
Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Fokker Services B.V.: Docket No. FAA–
2012–0593; Directorate Identifier 2011–
NM–238–AD.
(a) Comments Due Date
We must receive comments by July 27,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V.
Model F.28 Mark 0070 and 0100 airplanes;
certificated in any category; serial number (s/
n) 11340 through 11343 inclusive, 11347,
11348, 11350 through 11356 inclusive,
11359, 11360, 11361, 11367 through 11371
inclusive, 11374 through 11378 inclusive,
11382 through 11385 inclusive, 11387
through 11390 inclusive, 11394 through
11397 inclusive, 11400 through 11423
inclusive, 11425 through 11432 inclusive,
11434 through 11439 inclusive, 11441
through 11453 inclusive, and 11456 through
11585 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 24, Electrical Power.
(e) Reason
This AD was prompted by reports of
burned contacts in a certain production break
plug and its corresponding receptacle. We are
issuing this AD to prevent a high electrical
load which may lead to overheating of the
galley power supply wiring and/or the
electrical connector and consequent smoke or
fire in the galley area, which could result in
damage to the airplane and injury to
occupants.
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(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) Modification
Within 24 months after the effective date
of this AD: Modify the galley power supply
wiring, in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–24–044, dated July
14, 2011, which includes Fokker Manual
Change Notification—Maintenance
Documentation MCNM–F100–148, dated July
14, 2011.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
VerDate Mar<15>2010
16:28 Jun 11, 2012
Jkt 226001
Directorate, 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 International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
telephone (425) 227–1137; fax (425) 227–
1149. Information may be emailed to: 9–
ANM–116–AMOC–REQUESTS@faa.gov.
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.
(i) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0183, dated September 23,
2011; and Fokker Service Bulletin SBF 100–
24–044, dated July 14, 2011, which includes
Fokker Manual Change Notification—
Maintenance Documentation MCNM–F100–
148, dated July 14, 2011; for related
information.
Issued in Renton, Washington, on May 31,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–14211 Filed 6–11–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0594; Directorate
Identifier 2012–NM–019–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–8–400,
–401, and –402 airplanes. This proposed
AD was prompted by reports of
SUMMARY:
PO 00000
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Fmt 4702
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movement of the rudder pedals being
impeded due to corrosion of the
trunnion shaft of the rudder feel trim
unit (RFTU). This proposed AD would
require inspecting to determine if
certain RFTUs are installed, an
operational check for signs of seizure of
affected parts, repetitive lubrication for
certain RFTUs, and replacing the RFTU
with a new RFTU if necessary.
Installation of replaced RFTUs with
conformal bushings terminates the
repetitive lubrication requirements. We
are proposing this AD to detect and
correct any sign of seizure of the
trunnion shaft and its bushing, which
could cause a rudder control jam or a
large and rapid alternating rudder input
leading to a structural failure of the
vertical fin.
DATES: We must receive comments on
this proposed AD by July 27, 2012.
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
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12JNP1
Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, 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–
7318; 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–2012–0594; Directorate Identifier
2011–NM–019–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
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Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2012–02,
dated January 9, 2012 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
There have been several reported incidents
on DHC–8 Series 400 aeroplanes where the
movement of the rudder pedals has been
impeded. An investigation showed that the
Rudder Feel Trim Unit (RFTU) trunnion shaft
was corroded. The root cause of the corrosion
was a quality escape where cadmium plating
on the trunnion bushing within the RFTU
assembly was not removed. Corrosion on the
shaft and in the trunnion bushing seized the
trunnion and caused difficulties in
controlling the rudder movement.
This condition, if not corrected, could cause
a rudder control jam or a large and rapid
alternating rudder input leading to a
structural failure of the vertical fin.
This [TCCA] Airworthiness Directive (AD) is
issued [inspect to determine serial number,
an operational check for seizure, repetitive
lubrication and] to replace the affected
RFTUs to limit the possibility of binding and
replace the affected RFTUs with units that
have been reworked with conformal bushings
to terminate the lubrication requirements.
VerDate Mar<15>2010
16:28 Jun 11, 2012
Jkt 226001
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Bombardier, Inc. has issued Service
Bulletin 84–27–57, dated July 22, 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
affect about 83 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. 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 parts.
As we do not control warranty coverage
for affected parties, some parties may
incur costs higher than estimated here.
Based on these figures, we estimate the
cost of the proposed AD on U.S.
operators to be $35,275, or $425 per
product.
In addition, we estimate that any
necessary follow-on actions would take
about 10 work-hours and require parts
costing $0, for a cost of $850 per
product. 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:
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34875
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc.: Docket No. FAA–2012–
0594; Directorate Identifier 2012–NM–
019–AD.
