Special Conditions: Pratt and Whitney Canada Model PW210S Turboshaft Engine, 8321-8322 [2011-3068]
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Federal Register / Vol. 76, No. 30 / Monday, February 14, 2011 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
Federal Aviation Administration
The Proposed Special Conditions
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for the GVI
airplanes.
In lieu of compliance with § 25.349(a),
Gulfstream must comply with the
following special conditions.
The following conditions, speeds, and
cockpit roll control motions (except as
the motions may be limited by pilot
effort) must be considered in
combination with an airplane load
factor of zero and of two-thirds of the
positive maneuvering factor used in
design. In determining the resulting
control surface deflections, the torsional
flexibility of the wing must be
considered in accordance with
§ 25.301(b):
1. Conditions corresponding to steady
rolling velocities must be investigated.
In addition, conditions corresponding to
maximum angular acceleration must be
investigated for airplanes with engines
or other weight concentrations outboard
of the fuselage. For the angular
acceleration conditions, zero rolling
velocity may be assumed in the absence
of a rational time history investigation
of the maneuver.
2. At VA, sudden movement of the
cockpit roll control up to the limit is
assumed. The position of the cockpit
roll control must be maintained until a
steady roll rate is achieved and then
must be returned suddenly to the
neutral position.
3. At VC, the cockpit roll control must
be moved suddenly and maintained so
as to achieve a roll rate not less than
that obtained in paragraph 2.
4. At VD, the cockpit roll control must
be moved suddenly and maintained so
as to achieve a roll rate not less than one
third of that obtained in paragraph 2.
Issued in Renton, Washington, on February
3, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–3216 Filed 2–11–11; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
14:09 Feb 11, 2011
Jkt 223001
DEPARTMENT OF TRANSPORTATION
14 CFR Part 33
[Docket No. NE130; Notice No. 33–10–01–
SC]
Special Conditions: Pratt and Whitney
Canada Model PW210S Turboshaft
Engine
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
This action proposes special
conditions for the Pratt and Whitney
Canada (PWC) model PW210S
turboshaft engine. This engine model
will have a novel or unusual design
feature associated with engine operation
in auxiliary power unit (APU) mode.
The applicable airworthiness
regulations do not contain adequate or
appropriate safety standards for this
design feature. These proposed special
conditions contain the added safety
standards that the Administrator
considers necessary to establish a level
of safety equivalent to that established
by the existing airworthiness standards.
DATES: We must receive your comments
by March 16, 2011.
ADDRESSES: You must mail two copies
of your comments to: Federal Aviation
Administration, Engine and Propeller
Directorate, Attn: Marc Bouthillier,
Rules Docket (ANE–111), Docket No.
NE130, 12 New England Executive Park,
Burlington, Massachusetts 01803–5299.
You may deliver two copies to the
Engine and Propeller Directorate at the
above address. You must mark your
comments: Docket No. NE130. You can
inspect comments in the Rules Docket
weekdays, except Federal holidays,
between 7:30 am. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: For
technical questions concerning this
proposed rule contact Marc Bouthillier,
ANE–111, Engine and Propeller
Directorate, Aircraft Certification
Service, 12 New England Executive
Park, Burlington, Massachusetts 01803–
5299, telephone (781) 238–7120;
facsimile (781) 238–7199; e-mail
marc.bouthillier@faa.gov. For legal
questions concerning this proposed rule
contact Vincent Bennett, ANE–7 Engine
and Propeller Directorate, Aircraft
Certification Service, 12 New England
Executive Park, Burlington,
Massachusetts 01803–5299; telephone
(781) 238–7044; facsimile (781) 238–
7055; e-mail vincent.bennett@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
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Fmt 4702
Sfmt 4702
8321
Comments Invited
We invite interested people to take
part in this rulemaking by sending
written comments, data, or views. The
most helpful comments reference a
specific portion of the special
conditions, explain the reason for any
recommended change, and include
supporting data. We ask that you send
us two copies of written comments.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
about these special conditions. You can
inspect the docket before and after the
comment closing date. If you wish to
review the docket in person, go to the
address in the ADDRESSES section of this
preamble between 9 am. and 5 p.m.,
Monday through Friday, except Federal
holidays.
