[Federal Register Volume 76, Number 40 (Tuesday, March 1, 2011)]
[Proposed Rules]
[Pages 11172-11174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-4570]


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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.

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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 <a href="/cdn-cgi/l/email-protection#a5c8c4d7c68bc7cad0d1cdccc9c9ccc0d7e5c3c4c48bc2cad3"><span class="__cf_email__" data-cfemail="ea878b9889c488859f9e82838686838f98aa8c8b8bc48d859c">[email protected]</span></a>. 
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 
<a href="/cdn-cgi/l/email-protection#7f0916111c1a110b511d1a11111a0b0b3f191e1e51181009"><span class="__cf_email__" data-cfemail="2d5b44434e484359034f4843434859596d4b4c4c034a425b">[email protected]</span></a>.

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


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