E:\FR\FM\12JNP1.SGM
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34876
Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules
the replacement required by paragraph (h) is
done.
(a) Comments Due Date
We must receive comments by July 27,
2012.
(h) Replacement
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–400, –401, and –402 airplanes;
certificated in any category; serial numbers
4001, 4003 and subsequent, equipped with
rudder feel trim unit part number 399500–
1007.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(g) Inspection
Within 600 flight hours or six months after
the effective date of this AD whichever
occurs first, inspect the RTFU to determine
whether the serial number (S/N) is in the
range from 0009 through 0388 without a
suffix ‘‘A,’’ in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–57, dated July 22,
2011. A review of airplane maintenance
records is acceptable in lieu of this
inspection if the serial number of the RFTU
can be conclusively determined from that
review.
(1) If the RFTU’s serial number is not in
the range from 0009 through 0388 or if the
serial number has a suffix ‘‘A,’’ no further
action is required for this paragraph.
(2) If the RFTU’s serial number is in the
range from 0009 through 0388 without a
suffix ‘‘A,’’ before further flight, perform an
operational check of the RFTU for any sign
of seizure of the trunnion and its bushing, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–57, dated July 22, 2011.
(i) If a seizure of the RFTU trunnion and
its bushings is found: Before further flight,
replace the RFTU with a new RFTU, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–57, dated July 22, 2011.
(ii) If no seizure of the RFTU trunnion and
its bushings is found: Before further flight,
lubricate the RFTU, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–57, dated July 22,
2011. Repeat the lubrication of the RFTU at
intervals not to exceed 600 flight hours until
14 CFR Part 39
[Docket No. FAA–2012–0595; Directorate
Identifier 2012–NM–055–AD]
(j) Other FAA AD Provisions
(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.
Jkt 226001
BILLING CODE 4910–13–P
As of the effective date of this AD, no
person may install a RFTU P/N 399500–1007
with a serial number from 0009 through 0388
without a suffix ‘‘A’’ on any airplane.
(e) Reason
This AD was prompted by reports of
movement of the rudder pedals being
impeded due to corrosion of the trunnion
shaft of the rudder feel trim unit (RFTU).
We are issuing this AD to detect and
correct any sign of seizure of the trunnion
shaft and its bushing, which could cause a
rudder control jam or a large and rapid
alternating rudder input leading to a
structural failure of the vertical fin.
16:28 Jun 11, 2012
[FR Doc. 2012–14212 Filed 6–11–12; 8:45 am]
(i) Parts Installation
(d) Subject
Air Transport Association (ATA) of
America Code 27: Flight Controls.
VerDate Mar<15>2010
For airplanes identified in paragraph (g)(2)
of this AD: Within 6,000 flight hours after the
effective date of this AD, replace all affected
RFTUs with units that have a serial number
outside the range from 0009 through 0388 or
that have a serial number with a suffix ‘‘A,’’
in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–57, dated July 22, 2011.
Issued in Renton, Washington, on May 31,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Airworthiness Directives; The Boeing
Company
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–2012–02, dated January 9, 2012;
and Bombardier Service Bulletin 84–27–57,
dated July 22, 2011; for related information.
(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,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
PO 00000
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RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 777
airplanes. This proposed AD was
prompted by reports of failure of wire
support clamps in the forward section of
the aft pressure bulkhead. This
proposed AD would require a detailed
inspection of the clamps on the power
feeder cable auxiliary power unit (APU)
to determine if certain clamps are
installed, and related investigative and
corrective actions if necessary. We are
proposing this AD to prevent failure of
the clamp, which could result in wire
chafing and potential arcing and
consequent fire in section 48 (a
flammable fluid leakage zone) or heat
damage to the APU power feeder cable,
insulation blankets, or pressure
bulkhead.
SUMMARY:
We must receive comments on
this proposed AD by July 27, 2012.
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 service information identified in
this proposed AD, contact Boeing
DATES:
E:\FR\FM\12JNP1.SGM
12JNP1
]]>Agencies
[Federal Register Volume 77, Number 113 (Tuesday, June 12, 2012)]
[Proposed Rules]
[Pages 34874-34876]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14212]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0594; Directorate Identifier 2012-NM-019-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-8-400, -401, and -402 airplanes.
This proposed AD was prompted by reports of movement of the rudder
pedals being impeded due to corrosion of the trunnion shaft of the
rudder feel trim unit (RFTU). This proposed AD would require inspecting
to determine if certain RFTUs are installed, an operational check for
signs of seizure of affected parts, repetitive lubrication for certain
RFTUs, and replacing the RFTU with a new RFTU if necessary.
