Airworthiness Directives; Bombardier, Inc. Airplanes, 5902-5905 [2015-01187]
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Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 airworthiness
directive (AD):
■
2015–02–15 Quest Aircraft Design, LLC:
Amendment 39–18082; Docket No.
FAA–2015–0099; Directorate Identifier
2014–CE–039–AD.
(a) Effective Date
This AD is effective February 19, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Quest Aircraft Design,
LLC Model KODIAK 100 airplanes, all serial
numbers, that are:
(1) Equipped with elevators with serial
numbers 0001 through 0149; and
(2) certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 5522; Elevator Skins.
(e) Unsafe Condition
This AD was prompted by a report that
fatigue cracks were found in the lower
elevator skins. We are issuing this AD to
correct the unsafe condition on these
products.
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(f) Compliance
Comply with this AD within the
compliance times specified in paragraphs (g)
through (j) of this AD, unless already done.
(g) Inspect the Elevator Skins for Cracking
At or before reaching 1,500 hours time in
service (TIS) on the elevator or within the
next 25 hours TIS after February 19, 2015
(the effective date of this AD), whichever
occurs later, inspect the top and bottom of
the elevator for cracking in the forward
inboard end of the trailing edge skin, aft of
the spar. Do the inspection following section
4. of Quest Aircraft Field Service Instruction,
Elevator Doubler Installation, Elevator Serial
Numbers 0001 through 0149, Report No. FSI–
106, Revision 02, not dated, as specified in
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20:27 Feb 03, 2015
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Quest Aircraft KODIAK Mandatory Service
Bulletin SB 14–09, Revision 1, dated
December 11, 2014.
Note 1 to paragraph (g) of this AD: Quest
Aircraft Field Service Instruction, Elevator
Doubler Installation, Elevator Serial Numbers
0001 through 0149, Report No. FSI–106,
Revision 02, not dated, references Advisory
Circular 43.13–1B, Section 2. The reference
should state Advisory Circular 43.13–1B,
chapter 5, section 2. You may find Advisory
Circular 43.13–1B on the Internet at https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgAdvisoryCircular.nsf/0/99C827
DB9BAAC81B86256B4500596C4E?Open
Document&Highlight=43.13-1b.
(h) Install Doublers
If no cracking was found during the
inspection required in paragraph (g) of this
AD, before further flight after the inspection,
install doublers. Do the installation following
section 5.1 of Quest Aircraft Field Service
Instruction, Elevator Doubler Installation,
Elevator Serial Numbers 0001 through 0149,
Report No. FSI–106, Revision 02, not dated,
as specified in Quest Aircraft KODIAK
Mandatory Service Bulletin SB 14–09,
Revision 1, dated December 11, 2014.
(i) Repair Cracked Elevator Skins and Install
Doublers
If cracking was found during the
inspection required in paragraph (g) of this
AD, before further flight after the inspection,
repair the cracks and install doublers, except
as specified in paragraph (j). Do the repair
and installation following section 5.2 of
Quest Aircraft Field Service Instruction,
Elevator Doubler Installation, Elevator Serial
Numbers 0001 through 0149, Report No. FSI–
106, Revision 02, not dated, as specified in
Quest Aircraft KODIAK Mandatory Service
Bulletin SB 14–09, Revision 1, dated
December 11, 2014.
(j) Cracked Elevator Skins That Exceed
Service Bulletin Repair Limits
If the cracking found during the inspection
required in paragraph (g) of this AD exceeds
the repair specified in paragraph (i) of this
AD, before further flight, obtain an FAAapproved repair method from Quest Aircraft
by contacting the Manager, Seattle Aircraft
Certification Office (ACO), FAA, as specified
in paragraph (k) of this AD. To use a repair
method approved by the Manager of the
Seattle ACO, the approval letter must
specifically reference this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (m) of this AD.
(2) 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.
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(l) Related Information
For more information about this AD,
contact Jason Deutschman, Aerospace
Engineer, Seattle Aircraft Certification Office,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057; phone: (425) 917–6595;
fax: (425) 917–6590; email:
jason.deutschman@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Quest Aircraft KODIAK Mandatory
Service Bulletin SB 14–09, Revision 1, dated
December 11, 2014.
(ii) Quest Aircraft Field Service
Instruction, Elevator Doubler Installation,
Elevator Serial Numbers 0001 through 0149,
Report No. FSI–106, Revision 02, not dated.
