1. Ingeniería

EASA.IM.E.022
Description:
E.022 (IM) Pratt and Whitney Canada
PT6C-67 series engines
Language:
English
TCDS:
EASA.IM.E.022
Product type:
Engine (CS-E)
Manufacturer/TC
Holder:
Pratt and Whitney Canada Corp.
European Aviation Safety Agency: Ottoplatz 1, D-50679 Cologne, Germany - easa.europa.eu
An agency of the European Union
European Aviation Safety Agency
EASA
TYPE-CERTIFICATE
DATA SHEET
Number :
Issue :
Date :
Type :
Models
PT6C-67C
PT6C-67E
List of effective Pages:
Page
Issue
1
3
2
3
3
3
4
3
5
3
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3
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3
IM.E.022
03
28 January 2015
Pratt & Whitney Canada
PT6C-67 series engines
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PT6C-67 series engines
Intentionally left blank
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PT6C-67 series engines
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I. General
1. Type/Models:
PT6C-67 / PT6C-67C, PT6C-67E
2. Type Certificate Holder:
Pratt and Whitney Canada Corp.
Longueuil, Quebec
Canada
3. Manufacturer: Pratt and Whitney Canada
4. EASA Certification Application Date:
PT6C-67C
17 May 2002
(to ENAC-Italy)
PT6C-67E
24 March 2008
5. EASA Certification Reference Date:
PT6C-67C
27 March 1998
PT6C-67E
02 Nov. 2009
6. EASA Certification Date:
PT6C-67C
09 June 2003
PT6C-67E
09 Nov. 2012
EASA Type Certification for the PT6C-67C engine model is granted, in accordance with Article 2
paragraph 3(a) of EU Commission Regulation EC 1702/2003, based on the ENAC-Italy Type Certificate
Mo 127, issued prior to 28 September 2003.
II. Certification Basis
1. Transport Canada Certification Basis Details: see Transport Canada TCDS E-32
2. EASA Certification Basis:
2.1 Airworthiness Standards:
- JAR E Change 9 dated 21 October 1994 (PT6C-67C)
- CS-E Amendment 1 dated 03 December 2007 (PT6C-67E)
2.2 Special Conditions:
- 30-minute Take-off Power Rating (PT6C-67E)
2.3 Deviations:
- None.
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2.4 Equivalent Safety Findings:
- None.
2.5 Environmental Standards:
-
Fuel Venting:
nd
ICAO Annex 16 Volume II, 2 Edition, 1993 (PT6C-67C)
CS-34.1, Fuel Venting (PT6C-67E)
III.Technical Characteristics
1. Type Design Definition:
As defined by the applicable PT6C-67C resp. PT6C-67E Engine Parts List:
PT6C-67C: Manual No. 3045334
PT6C-67E: Manual No. 3072874
2. Description:
Four axial stages and single stage centrifugal compressor, reverse flow annular combustor, single
stage high pressure turbine, two stage free power turbine. Single channel Engine Electronic Control
System (EEC) with manual back-up for PT6C-67C, dual channel EEC without manual back-up for
PT6C-67E. The starter and engine mounts are not part of the engine definition.
3. Equipment:
The engine equipment list is inlcuded in the Type Design Definition.
4. Dimensions and Weight:
Model
Overall Length
Overall Diameter
Dry Weight
PT6C-67C
PT6C-67E
1.50m
1.50m
0.57m
0.57m
205 kg
216.8 kg
The Dry Weight includes Pratt & Whitney Canada supplied engine build-up components.
5. Ratings:
The engine ratings are based on dry sea level ICAO standard atmospheric conditions, with no external
accessory loads and no air bleed. The quoted ratings are obtainable on a test stand with the fuel, oil,
reference intake and exhaust ducts as specified in the relevant Installation Manual.
5.1
All Engine Operative Power (kW)
Model
30 Minutes Power
Take-off Power
(5 minutes)
Maximum
Continuous Power
PT6C-67C
PT6C-67E
969
861
969
815
900
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One Engine Inoperative (OEI) Power (kW)
Model
30 sec. OEI
2½-Minute OEI
2 Minute OEI
Continuous OEI
PT6C-67C
PT6C-67E
1485
1217
-
1321
1064
1154
6. Control System:
Fuel controls and power management are controlled by an Electronic Engine Control (EEC) with a
backup hydro-mechanical control for the PT6C-67C and a dual channel EEC for the PT6C-67E. The
hardware and software configuration of this system and the associated engine fuel pump and hydromechanical unit (PT6C-67C) or fuel control unit (PT6C-67E) are controlled by the approved engine
equipment list for the specific engine model and aircraft application.
7. Fluids
See applicable Engine Maintenance Manual for specific approved oil, fuel and additives.
8. Aircraft Accessory Drives:
Model
Drive
Rotation
Speed Ratio To
Gas Generator
Max. Torque
Continuous
Nm
Max. Torque
Static
Nm
PT6C-67C
Starter
Generator
Starter
Generator
CW
0.29:1
24.0
200.7
Max.
Moment
Overhang
Nm
28.2
CW
0.29:1
24.0
200.7
28.2
PT6C-67E
9. Maximum Permissible Air Bleed Extraction:
The maximum permissible air bleed extraction is 5.25% of the engine inlet airflow and nil during start.
IV.Operational Limits:
1. Temperature Limits:
1.1 Maximum Measured Gas Turbine Temperature Limits (ºC):
Rating and Transient
PT6C-67C
PT6C-67E
30 sec. OEI
2½ Minute OEI
2 Minute OEI
Continuous OEI
30 min Power
Take-off (5 minutes)
Maximum Continuous
835
775
775
735
Starting (2 seconds)
Transient
1100
847 (10 sec.)