We will consider all comments we
receive by the closing date for
comments. We will consider comments
filed late if it is possible to do so
without incurring expense or delay. We
may change these special conditions
based on the comments we receive.
If you want us to let you know we
received your comments on this
proposal, send us a pre-addressed,
stamped postcard on which the docket
number appears. We will stamp the date
on the postcard and mail it back to you.
Background
On December 5, 2005, PWC applied
for a type certificate for the model
PW210S turboshaft engine. The engine
is a free turbine turboshaft designed for
a transport category helicopter. This
engine incorporates a two stage
compressor driven by a single stage
turbine and a two stage free power
turbine driving a two stage reduction
gearbox and main output shaft. The
control system includes a dual channel
digital electronic control. The engine
will incorporate a novel or unusual
design feature associated with engine
operation in auxiliary power unit (APU)
mode. The helicopter will incorporate a
main rotor brake what will allow the
engine main output shaft and power
turbine to be brought to a stop and to
remain stationary, while the gas
generator portion of the engine
continues to operate as an APU while
on the ground.
The applicable airworthiness
standards do not contain adequate or
appropriate airworthiness standards to
address this design feature.
These special conditions contain the
additional airworthiness standards
necessary to establish a level of safety
equivalent to the level that would result
E:\FR\FM\14FEP1.SGM
14FEP1
8322
Federal Register / Vol. 76, No. 30 / Monday, February 14, 2011 / Proposed Rules
from compliance with the applicable
standards of airworthiness in effect on
the date of application.
Type Certification Basis
Under the provisions of 14 CFR 21.17,
PWC must show that the model PW210S
turboshaft engine meets the provisions
of the applicable regulations in effect on
the date of application. The application
date is December 5, 2005, which
corresponds to 14 CFR part 33
Amendment 20. However, PWC has
elected to demonstrate compliance to
later amendments of part 33 for this
model. Therefore, the certification basis
for the PW210S model turboshaft engine
will be part 33, effective February 1,
1965, as amended by Amendments 33–
1 through 33–24.
If the Administrator finds that the
applicable airworthiness regulations in
part 33, as amended, do not contain
adequate or appropriate safety standards
for the PWC model PW210S turboshaft
engine, because of a novel or unusual
design feature, special conditions are
prescribed under the provisions of
§ 21.16.
The FAA issues special conditions, as
defined by 14 CFR 11.19, in accordance
with 14 CFR 11.38, which become part
of the type certification basis in
accordance with § 21.17(b)(2).
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
include another related model that
incorporates the same or similar novel
or unusual design feature, or should any
other model already included on the
same type certificate be modified to
incorporate the same or similar novel or
unusual design feature, the special
conditions would also apply to the other
model.
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Novel or Unusual Design Features
The Pratt and Whitney Canada (PWC)
model PW210S turboshaft engine will
incorporate a novel or unusual design
feature associated with engine operation
in auxiliary power unit (APU) mode.
Special conditions for APU mode are
proposed to address the novel and
unusual design feature. The special
conditions are discussed below.
Discussion
The proposed special conditions are
similar to those requirements that
currently exist in 14 CFR part 33,
§ 33.96 Engine Tests in Auxiliary Power
Unit (APU) Mode. However the current
rule only applies to turboprop type
engines, therefore special conditions are
needed to apply appropriate
requirements to turboshaft type engines.
VerDate Mar<15>2010
14:09 Feb 11, 2011
Jkt 223001
Also, the type certification
considerations for function and
reliability are common between these
two engine types in this regard, making
requirements similar to current § 33.96
generally applicable to turboshaft
engine types. Future rulemaking may
occur to expand the applicability of
§ 33.96 to include turboshaft type
engines.