(3) For Quest Aircraft service information
identified in this AD, contact Quest Aircraft
Design, LLC, 1200 Turbine Drive, Sandpoint,
Idaho 83864; telephone: (208) 263–1111; toll
free: (866) 263–1112; fax: (208) 263–1511;
CustomerService@QuestAircraft.com;
www.questaircraft.com.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on January
16, 2015.
Kelly A. Broadway,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–01196 Filed 2–3–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0446; Directorate
Identifier 2013–NM–077–AD; Amendment
39–18069; AD 2015–02–02]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
SUMMARY:
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Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations
Bombardier, Inc. Model CL–215–6B11
(CL–215T Variant), and CL–215–6B11
(CL–415 Variant) airplanes. This AD
was prompted by a report that, during
a routine inspection, corrosion was
discovered on the lower bearing of the
rudder upper torque tube. This AD
requires applying grease to the bearing;
doing a general visual inspection of the
expelled old grease for any
contaminants, metal wear, and
indication of corrosion, and replacing
the bearing if necessary; and revising
the maintenance or inspection program,
as applicable, to incorporate the rudder
spring tab operational test and a check
of the rudder spring tab operation into
the daily inspection. We are issuing this
AD to prevent corroded bearings, which
could result in a partial or total loss of
axial support.
DATES: This AD becomes effective
March 11, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 11, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://www.
regulations.gov/#!docketDetail;D=FAA2014-0446 or in person at the Docket
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC.
For service information identified in
this AD, contact Bombardier, Inc., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec
H4S 1Y9, Canada; telephone 514–855–
5000; fax 514–855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com. You may view
this 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.
FOR FURTHER INFORMATION CONTACT:
Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE 171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7331; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc. Model
CL–215–6B11 (CL–215T Variant), and
CL–215–6B11 (CL–415 Variant)
airplanes. The NPRM published in the
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20:27 Feb 03, 2015
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Federal Register on July 15, 2014 (79 FR
41145).
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–08,
dated March 12, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model CL–
215–6B11 (CL–215T Variant), and CL–
215–6B11 (CL–415 Variant) airplanes.
The MCAI states:
During a routine inspection, corrosion was
discovered on the Rudder Upper Torque
Tube Lower bearing, part number (P/N)
DAT48–64A. Corroded bearings may
eventually result in a partial or total loss of
axial support.
As such, Bombardier has issued Service
Bulletin (SB) 215–A3171 Rev. 1 and SB 215–
A4452 Rev. 1, which provide instructions to
refresh the lubrication in the bearing in order
to inspect for corrosion and/or contaminants
in the existing grease. These SBs will also
incorporate an operational check to the 50
hour maintenance scheduled tasks, and a test
of the Rudder Spring Tab operation into the
Daily inspection or the aircrew Preflight
Check.
Required actions include applying
grease to the bearing, doing a general
visual inspection of the expelled old
grease for any contaminants, metal
wear, and indication of corrosion, and
replacing the bearing if necessary;
revising the maintenance or inspection
program, as applicable, to incorporate
the rudder spring tab operational test;
and revising the maintenance or
inspection program, as applicable, to
incorporate a check of the rudder spring
tab operation into the daily inspection.
You may examine the MCAI in the AD
docket on the Internet at https://www.
regulations.gov/#!documentDetail;D=
FAA-2014-0446-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 41145, July 15, 2014) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
41145, July 15, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
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5903
proposed in the NPRM (79 FR 41145,
July 15, 2014).
Related Service Information
Bombardier, Inc. has issued
Bombardier Alert Service Bulletin 215–
A3171, Revision 1, dated January 25,
2012, and Bombardier Alert Service
Bulletin 215–A4452, Revision 1, dated
January 3, 2012. This service
information describes applying grease to
the bearing; doing a general visual
inspection of the expelled old grease for
any contaminants, metal wear, and
indication of corrosion, and replacing
the bearing if necessary; and revising
the maintenance or inspection program,
as applicable, to incorporate the rudder
spring tab operational test and a check
of the rudder spring tab operation into
the daily inspection. You can find this
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0446.
Costs of Compliance
We estimate that this AD affects 5
airplanes of U.S. registry.
We also estimate that it will take
about 2 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will be
negligible. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $850, or $170 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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.
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Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
gov/#!docketDetail;D=FAA-2014-0446;
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
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 airworthiness
directive (AD):
tkelley on DSK3SPTVN1PROD with RULES
■
2015–02–02 Bombardier, Inc.: Amendment
39–18069. Docket No. FAA–2014–0446;
Directorate Identifier 2013–NM–077–AD.
(a) Effective Date
This AD becomes effective March 11, 2015.
