
[Federal Register Volume 80, Number 130 (Wednesday, July 8, 2015)]
[Rules and Regulations]
[Pages 38913-38914]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16713]



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  Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Rules 
and Regulations  

[[Page 38913]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 33

[Docket No.FAA-2015-1771; Special Conditions No. 33-016-SC]


Special Conditions: Pratt and Whitney Canada, PW210A; Flat 30-
Second and 2-Minute One Engine Inoperative Rating

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Pratt and Whitney 
Canada PW210A engine model. This engine will have a novel or unusual 
design feature--an additional one engine inoperative (OEI) rating that 
combines the 30-second and 2-minute OEI ratings into a single rating. 
The applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These special 
conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: Effective August 7, 2015.

FOR FURTHER INFORMATION CONTACT: For technical questions concerning 
these special conditions, contact Tara Fitzgerald, ANE-111, Engine and 
Propeller Directorate, Aircraft Certification Service, 12 New England 
Executive Park, Burlington, Massachusetts, 01803-5213; telephone (781) 
238-7130; facsimile (781) 238-7199; email tara.fitzgerald@faa.gov. For 
legal questions concerning these special conditions, 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; email vincent.bennett@faa.gov.

SUPPLEMENTARY INFORMATION: 

Background

    On February 14, 2013, Pratt and Whitney Canada applied for an 
amendment to Type Certificate No. E00083EN-E to include the new PW210A 
engine model. The PW210A, which is a derivative of the PW210S currently 
approved under E00083EN-E, is intended for rotorcraft use. For their 
PW210A engine model, Pratt and Whitney Canada requests an additional 
OEI rating that combines the 30-second and 2-minute OEI rating into a 
single rating to satisfy the rotorcraft requirements for increased 
power in OEI scenarios. This additional OEI rating is named ``Flat 30-
second and 2-minute OEI.''
    These special conditions are necessary because the applicable 
airworthiness regulations do not contain adequate or appropriate safety 
standards for combining the requirements of the flat 30-second and 2-
minute OEI rating.

Type Certification Basis

    Under the provisions of Sec.  21.101, Pratt and Whitney Canada must 
show that the PW210A meets the applicable provisions of 14 CFR part 33, 
as amended by Amendments 33-1 through 33-30. These regulations will be 
incorporated into Type Certificate No. E00083EN after type 
certification approval of the PW210A. The regulations incorporated by 
reference in the type certificate are commonly referred to as the 
``original type certification basis.'' The regulations incorporated by 
reference in Type Certificate No. E00083NE are as follows:
    Title 14 of the Code of Federal Regulations (14 CFR part 33), 
effective February 1, 1965, Amendments 33-1 through 33-24 and two 
special conditions:
33-008-SC: for on ground engine operation in auxiliary power unit (APU) 
mode, and
33-009-SC: for 30-minutes all engines operating (AEO) hovering power 
engine rating
For the PW210A the certification basis is:

    1. Airworthiness Standards: 14 CFR part 33, effective February 1, 
1965, Amendments 33-1 through 33-30, inclusive.
    2. Environmental Standards: 14 CFR part 34, effective September 10, 
1990, as amended by 34-1 through 34-4 and 40 CFR part 87, effective 
(ICAO Annex 16, Volume II--Aircraft Engine Emissions, as amended up to 
and including Amendment 6).
    In addition, the certification basis includes other regulations, 
special conditions and exemptions that are not relevant to these 
special conditions. Type Certificate No. E00083EN will be updated to 
include a complete description of the certification basis for this 
model engine.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 33) do not contain adequate or 
appropriate safety standards for the PW210A because of a novel or 
unusual design feature, special conditions are prescribed under the 
provisions of Sec.  21.16.
    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 any other 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 under Sec.  21.101.
    Accordingly, should type certificate E00083EN be amended to include 
another model that incorporates the ``Flat 30-second and 2-minute 
OEI,'' the special conditions as defined would apply to models whose 
certification basis is amendment 33-25 or later.
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38, and they become part of the type-
certification basis under Sec.  21.17(a)(2).

Novel or Unusual Design Features

    The PW210A will incorporate the following novel or unusual design 
features: The design feature is a ``Flat 30-second and 2-minute'' one 
engine inoperative (OEI) rating. The Flat 30-second and 2-minute OEI 
rating represents a case where the power levels and associated 
operating limitations for the 30-second OEI and 2-minute OEI ratings 
(defined in Part 33) are the same.

[[Page 38914]]