Applicability
As discussed above, these special
conditions are applicable to PWC model
PW210S turboshaft engines. If Pratt and
Whitney Canada applies later for a
change to the type certificate to include
another related model incorporating the
same novel or unusual design feature,
these special conditions would apply to
that model as well.
Conclusion
This action affects only certain novel
or unusual design features on one model
of engine. It is not a rule of general
applicability, and it affects only the
applicant who applied to the FAA for
approval of these features on the engine.
List of Subjects in 14 CFR Part 33
Air transportation, Aircraft, Aviation
safety, Safety.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701–
44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for Pratt and
Whitney Canada (PWC) model PW210S
turboshaft engines.
1. PART 1 DEFINITION. Unless
otherwise approved by the
Administrator and documented in the
appropriate manuals and certification
documents, the following definition
applies to this special condition:
‘‘Auxiliary Power Unit Mode’’ Engine
operation with the main output shaft
and power turbine locked and
stationary, while the gas generator
portion of the engine continues to
operate, for the purpose of supplying
the rotorcraft with electric/hydraulic/
pneumatic power (as applicable) while
on the ground.
2. PART 33 REQUIREMENTS:
(a) Ground locking: A total of 45
hours with the engine output shaft
locked to simulate rotor brake
engagement, in a manner which clearly
demonstrates the complete engine’s
ability to function without adverse
affect while operating in the APU mode
under the maximum conditions of
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
engine rotor speed, torque, temperature,
air bleed and power extraction as
specified by the applicant.
(b) Dynamic braking: A total of 400
application-release cycles of simulated
brake engagements must be made in a
manner which clearly demonstrates the
complete engine’s ability to function
without adverse affect under the
maximum conditions of engine
acceleration and deceleration rate, rotor
speed, torque and temperature as
specified by the applicant. The engine
output shaft must be stopped prior to
brake-release.
(c) One hundred engine starts and
stops with the output shaft locked in a
manner simulating rotor brake
engagement.
(d) The tests required by paragraphs
(a), (b) and (c) of this section must be
performed on the same engine, but this
engine need not be the same engine
used for the tests required by § 33.87 of
14 CFR part 33.
(e) The tests required by paragraphs
(a), (b) and (c) of this section must be
followed by engine disassembly to the
extent necessary to show that each
engine part conforms to the type design
and is eligible for incorporation into an
engine for continued operation in
accordance with information submitted
in compliance with § 33.4, Instructions
for Continued Airworthiness.
(f) Brake engagement and release: The
effects on the engine of braking and
releasing the output shaft, including
partial or sudden events while the
engine is running, must be determined.
Issued in Burlington, Massachusetts, on
January 30, 2011.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2011–3068 Filed 2–11–11; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2010–1264; Airspace
Docket No. 10–AWP–23]
Proposed Amendment of Class D and
Class E Airspace; Livermore, CA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Class E airspace at Livermore,
CA, to accommodate aircraft using new
Instrument Landing System (ILS)
SUMMARY:
E:\FR\FM\14FEP1.SGM
14FEP1
]]>Agencies
[Federal Register Volume 76, Number 30 (Monday, February 14, 2011)]
[Proposed Rules]
[Pages 8321-8322]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-3068]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 33
[Docket No. NE130; Notice No. 33-10-01-SC]
Special Conditions: Pratt and Whitney Canada Model PW210S
Turboshaft Engine
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
-----------------------------------------------------------------------
SUMMARY: This action proposes special conditions for the Pratt and
Whitney Canada (PWC) model PW210S turboshaft engine. This engine model
will have a novel or unusual design feature associated with engine
operation in auxiliary power unit (APU) mode. The applicable
airworthiness regulations do not contain adequate or appropriate safety
standards for this design feature. These proposed special conditions
contain the added safety standards that the Administrator considers
necessary to establish a level of safety equivalent to that established
by the existing airworthiness standards.