Installation of replaced RFTUs with conformal bushings terminates the
repetitive lubrication requirements. We are proposing this AD to detect
and correct any sign of seizure of the trunnion shaft and its bushing,
which could cause a rudder control jam or a large and rapid alternating
rudder input leading to a structural failure of the vertical fin.
DATES: We must receive comments on this proposed AD by July 27, 2012.
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
[[Page 34875]]
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, 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) 228-7318; 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-2012-0594;
Directorate Identifier 2011-NM-019-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 Airworthiness Directive CF-
2012-02, dated January 9, 2012 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
There have been several reported incidents on DHC-8 Series 400
aeroplanes where the movement of the rudder pedals has been impeded.
An investigation showed that the Rudder Feel Trim Unit (RFTU)
trunnion shaft was corroded. The root cause of the corrosion was a
quality escape where cadmium plating on the trunnion bushing within
the RFTU assembly was not removed. Corrosion on the shaft and in the
trunnion bushing seized the trunnion and caused difficulties in
controlling the rudder movement.
This condition, if not corrected, could cause a rudder control jam
or a large and rapid alternating rudder input leading to a
structural failure of the vertical fin.
This [TCCA] Airworthiness Directive (AD) is issued [inspect to
determine serial number, an operational check for seizure,
repetitive lubrication and] to replace the affected RFTUs to limit
the possibility of binding and replace the affected RFTUs with units
that have been reworked with conformal bushings to terminate the
lubrication requirements.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier, Inc. has issued Service Bulletin 84-27-57, dated July
22, 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 affect about 83 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. 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 parts.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $35,275, or $425 per product.
In addition, we estimate that any necessary follow-on actions would
take about 10 work-hours and require parts costing $0, for a cost of
$850 per product. 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-2012-0594; Directorate Identifier
2012-NM-019-AD.
[[Page 34876]]
(a) Comments Due Date
We must receive comments by July 27, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes; certificated in any category; serial numbers 4001,
4003 and subsequent, equipped with rudder feel trim unit part number
399500-1007.
(d) Subject
Air Transport Association (ATA) of America Code 27: Flight
Controls.
(e) Reason
This AD was prompted by reports of movement of the rudder pedals
being impeded due to corrosion of the trunnion shaft of the rudder
feel trim unit (RFTU).
We are issuing this AD to detect and correct any sign of seizure
of the trunnion shaft and its bushing, which could cause a rudder
control jam or a large and rapid alternating rudder input leading to
a structural failure of the vertical fin.
(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) Inspection
Within 600 flight hours or six months after the effective date
of this AD whichever occurs first, inspect the RTFU to determine
whether the serial number (S/N) is in the range from 0009 through
0388 without a suffix ``A,'' in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-27-57, dated July 22,
2011. A review of airplane maintenance records is acceptable in lieu
of this inspection if the serial number of the RFTU can be
conclusively determined from that review.
(1) If the RFTU's serial number is not in the range from 0009
through 0388 or if the serial number has a suffix ``A,'' no further
action is required for this paragraph.
(2) If the RFTU's serial number is in the range from 0009
through 0388 without a suffix ``A,'' before further flight, perform
an operational check of the RFTU for any sign of seizure of the
trunnion and its bushing, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-27-57, dated July 22,
2011.
(i) If a seizure of the RFTU trunnion and its bushings is found:
Before further flight, replace the RFTU with a new RFTU, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-27-57, dated July 22, 2011.
(ii) If no seizure of the RFTU trunnion and its bushings is
found: Before further flight, lubricate the RFTU, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 84-
27-57, dated July 22, 2011. Repeat the lubrication of the RFTU at
intervals not to exceed 600 flight hours until the replacement
required by paragraph (h) is done.
(h) Replacement
For airplanes identified in paragraph (g)(2) of this AD: Within
6,000 flight hours after the effective date of this AD, replace all
affected RFTUs with units that have a serial number outside the
range from 0009 through 0388 or that have a serial number with a
suffix ``A,'' in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-57, dated July 22, 2011.
(i) Parts Installation
As of the effective date of this AD, no person may install a
RFTU P/N 399500-1007 with a serial number from 0009 through 0388
without a suffix ``A'' on any airplane.
(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-2012-02,
dated January 9, 2012; and Bombardier Service Bulletin 84-27-57,
dated July 22, 2011; for related information.
(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, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 31, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-14212 Filed 6-11-12; 8:45 am]
BILLING CODE 4910-13-P
