[Federal Register Volume 76, Number 30 (Monday, February 14, 2011)]
[Proposed Rules]
[Pages 8321-8322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-3068]


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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.

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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 [email protected]. 
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 
[email protected].

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]
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