DESCRIPTION AND OPERATION 1. ENGINE ASSEMBLY, COMPLETE
WALTER M601E-21 Fig. 6
km/hr
ITT [oC]
ITT
km/hr
WALTER a.s.
MAINTENANCE MANUAL MANUAL PART No. 0982055
72.01.02
Page 18
Jul 1, 2003
WALTER a.s.
MAINTENANCE MANUAL MANUAL PART No. 0982055
Table 2 72.01.02
placement Oil Power
rating Ambient
temperature NOTE
kW
External power source; ISA
alt. of up to 4 km (13123 ft) 700 minimum speed For ambient air
temperature In case of interrupted starting at higher ambient temperature (in altitudes above 2.5 km (8202 ft)) Starting Storage battery; ISA
altitude
of up to 4 km (13123 ft)
730 when starter is
switched on minimum
-20 below
0 °C (+32 °F) 45 sec due to ITT exceeding start the engine using the emergency circuit.
In-flight
(starter + autorotation) 730 18 max. 0.35
Ground idle 550 60 + 3 With increasing flight altitude the idling speed
increases automatically.
Max. continuous 490
(657) 690 max. 97 max. 2080 +20 to +85
Take-off 560
(751) 735 max. 100 2080 max. 100 at nG ≥ 80% 5 min -50 to +50
(-58 to +122) At take-off short-time torque increase up to 106 % is acceptable.
Take-off with water injection 2) 560
(751) 735 max. 100 2080 0.18 to 0.27 5 min
Maximum contingency 595
(798) 780 max. 102 2080 max. 106.5 +20 to +95 10 min Both ratings are exclusively defined for the event of one engine inoperative (OEI) flight.
Intermediate contingency 560
(751) 760 max. 100 2080 max. 100 3) Application of both ratings is described in the Operation
Manual in section Emergency Procedures.
Acceleration
Acceleration period from flight idle up to 95 % of take-off power is max. 5 sec when displacing ECL in 1 sec.
Steady run within max. 6 sec.
For ISA altitude above 4 km
(13123 ft) 3 peaks until When the emergency circuit is
on
max. 2200 min. 6
BETA Control (on ground only)
710 max. 97 max. 1900 max. 100 min. 0.12
at nG ≥ 80 % 1 min At ambient conditions different from ISA H = 0 km (0 ft), V =0 km/hr (0 kt), the gas generator speed and the shaft power are controlled for fuel flow rate constant.
Maximal values when emergency
circuit is on 560
(751) 710 max. 99 max. 2080 max. 100 0.18 to 0.27
2 hrs Atmospheric conditions: Max. ISA flight altitude of 6.1 km (20013 ft);
full operational ability in severe ice-forming conditions.
Run-down: Minimum run-down from idle speed is 18 sec.
Oil: Oil consumption 0.1 litre/hr (0.0264 US gal/hr). At negative load factors, falls and side slips oil leakage through the oil separator up to 0.5 litre/hr (0.132 US gal/hr) is acceptable. Check the oil quantity after landing.
At negative load factors a pressure drop to zero within 5 sec and pressure recovery in following 5 sec is acceptable. Due to the oil pressure drop short-time propeller speed drop and oscillations in indicated torque can occur.
Fuel: Fuel system inlet pressure 0.07 to 0.3 MPa abs. (at booster pump switched off 0.05 MPa abs. as minimum).
WARNING: AT OIL PRESSURE OF 0.12 TO 0.18 MPa AT GAS GENERATOR SPEED HIGHER THAN 80 % THE ENGINE CAN OPERATE UNTIL NEXT LANDING SUPPOSING THE OIL TEMPERATURE IS WITHIN THE NORMAL RANGE. BEFORE THE NEXT TAKE-OFF IT IS NECESSARY TO REPLACE THE FILTER CARTRIDGE (WHEN CLOGGED) OR TO REMOVE ANOTHER REASON OF THE OIL PRESSURE DROP. AT FURTHER OIL PRESSURE DROP TO LESS THAN 0.12 MPa DANGER OF THE ENGINE SEIZING IS IMPENDING. THE MINIMUM OIL QUANTITY SIGNALLER CAN BE USED ONLY FOR GROUND CHECKING WHEN THE ENGINE IS AT REST.
1) Flight idle speed is identical to acceleration datum speed at acceleration time test on the ground.
2) Refer to Operation Manual (Manual Part No. 0982404).
WALTER a.s.