915
865
820
815
815
775
Per Installation
Manual
925 (20 sec.)
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1.2 Maximum Oil Inlet Temperature Range (ºC):
PT6C-67C
PT6C-67E
-50
10
140
-50
10
140
Minimum for starting
Minimum for continuous operation
Maximum for continuous operation
1.3 Fuel Inlet Temperature (ºC):
The minimum fuel temperature at the pump inlet shall be that equivalent to a viscosity of 12
centistokes. Refer to the relevant installation Manual for the recommended additives.
PT6C-67C
PT6C-67E
-50
-34
-30
50
(all types)
-29
-29
60
(Jet A, A1, JP5 & JP8 only)
Minimum for starting for :
JP4, Jet B fuel types
Jet A, A-1 fuel types
JP5 fuel type
Maximum
2. Maximum Permissible Rotor Speeds (rpm) :
2.1 All Engine Operative:
PT6C-67C:
Rotor Shaft
Take-off
(5 Minutes)
21420
39100
21420
Output Shaft
Gas Generator
Power Turbine
Maximum
Continuous
21420
38200
21420
Transient
10 seconds
23310
40900
23310
PT6C-67E:
Rotor Shaft
30 Min Power
Output Shaft
Gas Generator
Power Turbine
22470
39200
22470
Take-off
(5 Minutes)
22470
39200
22470
Maximum
Continuous
22470
38500
22470
2.2 One Engine Operative:
PT6C-67C:
Rotor Shaft
Output Shaft
Gas Generator
Power Turbine
2½ Minute OEI
21420
40500
21420
100% reference speeds:
Continuous OEI
21420
39100
21420
Power Turbine:
Gas Generator:
21000 rpm
38200 rpm
Transient
20 seconds
23470
39500
23470
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PT6C-67E:
Rotor Shaft
Output Shaft
Gas Generator
Power Turbine
30 sec. OEI
21000
41600
21000
100% reference speeds:
2 Minute OEI
21000
40500
21000
Power Turbine:
Gas Generator:
Continuous OEI
21000
39500
21000
21000 RPM
37468 RPM
3. Maximum Permissible Torque Limits (Nm):
PT6C-67C :
2½ Minute
OEI
542
Continuous
OEI
475
Take-off
(5 minutes)
384
Maximum
Continuous
363
Transient
(10 sec.)
597
PT6C-67E :
30 sec
OEI
675
2 Minute
OEI
600
Continuous
OEI
525
30 min
Power
441
Take-off
(5 minutes)
441
Maximum
Continuous
410
Transient
(20 sec.)
543
4. Pressure Limits:
4.1 Fuel Pump Inlet pressure:
Minimum pressure at maximum fuel temperature, at Sea Level, kPa
PT6C-67E
Fuel Type
PT6C-67C
Jet A, Jet A1,
JP5
22.8
Aircraft Boost
Pumps
Operational
Aircraft Boost Pumps NotOperational
V/L = 0.48 max up to 15000 ft
(4572 m) linearly decreasing to V/L
= 0.44 max at 20000 ft (6096 m)
JP4
49.0
(TVP: True Vapour Pressure, V/L: Vapour to Liquid Ratio)
TVP + 0.29
The minimum required fuel pressure at the engine fuel pump inlet varies with altitude (see the
relevant Installation Manual).
Maximum pressure: 206.9 kPa for the PT6C-67C, 276 kPa for the PT6C-67E
4.2 Oil Pressure Limits:
Maximum for starting PT6C-67C & E:
1517 kPa
The minimum and maximum oil pressures during operation vary with the gas generator speed
(see the relevant Installation Manual).
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5. Installation Assumptions:
The installation assumptions are quoted in the applicable Engine Installation Manual.
6. Dispatch Limitations: see Note 5
There is no Time Limited Dispatch for the EEC of this engine.
V. Operating and Service Instructions
Manuals
Engine Maintenance Manual
Engine Overhaul Manual
Installation Manual
Operating Instruction Manual
PT6C-67C
PT6C-67E
3045332
3045333
3072872
ER 4218
ER 6857
Service Bulletins as issued for each engine model.
VI. Notes
Note 1: Lightning protection levels and electromagnetic interference are specified in the Installation
Manual, Section 7.
Note 2: The Electronic Engine Control Unit must not be installed in a designated fire zone.
Note 3: The engines are approved to be fitted to rotorcraft only where the installation precludes
foreign objects from entering the engine inlet as defined in JAR-E 790(c) and JAR-E 800
(PT6C-67C) resp. CS-E 790(b) and CS-E 800 (PT6C-67E).
Note 4: The life limited parts are listed in Pratt & Whitney Canada Maintenance Manual, Airworthiness
Limitations Section.
Note 5: Dispatch is not permitted with faults in the EEC or in any engine-associated equipment unless
it is included in an approved MMEL. Aircraft disptachability with failed engine ITT
thermocouple assembly is permitted for one ferry flight only and within the envelope declared
in the relevant Installation Manual, Section 2.
Note 6: The uninstalled engine meets the JAR (PT6C-67C) resp. CS (PT6C-67E) requirement for
operation in icing conditions within the envelope defined in JAR/FAR/CS-29 Appendix C when
installed and operated in accordance with the Installation Manual.
Note 7: The software for the Electronic Engine Control has been developed and tested in accordance
with the provisions of Flight Critical catefory (level A) of RTCA DO 178B.
Note 8: Prior to issue of Transport Canada accepted Overhaul Manual, overhauls are not permitted
and engine may be re-manufactured to new production configuration.
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