Special Conditions: Pratt and Whitney Canada Model PW210S Turboshaft Engine, 11172-11174 [2011-4570]
Download as PDF
<![CDATA[
11172
Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules
b. Revise paragraphs II(a)(2)(viii)(A),
II(a)(2)(viii)(B) introductory text,
II(b)(1)(iv), II(b)(2)(ii), and II(b)(4);
b. Remove paragraph II(c)(3) and
remove and reserve paragraph II(c)(4);
and
c. Add new paragraph II(c)(3).
The revisions and addition read as
follows:
Appendix C to Part 704—Risk-Based
Capital Credit Risk-Weight Categories
*
*
*
*
*
Part II: Risk-Weightings
(a) * * *
(2) * * *
(viii) * * *
(A) A qualifying securities firm must meet
the minimum credit quality standards as
established by the corporate credit union’s
board of directors or demonstrate at least a
strong capacity to meet its financial
obligations, even under adverse economic
conditions, for the projected life of the
exposure, whichever requirement is more
stringent. Alternatively, a qualifying
securities firm may rely on the
creditworthiness of its parent consolidated
company, if the parent consolidated
company guarantees the claim.
(B) A collateralized claim on a qualifying
securities firm does not have to comply with
the requirements of paragraph (a) if the claim
arises under a contract that:
*
*
*
*
*
(b) * * *
(1) * * *
(iv) Unused portions of ABCP liquidity
facilities that do not meet the definition of an
eligible ABCP liquidity facility. The resulting
credit equivalent amount is assigned to the
risk category appropriate to the assets to be
funded by the liquidity facility based on the
assets or the obligor, after considering any
collateral or guarantees.
*
*
*
*
*
(2) * * *
(ii) Unused portions of commitments
(including home equity lines of credit and
eligible ABCP liquidity facilities) with an
original maturity exceeding one year except
those listed in paragraph II(b)(5) of this
Appendix. For eligible ABCP liquidity
facilities, the resulting credit equivalent
amount is assigned to the risk category
appropriate to the assets to be funded by the
liquidity facility based on the assets or the
obligor, after considering any collateral or
guarantees.
jlentini on DSKJ8SOYB1PROD with PROPOSALS
*
*
*
*
*
(4) 10 percent credit conversion factor
(Group D). Unused portions of eligible ABCP
liquidity facilities with an original maturity
of one year or less. The resulting credit
equivalent amount is assigned to the risk
category appropriate to the assets to be
funded by the liquidity facility based on the
assets or the obligor, after considering any
collateral or guarantees.
*
*
*
*
*
(c) * * *
(3) Internal ratings-based approach—
(i) Calculation. Corporate credit unions
with advanced risk management and
VerDate Mar<15>2010
18:33 Feb 28, 2011
Jkt 223001
reporting systems may seek NCUA approval
to use credit risk models to calculate riskweighted asset amounts for positions
described in paragraphs II(c)(1) and (2) of this
section. In determining whether to grant
approval, NCUA will consider the financial
condition and risk management
sophistication of the corporate credit union
and the adequacy of the corporate’s risk
models and supporting management
information systems.
(ii) Consistent use of internal ratings-based
approach. A corporate credit union that has
been granted NCUA approval to use an
internal ratings-based approach and that has
determined to use such an approach must do
so in a consistent manner for all securities so
rated.
in effect before such repeal or
modification. For purposes of this
paragraph, a participation would be in
effect on the date that the parties
executed the participation agreement.
PART 742—REGULATORY
FLEXIBILITY PROGRAM
13. The authority citation for part 742
continues to read as follows:
Authority: 12 U.S.C. 1756, 1766.
14. In § 742.4, revise paragraph
(a)(6)(i) to read as follows:
§ 742.4
RegFlex relief.
PART 709—INVOLUNTARY
LIQUIDATION OF FEDERAL CREDIT
UNIONS AND ADJUDICATION OF
CREDITOR CLAIMS INVOLVING
FEDERALLY INSURED CREDIT
UNIONS IN LIQUIDATIONS
11. The authority citation for part 709
continues to read as follows:
(a) * * *
(6) * * *
(i) The issuer has at least a very strong
capacity to meet its financial
obligations, even under adverse
economic conditions, for the projected
life of the security;
*
*
*
*
*
[FR Doc. 2011–4070 Filed 2–28–11; 8:45 am]
Authority: 12 U.S.C. 1757, 1766, 1767,
1786(h), 1787, 1788, 1789, 1789a.
12. In § 709.10, remove paragraphs
(a)(5) and (a)(6), and revise the section
heading and paragraphs (b), (f), and (g)
to read as follows:
BILLING CODE 7535–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
§ 709.10 Treatment by conservator or
liquidating agent of financial assets
transferred in connection with a
participation.
