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RRPM for ambient temperatures of –20
C and below.
7-7-4. Performance Penalties with EAPS.
The engine performance loss with EAPS installed is
shown in table 7-7-1. The corrections shown in the table
are to be applied to the applicable to the applicable performance
data shown on Chapter 7.
TM 1-1520-240-10
7-7-2
Table 7-7-1 EAPS Penalty Table
Pressure
OAT
Increase Total
Fuel Flow By
Decrease Torque Available (%)
Altitude (ft)
(
C)
(lb/hr) KTAS = 0 85 135 160
Sea Level -50 40 0 0 0 0
-40 40 0 0 0 0
-30 40 0 0 0 0
-20 40 0 0 0 0
-10 40 0 0 0 0
0 40 0 0 0 0
10 40 0 0 0 0
20 40 0 0 3 5
30 40 2 3 6 8
40 40 2 3 6 8
50 40 2 3 6 8
2000 -50 40 0 0 0 0
-40 40 0 0 0 0
-30 40 0 0 0 0
-20 40 0 0 0 0
-10 40 0 0 0 0
0 40 0 0 0 0
10 40 0 0 3 5
20 40 2 3 6 9
30 40 2 3 6 8
40 40 2 3 6 8
50 40 2 3 6 8
4000 -50 40 0 0 0 0
-40 40 0 0 0 0
-30 40 0 0 0 0
-20 40 0 0 0 0
-10 40 0 0 0 0
0 40 0 0 0 0
10 40 2 3 6 9
20 40 2 3 6 9
30 40 2 3 6 8
40 40 2 3 6 8
50 40 2 3 6 8
TM 1-1520-240-10
7-7-3
Table 7-7-1 EAPS Penalty Table (Continued)
Pressure
OAT
Increase Total
Fuel Flow By
Decrease Torque Available (%)
Altitude (ft)
(
C)
(lb/hr) KTAS = 0 85 135 160
6000 -50 35 2 2 5 6
-40 35 2 2 3 4
-30 35 1 0 1 2
-20 35 0 1 5 8
-10 35 2 3 7 9
0 35 2 3 7 9
10 35 2 3 6 9
20 35 2 3 6 9
30 35 2 3 6 8
40 35 2 3 6 8
50 35 2 3 6 8
8000 -50 35 2 2 5 6
-40 35 2 2 4 6
-30 35 2 2 4 6
-20 35 2 3 7 10
-10 35 2 3 7 9
0 35 2 3 7 9
10 35 2 3 6 9
20 35 2 3 6 9
30 35 2 3 6 8
40 35 2 3 6 8
50 35 2 3 6 8
10000 -50 30 2 2 5 6
-40 30 2 2 4 6
-30 30 2 2 4 6
-20 30 2 3 7 10
-10 30 2 3 7 10
0 30 2 3 7 9
10 30 2 3 6 9
20 30 2 3 6 9
30 30 2 3 6 8
40 30 2 3 6 8
50 30 2 3 6 8
TM 1-1520-240-10
7-7-4
Table 7-7-1 EAPS Penalty Table (Continued)
Pressure
OAT
Increase Total
Fuel Flow By
Decrease Torque Available (%)
Altitude (ft)
(
C)
(lb/hr) KTAS = 0 85 135 160
12000 -50 30 2 2 5 6
-40 30 2 2 4 6
-30 30 2 2 4 6
-20 30 2 3 7 10
-10 30 2 3 7 9
0 30 2 3 7 9
10 30 2 3 6 9
20 30 2 3 6 9
30 30 2 3 6 8
40 30 2 3 6 8
50 30 2 3 6 8
14000 -50 30 2 2 5 6
-40 30 2 2 4 6
-30 30 2 2 4 6
-20 30 2 3 7 10
-10 30 2 3 7 9
0 30 2 3 7 9
10 30 2 3 6 9
20 30 2 3 6 9
30 30 2 3 6 8
40 30 2 3 6 8
50 30 2 3 6 8
16000 -50 30 2 2 5 6
-40 30 2 2 4 6
-30 30 2 2 4 6
-20 30 2 3 7 10
-10 30 2 3 7 9
0 30 2 3 7 9
10 30 2 3 6 9
20 30 2 3 6 9
30 30 2 3 6 8
40 30 2 3 6 8
TM 1-1520-240-10
7-7-5
Table 7-7-1 EAPS Penalty Table (Continued)
Pressure
OAT
Increase Total
Fuel Flow By
Decrease Torque Available (%)
Altitude (ft)
(
C)
(lb/hr) KTAS = 0 85 135 160
18000 -50 25 2 2 5 6
-40 25 2 2 4 6
-30 25 2 2 4 6
-20 25 2 3 7 10
-10 25 2 3 7 9
0 25 2 3 7 9
10 25 2 3 6 9
20 25 2 3 6 9
20000 -50 25 2 2 5 6
-40 25 2 2 4 6
-30 25 2 2 4 6
-20 25 2 3 7 10
-10 25 2 3 7 9
0 25 2 3 7 9
10 25 2 3 6 9
20 25 2 3 6 9
TM 1-1520-240-10
7-7-6
CRUISE EXAMPLE
EXAMPLE 1 (DUAL ENGINE)
WANTED:
SPEED FOR MAXIMUM ENDURANCE
SPEED FOR MAXIMUM RANGE
MAX. SPEED AT CONTINUOUS TORQUE RATING
ESTIMATED AIRSPEED LIMIT WITH CRUISE
GUIDE INDICATOR OPERATIVE
KNOWN:
GROSS WEIGHT = 50,000 LB.
PRESSURE ALTITUDE = SEA LEVEL
FAT = 30
C
METHOD:
READ SPEEDS WHERE GROSS WEIGHT LINE
INTERSECTS PERFORMANCE OR LIMIT LINE
MAXIMUM ENDURANCE: TAS = 89 KN, IAS = 83
MAXIMUM RANGE: TAS = 144 KN, IAS = 140 KN
(REQUIRES POWER IN EXCESS OF MAX
CONTINUOUS POWER)
MAX SPEED (CONTINUOUS TORQUE RATING):
TAS = 130 KN, IAS = 127 KN
ESTIMATED AIRSPEED LIMIT (VCGI): 152 KN
IAS = 148 KN
EXAMPLE 2 (DUAL ENGINE)
(DASH LINE)
WANTED:
TORQUE REQUIRED FOR LEVEL FLIGHT, FUEL
FLOW, AND INDICATED AIRSPEED AT TAS = 120
KN.
KNOWN:
GROSS WEIGHT = 45,000 LB.
PRESSURE ALTITUDE = SEA LEVEL
FAT = 35
C
TRUE AIRSPEED = 120KN
METHOD 1 (SIMPLEST)
USE NEXT HIGHER TEMPERATURE (40
C)
ENTER TAS, MOVE RIGHT TO GROSS WEIGHT
MOVE DOWN READ TORQUE REQ’D = 55%
　
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