Discussion

    These special conditions are necessary because current part 33 
regulations do not contain airworthiness standards for extending the 2-
minute OEI rating for 30-seconds. These special conditions extend the 
time dependent requirements applicable to the 30-second OEI or 2-minute 
OEI to the 2.5 minutes time duration of the ``Flat 30-second and 2-
minute OEI'' Power.
    The 2.5 minutes time duration for the rating may affect the 
engine's structural and operational characteristics that are time 
dependent, such as the values for transients, time duration for 
stabilization to steady state, and part growth due to deformation. To 
address these aspects, we propose special conditions based on revised 
requirements of Sec. Sec.  33.27, 33.87(a)(7), and 33.88(b).
    The 2.5 minutes time duration for the rating affects the test 
conducted for the endurance test. For the 30-second OEI and 2-minute 
OEI the test schedule of Sec.  33.87(f) is divided among the two 
ratings. We propose special conditions based on revised requirements of 
Sec.  33.87(f) to ensure the test will be run for 2.5 minutes duration 
with no interruption.
    The 2.5 minutes time duration for the rating necessitates extending 
the time duration requirement of Sec.  33.28(k) applicable to the 30-
second OEI rating from 30 seconds to 2.5 minutes. This requirement is 
for automatic availability and control of the engine for the entire 
duration of the rating's usage.
    The 2.5 minutes time duration for the rating necessitates extending 
the requirements of Sec.  33.29(c) that are applicable to 30-second OEI 
and 2-minute OEI ratings to the single Flat 30-second and 2-minute OEI 
Power rating. We propose special conditions to ensure that the 
instrumentation requirements normally reserved for 30-second OEI and 2-
minute OEI ratings are applied to the Flat 30-second and 2-minute OEI 
Power rating over its whole duration. The pilot does not have to be 
alerted at the end of 30 seconds use of the Flat 30-second and 2-minute 
OEI Power rating, only after the entire 2 minutes 30 seconds has 
expired. Paragraph 2.(e)(3) of these special conditions states that the 
engine must provide means or provision of means to alert maintenance of 
use of the Flat 30-second and 2-minute OEI Power rating, `alert' means 
after the aircraft lands, so any required maintenance actions can be 
completed before next flight.

Applicability

    As discussed above, these special conditions are applicable to the 
PW210A. Should Pratt and Whitney Canada apply at a later date for a 
change to the type certificate to include another model incorporating 
the same novel or unusual design feature, the special conditions would 
apply to that model as well.

Conclusion

    This action affects only the Flat 30-second and 2-minute OEI design 
features on the PW210A engine model. It is not a rule of general 
applicability and applies only to Pratt and Whitney Canada, who 
requested FAA approval of this engine feature.

List of Subjects in 14 CFR Part 33

    Aircraft, Engines, Aviation Safety, Reporting and Recordkeeping 
requirements.

    The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701, 44702, 44704.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Pratt and Whitney Canada PW210A engine 
model.

Flat 30-second and 2-minute OEI

1. Part 1.1 Definitions
    ``Rated Flat 30-second and 2-minute One Engine Inoperative (OEI) 
Power,'' with respect to rotorcraft turbine engines, means (1) a single 
rating for which the shaft horsepower and associated operating 
limitations of the 30-second OEI and 2-minute OEI ratings are equal, 
and (2) the shaft horsepower is that developed under static conditions 
at the altitude and temperature for the hot day, and within the 
operating limitations established under Part 33. The rating is for 
continuation of flight operation after the failure or shutdown of one 
engine in multiengine rotorcraft, for up to three periods of use no 
longer than 2.5 minutes each in any one flight, and followed by 
mandatory inspection and prescribed maintenance action.
2. Part 33 requirements
    (a) The airworthiness standards in Part 33 Amendment 30 for the 30-
second OEI and 2-minute OEI ratings are applicable to the Flat 30-
second and 2-minute OEI Power rating. In addition the following special 
conditions apply;
    (b) Section 33.7 Engine ratings and operating limitations. Flat 30-
second and 2-minute OEI Power rating and operating limitations are 
established for power, torque, rotational speed, gas temperature, and 
time duration.
    (c) Section 33.27 Turbine, compressor, fan, and turbosupercharger 
rotor overspeed. The requirements of Sec.  33.27, except that following 
the test, the rotor may not exhibit conditions such as cracking or 
distortion which preclude continued safe operation.
    (d) Section 33.28 Engine controls systems. Must incorporate a 
means, or a provision for a means, for automatic availability and 
automatic control of the Flat 30-second and 2-minute OEI Power within 
the declared operating limitations.
    (e) Section 33.29 Instrument Connection. In lieu of the 
requirements of 33.29(c) the PW210A must incorporate a means or a 
provision for a means to:
    (1) Alert the pilot when the engine is at the Flat 30-second and 2-
minute OEI Power level, when the event begins, and when the time 
interval expires;
    (2) Automatically record each usage and duration of power at the 
Flat 30-second and 2-minute OEI Power rating;
    (3) Following each flight when the Flat 30-second and 2-minute OEI 
Power rating is used, alert maintenance personnel in a positive manner 
that the engine has been operated at the Flat 30-second and 2-minute 
OEI Power level, and permit retrieval of the recorded data; and
    (4) Enable routine verification of the proper operation of the 
above means.
    (f) Section 33.87 Endurance test. The requirements applicable to 
30-second and 2-minute OEI ratings, except for:
    (1) The test of Sec.  33.87(a)(7) for the purposes of temperature 
stabilization, must be run with a test period time of 2.5 minutes.
    (2) The tests in Sec.  33.87(f)(2) and (3) must be run continuously 
for the duration of 2.5 minutes, and
    (3) The tests in Sec.  33.87(f)(6) and (7) must be run continuously 
for the duration of 2.5 minutes.
    (g) Section 33.88 Engine overtemperature test. The requirements of 
Sec.  33.88(b) except that the test time is 5 minutes instead of 4 
minutes.

    Issued in Burlington, Massachusetts, on June 26, 2015.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-16713 Filed 7-7-15; 8:45 am]
 BILLING CODE 4910-13-P