14 CFR Part 33
*
Special Conditions: Pratt and Whitney
Canada Model PW210S Turboshaft
Engine
*
*
*
*
(b) The Board, by exercise of its
authority to disaffirm or repudiate
contracts under 12 U.S.C. 1787(c), will
not reclaim, recover, or recharacterize as
property of the credit union or the
liquidation estate any financial assets
transferred to another party by a
federally-insured credit union in
connection with a participation,
provided that the transfer meets all the
conditions for sale accounting treatment
under generally accepted accounting
principles, other than the ‘‘legal
isolation’’ condition addressed by this
section.
*
*
*
*
*
(f) The Board will not seek to avoid
an otherwise legally enforceable
participation agreement executed by a
federally-insured credit union solely
because such agreement does not meet
the ‘‘contemporaneous’’ requirement of
sections 207(b)(9) and 208(a)(3) of the
Federal Credit Union Act.
(g) This section may be repealed by
the NCUA upon 30 days notice and
opportunity for comment provided in
the Federal Register, but any such
repeal or amendment will not apply to
any transfers of financial assets made in
connection with a participation that was
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
[Docket No. NE131; Notice No. 33–10–02–
SC]
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
This action proposes special
conditions for Pratt and Whitney
Canada (PWC) model PW210S engines.
The engine model will have a novel or
unusual design feature which is a 30–
Minute All Engines Operating (AEO)
power rating. This rating is intended to
be used for hovering at increased power
for search and rescue missions. 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 31, 2011.
ADDRESSES: You must mail two copies
of your comments to: Federal Aviation
Administration, Engine and Propeller
SUMMARY:
E:\FR\FM\01MRP1.SGM
01MRP1
Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules
Directorate, Attn: Marc Bouthillier,
Rules Docket (ANE–111), Docket No.
NE131, 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. NE131. You can
inspect comments in the Rules Docket
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
jlentini on DSKJ8SOYB1PROD with PROPOSALS
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 a.m. 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.
VerDate Mar<15>2010
18:33 Feb 28, 2011
Jkt 223001
Background
On December 5, 2005, PWC applied
for type certification for a new model
PW210S turboshaft engine. This engine
incorporates a two stage compressor
driven by a single stage un-cooled
turbine and a two stage free power
turbine driving a two stage reduction
gearbox. The control system includes a
dual channel full authority digital
electronic control. The engine will
incorporate a novel or unusual design
feature which is a 30–Minute All Engine
Operating (AEO) power rating. This
rating was requested by the applicant to
support rotorcraft search and rescue
missions that require extensive hover
operations at high power.
The applicable airworthiness
standards do not contain adequate or
appropriate airworthiness standards to
address this design feature. Therefore a
special condition is necessary to apply
additional requirements for rating
definition, instructions for continued
airworthiness (ICA) and endurance
testing. The 30 minute time limit
applies to each instance the rating is
used; however there is no limit to the
number of times the rating can be used
during any one flight, and there is no
cumulative time limitation. The ICA
requirement is intended to address the
unknown nature of actual rating usage
and associated engine deterioration. The
applicant is expected to make an
assessment of the expected usage and
publish ICA’s and ALS limits in
accordance with those assumptions,
such that engine deterioration is not
excessive. The endurance test
requirement of 25 hours operation at 30
minutes AEO is similar to several
special conditions issued over the past
20 years. Because the PWC model
PW210S turboshaft engine has a
continuous OEI rating and limits equal
or higher than the 30 minute AEO
rating, the test time performed at the
continuous OEI rating may be credited
toward the 25 hour requirement.
However, test time spent at other rating
elements of the test, such as takeoff or
other OEI ratings (that may be equal to
or higher values), may not be counted
toward the 25 hours of required
running.
These special conditions contain the
additional airworthiness standards
necessary to establish a level of safety
equivalent to the level that would result
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
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
11173
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.
Novel or Unusual Design Features
The Pratt and Whitney Canada (PWC)
model PW210S turbo shaft engine will
incorporate a novel or unusual design
feature which is a 30-Minute All Engine
Operating (AEO) power rating, for use
up to 30 minutes at any time between
the take-off and landing phases of a
flight. Special conditions for a 30Minute AEO rating are proposed to
address this novel and unusual design
feature. The special conditions are
discussed below.
Discussion
The PWC model PW210S turboshaft
engine is a free turbine turboshaft
designed for a transport category twinengine helicopter. The helicopter
manufacturer anticipates that for search
and rescue, extended hovering
maneuvers may require more than
maximum continuous power for periods
up to 30 minutes. PWC has requested a
30-Minute All Engine Operating (AEO)
rating, for use up to 30 minutes at any
time between the take-off and landing
phases of a flight. PWC has indicated
E:\FR\FM\01MRP1.SGM
01MRP1
11174
Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules
that the number of times this rating can
be used in one flight is not limited.