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Jkt 235001
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc.
airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model CL–215–6B11 (CL–215T Variant)
airplanes, serial numbers 1056 through 1125
inclusive.
(2) Model CL–215–6B11 (CL–415 Variant)
airplanes, serial numbers 2001 through 2990
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by a report that,
during a routine inspection, corrosion was
discovered on the lower bearing of the rudder
upper torque tube. We are issuing this AD to
prevent corroded bearings, which could
result in a partial or total loss of axial
support.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Lubrication of the Rudder Upper Torque
Tube Bearing
Within 3 months after the effective date of
this AD, apply grease to the bearing, and do
a general visual inspection of the expelled
old grease for any contaminants (i.e. ashes,
dust, and algae), metal wear, and indication
of corrosion, in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A3171, Revision
1, dated January 25, 2012 (for Model CL–
215–6B11 (CL–215T Variant) airplanes); or
Bombardier Alert Service Bulletin 215–
A4452, Revision 1, dated January 3, 2012 (for
Model CL–215–6B11 (CL–415 Variant)
airplanes). If any contaminants (i.e., ashes,
dust, and algae), metal wear, or indication of
corrosion are found, before further flight,
replace the bearing with a new bearing, in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3171, Revision 1, dated
January 25, 2012 (for Model CL–215–6B11
(CL–215T Variant) airplanes); or Bombardier
Alert Service Bulletin 215–A4452, Revision
1, dated January 3, 2012 (for Model CL–215–
6B11 (CL–415 Variant) airplanes). Repeat the
inspection, thereafter, before and after each
fire season or at intervals not to exceed 6
months, whichever occurs first.
Note 1 to paragraph (g) of this AD: It is
suggested that paragraph (g) of this AD be
carried out in conjunction with AD 2009–05–
04, Amendment 39–15828 (74 FR 8860,
February 27, 2009), as the task and task
intervals are in the same general area.
(h) Operational Test
Within 30 days after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, to
incorporate the rudder spring tab operational
test, in accordance with the Accomplishment
Instructions of Bombardier Alert Service
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Bulletin 215–A3171, Revision 1, dated
January 25, 2012 (for Model CL–215–6B11
(CL–215T Variant) airplanes); or Bombardier
Alert Service Bulletin 215–A4452, Revision
1, dated January 3, 2012 (for Model CL–215–
6B11 (CL–415 Variant) airplanes).
(i) Daily Maintenance Procedure Check
Within 30 days after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, to
incorporate a check of the rudder spring tab
operation into the daily inspection, in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3171, Revision 1, dated
January 25, 2012 (for Model CL–215–6B11
(CL–215T Variant) airplanes); or Bombardier
Alert Service Bulletin 215–A4452, Revision
1, dated January 3, 2012 (for Model CL–215–
6B11 (CL–415 Variant) airplanes).
(j) No Alternative Actions and Intervals
After accomplishment of the maintenance
or inspection program revision required by
paragraphs (h) and (i) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (k)(1) of this AD.
(k) 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, NY 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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–08, dated
March 12, 2013, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/#
!documentDetail;D=FAA-2014-0446-0002.
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Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Alert Service Bulletin 215–
A3171, Revision 1, dated January 25, 2012.
(ii) Bombardier Alert Service Bulletin 215–
A4452, Revision 1, dated January 3, 2012.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January
12, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–01187 Filed 2–3–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0540; Directorate
Identifier 2014–NE–10–AD; Amendment 39–
18074; AD 2015–02–07]
RIN 2120–AA64
Airworthiness Directives; Lycoming
Engines Reciprocating Engines (Type
Certificate previously held by Textron
Lycoming Division, AVCO Corporation)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
serial number (S/N) Lycoming Engines
reciprocating engines. This AD was
prompted by propeller governor shaft
set screws coming loose due to
improper installation. We are issuing
this AD to prevent the propeller
governor shaft set screw from coming
loose, causing damage to the engine and
damage to the airplane.
tkelley on DSK3SPTVN1PROD with RULES
SUMMARY:
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5905
This AD is effective March 11,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 11, 2015.
ADDRESSES: For service information
identified in this AD, contact Lycoming
Engines, 652 Oliver Street,
Williamsport, PA 17701; phone: 800–
258–3279; fax: 570–327–7101; Internet:
www.lycoming.com/Lycoming/
SUPPORT/TechnicalPublications/
ServiceBulletins.aspx. You may view
this service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington,
MA. For information on the availability
of this material at the FAA, call 781–
238–7125.
each installation of the set screw in
addition to the peening of crankcase
hole threads. We are issuing this AD to
prevent the propeller governor shaft set
screw from coming loose, causing
damage to the engine and damage to the
airplane.