DATES: We must receive your comments by March 16, 2011.
ADDRESSES: You must mail two copies of your comments to: Federal
Aviation Administration, Engine and Propeller Directorate, Attn: Marc
Bouthillier, Rules Docket (ANE-111), Docket No. NE130, 12 New England
Executive Park, Burlington, Massachusetts 01803-5299. You may deliver
two copies to the Engine and Propeller Directorate at the above
address. You must mark your comments: Docket No. NE130. You can inspect
comments in the Rules Docket weekdays, except Federal holidays, between
7:30 am. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: For technical questions concerning
this proposed rule contact Marc Bouthillier, ANE-111, Engine and
Propeller Directorate, Aircraft Certification Service, 12 New England
Executive Park, Burlington, Massachusetts 01803-5299, telephone (781)
238-7120; facsimile (781) 238-7199; e-mail marc.bouthillier@faa.gov.
For legal questions concerning this proposed rule contact Vincent
Bennett, ANE-7 Engine and Propeller Directorate, Aircraft Certification
Service, 12 New England Executive Park, Burlington, Massachusetts
01803-5299; telephone (781) 238-7044; facsimile (781) 238-7055; e-mail
vincent.bennett@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite interested people to take part in this rulemaking by
sending written comments, data, or views. The most helpful comments
reference a specific portion of the special conditions, explain the
reason for any recommended change, and include supporting data. We ask
that you send us two copies of written comments.
We will file in the docket all comments we receive, as well as a
report summarizing each substantive public contact with FAA personnel
about these special conditions. You can inspect the docket before and
after the comment closing date. If you wish to review the docket in
person, go to the address in the ADDRESSES section of this preamble
between 9 am. and 5 p.m., Monday through Friday, except Federal
holidays.
We will consider all comments we receive by the closing date for
comments. We will consider comments filed late if it is possible to do
so without incurring expense or delay. We may change these special
conditions based on the comments we receive.
If you want us to let you know we received your comments on this
proposal, send us a pre-addressed, stamped postcard on which the docket
number appears. We will stamp the date on the postcard and mail it back
to you.
Background
On December 5, 2005, PWC applied for a type certificate for the
model PW210S turboshaft engine. The engine is a free turbine turboshaft
designed for a transport category helicopter. This engine incorporates
a two stage compressor driven by a single stage turbine and a two stage
free power turbine driving a two stage reduction gearbox and main
output shaft. The control system includes a dual channel digital
electronic control. The engine will incorporate a novel or unusual
design feature associated with engine operation in auxiliary power unit
(APU) mode. The helicopter will incorporate a main rotor brake what
will allow the engine main output shaft and power turbine to be brought
to a stop and to remain stationary, while the gas generator portion of
the engine continues to operate as an APU while on the ground.
The applicable airworthiness standards do not contain adequate or
appropriate airworthiness standards to address this design feature.
These special conditions contain the additional airworthiness
standards necessary to establish a level of safety equivalent to the
level that would result
[[Page 8322]]
from compliance with the applicable standards of airworthiness in
effect on the date of application.
Type Certification Basis
Under the provisions of 14 CFR 21.17, PWC must show that the model
PW210S turboshaft engine meets the provisions of the applicable
regulations in effect on the date of application. The application date
is December 5, 2005, which corresponds to 14 CFR part 33 Amendment 20.
However, PWC has elected to demonstrate compliance to later amendments
of part 33 for this model. Therefore, the certification basis for the
PW210S model turboshaft engine will be part 33, effective February 1,
1965, as amended by Amendments 33-1 through 33-24.
If the Administrator finds that the applicable airworthiness
regulations in part 33, as amended, do not contain adequate or
appropriate safety standards for the PWC model PW210S turboshaft
engine, because of a novel or unusual design feature, special
conditions are prescribed under the provisions of Sec. 21.16.