Applicability
As discussed above, these special
conditions are applicable to PWC model
PW210S turbo shaft engines. If Pratt and
Whitney Canada applies later for a
change to the type certificate to include
another closely 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:
jlentini on DSKJ8SOYB1PROD with PROPOSALS
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
turbo shaft 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: ‘‘Rated
30 Minute AEO Power’’, means the
approved brake horsepower developed
under static conditions at the specified
altitude and temperature, and within
the operating limitations established
under part 33, and limited in use to
periods not exceeding 30 minutes each.
2. PART 33 REQUIREMENTS.
(a) Sections 33.1 Applicability and
33.3 General: As applicable, all
documentation, testing and analysis
required to comply with the part 33
certification basis, must account for the
30 minute AEO rating, limits and usage.
(b) Section 33.4, Instructions for
Continued Airworthiness (ICA). In
addition to the requirements of § 33.4,
the ICA must:
(1) Include instructions to ensure that
in-service engine deterioration due to
rated 30 minute AEO power usage will
not be excessive, meaning that all other
approved ratings, including one engine
inoperative (OEI), are available (within
associated limits and assumed usage) for
each flight; and that deterioration will
VerDate Mar<15>2010
18:33 Feb 28, 2011
Jkt 223001
not exceed that assumed for declaring a
time between overhaul (TBO) period.
(i) The applicant must validate the
adequacy of the maintenance actions
required under paragraph (b)(1) above.
(2) Include in the airworthiness
limitations section (ALS), any
mandatory inspections and
serviceability limits related to the use of
the 30-minute AEO rating.
(c) Section 33.87, Endurance Test. In
addition to the requirements of
§§ 33.87(a) and 33.87(d), the overall test
run must include a minimum of 25
hours of operation at 30 minute AEO
power and limits, divided into periods
of 30 minutes AEO power with alternate
periods at maximum continuous power.
(1) Each § 33.87(d) continuous oneengine-inoperative (OEI) rating test
period of 30 minutes or longer, run at
power and limits equal to or higher then
the 30 minute AEO rating, may be
credited toward this requirement.
Issued in Burlington, Massachusetts on
February 1, 2011.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2011–4570 Filed 2–28–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0099; Directorate
Identifier 2010–SW–085–AD]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Model S–76A, S–
76B, and S–76C Helicopters Modified
by Supplemental Type Certificate
SR09211RC
crew from successfully deploying and
using the life raft. It was determined
that the handle in this incident was not
manufactured to the approved Type
Design. We are proposing this AD to
prevent the bending of the handle,
which could result in failure of the life
raft to deploy. This failure could lead to
loss of access to the life raft after an
emergency ditching on water.
DATES: We must receive comments on
this proposed AD by May 2, 2011.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• 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 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may get the service information
identified in this proposed AD from
Aero Seats and Systems, Inc., 340
Thomas Place, Everman, Texas 76140,
telephone (817) 551–0818, fax (817)
551–0838, e-mail
rcrouch@aeroseatsandsystems.com.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://
www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Martin Crane, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, 2601 Meacham
Blvd., Fort Worth, Texas 76137,
telephone (817) 222–5170, fax (817)
222–5783.
SUPPLEMENTARY INFORMATION:
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
Comments Invited
We propose to adopt a new
airworthiness directive (AD) for all
Sikorsky Aircraft Corporation (Sikorsky)
S–76 model helicopters with a certain
life raft deployment system (LRDS)
installed per Supplemental Type
Certificate (STC) SR09211RC. This
proposed AD would require removing
and replacing the pilot or co-pilot life
raft deployment handle (handle) located
on the left side of the ‘‘broom closet’’ of
the helicopter. This proposed AD is
prompted by an incident that occurred
where the handle bent prior to the life
raft deploying, and this prohibited the
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0099, Directorate Identifier
2010–SW–085–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
AGENCY:
SUMMARY:
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
E:\FR\FM\01MRP1.SGM
01MRP1
]]>Agencies
[Federal Register Volume 76, Number 40 (Tuesday, March 1, 2011)]
[Proposed Rules]
[Pages 11172-11174]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-4570]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 33
[Docket No. NE131; Notice No. 33-10-02-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 Pratt and Whitney
Canada (PWC) model PW210S engines. The engine model will have a novel
or unusual design feature which is a 30-Minute All Engines Operating
(AEO) power rating. This rating is intended to be used for hovering at
increased power for search and rescue missions. 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 31, 2011.
ADDRESSES: You must mail two copies of your comments to: Federal
Aviation Administration, Engine and Propeller
[[Page 11173]]
Directorate, Attn: Marc Bouthillier, Rules Docket (ANE-111), Docket No.