Examining the AD Docket
Conclusion
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0540; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Norm Perenson, Aerospace Engineer,
New York Aircraft Certification Office,
FAA, Engine & Propeller Directorate,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: 516–228–
7337; fax: 516–794–5531; email:
norman.perenson@faa.gov.
SUPPLEMENTARY INFORMATION:
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed.
DATES:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain S/N Lycoming Engines
reciprocating engines. The NPRM
published in the Federal Register on
September 11, 2014 (79 FR 54218). The
NPRM was prompted by events of
propeller governor shaft set screws
coming loose due to improper
installation. If the set screws come
loose, the engine may lose oil resulting
in damage to the engine and damage to
the airplane. The NPRM proposed to
require application of Loctite 290, or
equivalent, to the threads of the
propeller governor shaft set screw at
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 54218, September 11, 2014) or on the
determination of the cost to the public.
We did however; find that we
directed the use of LocTite 290, a
commercial product by brand name. We
changed the AD to remove the
requirement to use any particular brand
like LocTite 290, from this AD.
Related Service Information
We reviewed Lycoming Engines
Service Instruction No. 1343B, dated
June 15, 2007. The service instruction
describes procedures for application of
sealant for the propeller governor shaft
set screw and the peening of crankcase
hole threads. You can find this
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0540.
Costs of Compliance
We estimate that this AD will affect
about 2,330 engines installed on
airplanes of U.S. registry. We also
estimate that it will take about 0.1 hours
per engine to comply with this AD. The
average labor rate is $85 per hour.
Prorated parts life will cost about $1 per
engine. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $22,135.
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
E:\FR\FM\04FER1.SGM
04FER1
]]>Agencies
[Federal Register Volume 80, Number 23 (Wednesday, February 4, 2015)]
[Rules and Regulations]
[Pages 5902-5905]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01187]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0446; Directorate Identifier 2013-NM-077-AD;
Amendment 39-18069; AD 2015-02-02]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
[[Page 5903]]
Bombardier, Inc. Model CL-215-6B11 (CL-215T Variant), and CL-215-6B11
(CL-415 Variant) airplanes. This AD was prompted by a report that,
during a routine inspection, corrosion was discovered on the lower
bearing of the rudder upper torque tube. This AD requires applying
grease to the bearing; doing a general visual inspection of the
expelled old grease for any contaminants, metal wear, and indication of
corrosion, and replacing the bearing if necessary; and revising the
maintenance or inspection program, as applicable, to incorporate the
rudder spring tab operational test and a check of the rudder spring tab
operation into the daily inspection. We are issuing this AD to prevent
corroded bearings, which could result in a partial or total loss of
axial support.
DATES: This AD becomes effective March 11, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 11,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0446 or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Bombardier,
Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9,
Canada; telephone 514-855-5000; fax 514-855-7401; email
thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You
may view this 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.
FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE 171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7331; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Bombardier, Inc.
Model CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant)
airplanes. The NPRM published in the Federal Register on July 15, 2014
(79 FR 41145).
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-08, dated March 12, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Bombardier, Inc. Model CL-215-6B11 (CL-
215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. The MCAI
states:
During a routine inspection, corrosion was discovered on the
Rudder Upper Torque Tube Lower bearing, part number (P/N) DAT48-64A.
Corroded bearings may eventually result in a partial or total loss
of axial support.
As such, Bombardier has issued Service Bulletin (SB) 215-A3171
Rev. 1 and SB 215-A4452 Rev. 1, which provide instructions to
refresh the lubrication in the bearing in order to inspect for
corrosion and/or contaminants in the existing grease. These SBs will
also incorporate an operational check to the 50 hour maintenance
scheduled tasks, and a test of the Rudder Spring Tab operation into
the Daily inspection or the aircrew Preflight Check.
Required actions include applying grease to the bearing, doing a
general visual inspection of the expelled old grease for any
contaminants, metal wear, and indication of corrosion, and replacing
the bearing if necessary; revising the maintenance or inspection
program, as applicable, to incorporate the rudder spring tab
operational test; and revising the maintenance or inspection program,
as applicable, to incorporate a check of the rudder spring tab
operation into the daily inspection. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0446-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 41145, July 15,
2014) or on the determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed, except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 41145, July 15, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 41145, July 15, 2014).