The FAA issues special conditions, as defined by 14 CFR 11.19, in
accordance with 14 CFR 11.38, which become part of the type
certification basis in accordance with Sec. 21.17(b)(2).
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include another related model that incorporates the same or
similar novel or unusual design feature, or should any other model
already included on the same type certificate be modified to
incorporate the same or similar novel or unusual design feature, the
special conditions would also apply to the other model.
Novel or Unusual Design Features
The Pratt and Whitney Canada (PWC) model PW210S turboshaft engine
will incorporate a novel or unusual design feature associated with
engine operation in auxiliary power unit (APU) mode. Special conditions
for APU mode are proposed to address the novel and unusual design
feature. The special conditions are discussed below.
Discussion
The proposed special conditions are similar to those requirements
that currently exist in 14 CFR part 33, Sec. 33.96 Engine Tests in
Auxiliary Power Unit (APU) Mode. However the current rule only applies
to turboprop type engines, therefore special conditions are needed to
apply appropriate requirements to turboshaft type engines. Also, the
type certification considerations for function and reliability are
common between these two engine types in this regard, making
requirements similar to current Sec. 33.96 generally applicable to
turboshaft engine types. Future rulemaking may occur to expand the
applicability of Sec. 33.96 to include turboshaft type engines.
Applicability
As discussed above, these special conditions are applicable to PWC
model PW210S turboshaft engines. If Pratt and Whitney Canada applies
later for a change to the type certificate to include another related
model incorporating the same novel or unusual design feature, these
special conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on one model of engine. It is not a rule of general applicability, and
it affects only the applicant who applied to the FAA for approval of
these features on the engine.
List of Subjects in 14 CFR Part 33
Air transportation, Aircraft, Aviation safety, Safety.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701-44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation Administration (FAA) proposes the
following special conditions as part of the type certification basis
for Pratt and Whitney Canada (PWC) model PW210S turboshaft engines.
1. PART 1 DEFINITION. Unless otherwise approved by the
Administrator and documented in the appropriate manuals and
certification documents, the following definition applies to this
special condition: ``Auxiliary Power Unit Mode'' Engine operation with
the main output shaft and power turbine locked and stationary, while
the gas generator portion of the engine continues to operate, for the
purpose of supplying the rotorcraft with electric/hydraulic/pneumatic
power (as applicable) while on the ground.
2. PART 33 REQUIREMENTS:
(a) Ground locking: A total of 45 hours with the engine output
shaft locked to simulate rotor brake engagement, in a manner which
clearly demonstrates the complete engine's ability to function without
adverse affect while operating in the APU mode under the maximum
conditions of engine rotor speed, torque, temperature, air bleed and
power extraction as specified by the applicant.
(b) Dynamic braking: A total of 400 application-release cycles of
simulated brake engagements must be made in a manner which clearly
demonstrates the complete engine's ability to function without adverse
affect under the maximum conditions of engine acceleration and
deceleration rate, rotor speed, torque and temperature as specified by
the applicant. The engine output shaft must be stopped prior to brake-
release.
(c) One hundred engine starts and stops with the output shaft
locked in a manner simulating rotor brake engagement.
(d) The tests required by paragraphs (a), (b) and (c) of this
section must be performed on the same engine, but this engine need not
be the same engine used for the tests required by Sec. 33.87 of 14 CFR
part 33.
(e) The tests required by paragraphs (a), (b) and (c) of this
section must be followed by engine disassembly to the extent necessary
to show that each engine part conforms to the type design and is
eligible for incorporation into an engine for continued operation in
accordance with information submitted in compliance with Sec. 33.4,
Instructions for Continued Airworthiness.
(f) Brake engagement and release: The effects on the engine of
braking and releasing the output shaft, including partial or sudden
events while the engine is running, must be determined.
Issued in Burlington, Massachusetts, on January 30, 2011.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2011-3068 Filed 2-11-11; 8:45 am]
BILLING CODE 4910-13-M