MAINTENANCE MANUAL MANUAL PART No. 0982055
Table 2 72.01.02
Pages 19/20 Jul 1, 2003 Short-time fuel pressure drop at fuel system inlet to the atmospheric pressure is acceptable.
Inlet fuel temperature: max. +60 oC (max. +140 oF). 3) Time necessary for finishing of the flight.
WALTER a.s.
MAINTENANCE MANUAL MANUAL PART No. 0982055
Table 2 72.01.02
placement Oil Power
rating Ambient
temperature NOTE
kW
External power source; ISA
alt. of up to 4 km (13123 ft) 700 minimum speed For ambient air
temperature In case of interrupted starting at higher ambient temperature (in altitudes above 2.5 km (8202 ft)) Starting Storage battery; ISA
altitude
of up to 4 km (13123 ft)
730 when starter is
switched on minimum
-20 below
0 °C (+32 °F) 45 sec due to ITT exceeding start the engine using the emergency circuit.
In-flight
(starter + autorotation) 730 18 max. 0.35
Ground idle 550 60 + 3 With increasing flight altitude the idling speed
increases automatically.
(-58 to +122) At take-off short-time torque increase up to 106 % is acceptable.
Take-off with water injection 2) 560
(751) 735 max. 100 2080 0.18 to 0.27 5 min
Max. take-off 595
(798) 780 max. 102 2080 max. 106.5 +20 to +95 5 min Both ratings are exclusively defined for the event of one engine inoperative (OEI) flight.
Max. continuos 560
(751) 760 max. 100 2080 max. 100 3) Application of both ratings is described in the Operation
Manual in section Emergency Procedures.
Acceleration
Acceleration period from flight idle up to 95 % of take-off power is max. 5 sec when displacing ECL in 1 sec.
Steady run within max. 6 sec.
For ISA altitude above 4 km
(13123 ft) 3 peaks until When the emergency circuit is
on
max. 2200 min. 6
BETA Control (on ground only)
710 max. 97 max. 1900 max. 100 min. 0.12
at nG ≥ 80 % 1 min At ambient conditions different from ISA H = 0 km (0 ft), V =0 km/hr (0 kt), the gas generator speed and the shaft power are controlled for fuel flow rate constant.
Maximal values when emergency
circuit is on 560
(751) 710 max. 99 max. 2080 max. 100 0.18 to 0.27
2 hrs Atmospheric conditions: Max. ISA flight altitude of 6.1 km (20013 ft);
full operational ability in severe ice-forming conditions.
Run-down: Minimum run-down from idle speed is 18 sec.
Oil: Oil consumption 0.1 litre/hr (0.0264 US gal/hr). At negative load factors, falls and side slips oil leakage through the oil separator up to 0.5 litre/hr (0.132 US gal/hr) is acceptable. Check the oil quantity after landing.
At negative load factors a pressure drop to zero within 5 sec and pressure recovery in following 5 sec is acceptable. Due to the oil pressure drop short-time propeller speed drop and oscillations in indicated torque can occur.
Fuel: Fuel system inlet pressure 0.07 to 0.3 MPa abs. (at booster pump switched off 0.05 MPa abs. as minimum).
WARNING: AT OIL PRESSURE OF 0.12 TO 0.18 MPa AT GAS GENERATOR SPEED HIGHER THAN 80 % THE ENGINE CAN OPERATE UNTIL NEXT LANDING SUPPOSING THE OIL TEMPERATURE IS WITHIN THE NORMAL RANGE. BEFORE THE NEXT TAKE-OFF IT IS NECESSARY TO REPLACE THE FILTER CARTRIDGE (WHEN CLOGGED) OR TO REMOVE ANOTHER REASON OF THE OIL PRESSURE DROP. AT FURTHER OIL PRESSURE DROP TO LESS THAN 0.12 MPa DANGER OF THE ENGINE SEIZING IS IMPENDING. THE MINIMUM OIL QUANTITY SIGNALLER CAN BE USED ONLY FOR GROUND CHECKING WHEN THE ENGINE IS AT REST.
1) Flight idle speed is identical to acceleration datum speed at acceleration time test on the ground.
2) Refer to Operation Manual (Manual Part No. 0982404).
WALTER a.s.
MAINTENANCE MANUAL MANUAL PART No. 0982055
Table 2 72.01.02
Pages 21/22 Jul 1, 2003 Short-time fuel pressure drop at fuel system inlet to the atmospheric pressure is acceptable.
Inlet fuel temperature: max. +60 oC (max. +140 oF). 3) Time necessary for finishing of the flight.