NE131, 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. NE131. You can inspect comments in the Rules Docket weekdays,
except Federal holidays, between 7:30 a.m. 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 a.m. 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 type certification for a new
model PW210S turboshaft engine. This engine incorporates a two stage
compressor driven by a single stage un-cooled turbine and a two stage
free power turbine driving a two stage reduction gearbox. The control
system includes a dual channel full authority digital electronic
control. The engine will incorporate a novel or unusual design feature
which is a 30-Minute All Engine Operating (AEO) power rating. This
rating was requested by the applicant to support rotorcraft search and
rescue missions that require extensive hover operations at high power.
The applicable airworthiness standards do not contain adequate or
appropriate airworthiness standards to address this design feature.
Therefore a special condition is necessary to apply additional
requirements for rating definition, instructions for continued
airworthiness (ICA) and endurance testing. The 30 minute time limit
applies to each instance the rating is used; however there is no limit
to the number of times the rating can be used during any one flight,
and there is no cumulative time limitation. The ICA requirement is
intended to address the unknown nature of actual rating usage and
associated engine deterioration. The applicant is expected to make an
assessment of the expected usage and publish ICA's and ALS limits in
accordance with those assumptions, such that engine deterioration is
not excessive. The endurance test requirement of 25 hours operation at
30 minutes AEO is similar to several special conditions issued over the
past 20 years. Because the PWC model PW210S turboshaft engine has a
continuous OEI rating and limits equal or higher than the 30 minute AEO
rating, the test time performed at the continuous OEI rating may be
credited toward the 25 hour requirement. However, test time spent at
other rating elements of the test, such as takeoff or other OEI ratings
(that may be equal to or higher values), may not be counted toward the
25 hours of required running.
These special conditions contain the additional airworthiness
standards necessary to establish a level of safety equivalent to the
level that would result 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 turbo shaft engine
will incorporate a novel or unusual design feature which is a 30-Minute
All Engine Operating (AEO) power rating, for use up to 30 minutes at
any time between the take-off and landing phases of a flight. Special
conditions for a 30-Minute AEO rating are proposed to address this
novel and unusual design feature. The special conditions are discussed
below.
Discussion
The PWC model PW210S turboshaft engine is a free turbine turboshaft
designed for a transport category twin-engine helicopter. The
helicopter manufacturer anticipates that for search and rescue,
extended hovering maneuvers may require more than maximum continuous
power for periods up to 30 minutes. PWC has requested a 30-Minute All
Engine Operating (AEO) rating, for use up to 30 minutes at any time
between the take-off and landing phases of a flight. PWC has indicated
[[Page 11174]]
that the number of times this rating can be used in one flight is not
limited.
Applicability
As discussed above, these special conditions are applicable to PWC
model PW210S turbo shaft engines. If Pratt and Whitney Canada applies
later for a change to the type certificate to include another closely
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 turbo shaft 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: ``Rated 30 Minute AEO Power'', means the approved
brake horsepower developed under static conditions at the specified
altitude and temperature, and within the operating limitations
established under part 33, and limited in use to periods not exceeding
30 minutes each.
2. PART 33 REQUIREMENTS.
(a) Sections 33.1 Applicability and 33.3 General: As applicable,
all documentation, testing and analysis required to comply with the
part 33 certification basis, must account for the 30 minute AEO rating,
limits and usage.
(b) Section 33.4, Instructions for Continued Airworthiness (ICA).
In addition to the requirements of Sec. 33.4, the ICA must:
(1) Include instructions to ensure that in-service engine
deterioration due to rated 30 minute AEO power usage will not be
excessive, meaning that all other approved ratings, including one
engine inoperative (OEI), are available (within associated limits and
assumed usage) for each flight; and that deterioration will not exceed
that assumed for declaring a time between overhaul (TBO) period.
(i) The applicant must validate the adequacy of the maintenance
actions required under paragraph (b)(1) above.
(2) Include in the airworthiness limitations section (ALS), any
mandatory inspections and serviceability limits related to the use of
the 30-minute AEO rating.
(c) Section 33.87, Endurance Test. In addition to the requirements
of Sec. Sec. 33.87(a) and 33.87(d), the overall test run must include
a minimum of 25 hours of operation at 30 minute AEO power and limits,
divided into periods of 30 minutes AEO power with alternate periods at
maximum continuous power.
(1) Each Sec. 33.87(d) continuous one-engine-inoperative (OEI)
rating test period of 30 minutes or longer, run at power and limits
equal to or higher then the 30 minute AEO rating, may be credited
toward this requirement.
Issued in Burlington, Massachusetts on February 1, 2011.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2011-4570 Filed 2-28-11; 8:45 am]
BILLING CODE 4910-13-P