Related Service Information
Bombardier, Inc. has issued Bombardier Alert Service Bulletin 215-
A3171, Revision 1, dated January 25, 2012, and Bombardier Alert Service
Bulletin 215-A4452, Revision 1, dated January 3, 2012. This service
information describes applying grease to the bearing; doing a general
visual inspection of the expelled old grease for any contaminants,
metal wear, and indication of corrosion, and replacing the bearing if
necessary; and revising the maintenance or inspection program, as
applicable, to incorporate the rudder spring tab operational test and a
check of the rudder spring tab operation into the daily inspection. You
can find this information at https://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0446.
Costs of Compliance
We estimate that this AD affects 5 airplanes of U.S. registry.
We also estimate that it will take about 2 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will be negligible. Based on
these figures, we estimate the cost of this AD on U.S. operators to be
$850, or $170 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
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.
[[Page 5904]]
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0446; 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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2015-02-02 Bombardier, Inc.: Amendment 39-18069. Docket No. FAA-
2014-0446; Directorate Identifier 2013-NM-077-AD.
(a) Effective Date
This AD becomes effective March 11, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc. airplanes, certificated
in any category, identified in paragraphs (c)(1) and (c)(2) of this
AD.
(1) Model CL-215-6B11 (CL-215T Variant) airplanes, serial
numbers 1056 through 1125 inclusive.
(2) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers
2001 through 2990 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a report that, during a routine
inspection, corrosion was discovered on the lower bearing of the
rudder upper torque tube. We are issuing this AD to prevent corroded
bearings, which could result in a partial or total loss of axial
support.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Lubrication of the Rudder Upper Torque Tube Bearing
Within 3 months after the effective date of this AD, apply
grease to the bearing, and do a general visual inspection of the
expelled old grease for any contaminants (i.e. ashes, dust, and
algae), metal wear, and indication of corrosion, in accordance with
the Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3171, Revision 1, dated January 25, 2012 (for Model CL-215-6B11
(CL-215T Variant) airplanes); or Bombardier Alert Service Bulletin
215-A4452, Revision 1, dated January 3, 2012 (for Model CL-215-6B11
(CL-415 Variant) airplanes). If any contaminants (i.e., ashes, dust,
and algae), metal wear, or indication of corrosion are found, before
further flight, replace the bearing with a new bearing, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin 215-A3171, Revision 1, dated January 25, 2012 (for
Model CL-215-6B11 (CL-215T Variant) airplanes); or Bombardier Alert
Service Bulletin 215-A4452, Revision 1, dated January 3, 2012 (for
Model CL-215-6B11 (CL-415 Variant) airplanes). Repeat the
inspection, thereafter, before and after each fire season or at
intervals not to exceed 6 months, whichever occurs first.
Note 1 to paragraph (g) of this AD: It is suggested that
paragraph (g) of this AD be carried out in conjunction with AD 2009-
05-04, Amendment 39-15828 (74 FR 8860, February 27, 2009), as the
task and task intervals are in the same general area.
(h) Operational Test
Within 30 days after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, to incorporate the
rudder spring tab operational test, in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3171, Revision 1, dated January 25, 2012 (for Model CL-215-6B11
(CL-215T Variant) airplanes); or Bombardier Alert Service Bulletin
215-A4452, Revision 1, dated January 3, 2012 (for Model CL-215-6B11
(CL-415 Variant) airplanes).
(i) Daily Maintenance Procedure Check
Within 30 days after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, to incorporate a
check of the rudder spring tab operation into the daily inspection,
in accordance with the Accomplishment Instructions of Bombardier
Alert Service Bulletin 215-A3171, Revision 1, dated January 25, 2012
(for Model CL-215-6B11 (CL-215T Variant) airplanes); or Bombardier
Alert Service Bulletin 215-A4452, Revision 1, dated January 3, 2012
(for Model CL-215-6B11 (CL-415 Variant) airplanes).
(j) No Alternative Actions and Intervals
After accomplishment of the maintenance or inspection program
revision required by paragraphs (h) and (i) of this AD, no
alternative actions (e.g., inspections) or intervals may be used
unless the actions or intervals are approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (k)(1) of this AD.
(k) 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, NY 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, Engine and Propeller Directorate, FAA; or Transport Canada
Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must
include the DAO-authorized signature.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2013-08, dated March 12, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-
2014-0446-0002.
[[Page 5905]]
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Alert Service Bulletin 215-A3171, Revision 1,
dated January 25, 2012.
(ii) Bombardier Alert Service Bulletin 215-A4452, Revision 1,
dated January 3, 2012.
(3) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(4) You may view this 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January 12, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-01187 Filed 2-3-15; 8:45 am]
BILLING CODE 4910-13-P
