Boeing 727-200/200A Performance

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and is not intended to be used in real life. Attention VA's - you may post this file on your site for
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Compiled by Matt Zagoren

POWER SETTING CHARTS
727-200 Maximum Take-Off EPR
A/C BLEED ON No. 1 & 3 No. 2 A/C BLEED OFF ADD .02 EPR for No. 2 ENG.

PRESS OUTSIDE AIR TEMPERATURE - °F

ALT
1000 -40 60
FT to -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 to
-25 84
-1 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95 1.95

SL 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00 2.00

1 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.05 2.03 2.01 2.00
2 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.09 2.07 2.05 2.03 2.01 2.00
3 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.14 2.12 2.10 2.09 2.07 2.05 2.03 2.01 2.00

4 2.21 2.21 2.21 2.21 2.21 2.20 2.18 2.17 2.15 2.14 2.12 2.10 2.09 2.07 2.05 2.03 2.01 2.00
5
AND 2.26 2.25 2.24 2.22 2.21 2.20 2.18 2.17 2.15 2.14 2.12 2.10 2.09 2.07 2.05 2.03 2.01 2.00
ABOVE
Use this table above 84° F at all altitudes.
OAT
90 95 100 105 110 115 120
DEG F
EPR 1.97 1.94 1.91 1.89 1.86 1.84 1.81
Use of No. 2 engine A/C bleed is not authorized.

ADJUSTMENTS

• Engine A/C Bleed Off 1 & 3 - add .04

• Engine Anti-Icing ON

o No. 1 & 3 No Correction

o No. 2 - Subtract .03

Standard thrust takeoffs are SOP, except where not authorized as noted below and subject to other
conditions when the Captain elects to use maximum take-off power.

Takeoff with Standard Power is not authorized:

• With tailwind.

• With anti-skid inoperative.

• With wet snow, slush, ice or standing water on the runway.

• With tailskid locked in an extended position.

• With engine anti-icing on.
• With any EPR gauge inoperative.
2
 • With "mixed" engines.
• For runways covered by Temporary Airport Analysis unless otherwise specified in TPS print-
out.

• If existing temperature is within 10° F of Maximum Allowable Temperature derived from

Airport Analysis.
• If actual TOGW is greater than the assumed TOGW.
• For any runway that Flight Manual Part II calls for the use of maximum power.
• When ambient temperature is below -4 F.

Take-Off N1, Use if EPR Gauge is Inoperative

A/C BLEED ON 1 & 3 only. DO NOT BLEED No. 2 Engine for Take-Off

PRESS
ALT OUTSIDE AIR TEMPERATURE - °F
1000
FT. -40 -30 -20 -10 0 10 20 30 40 50 60 65 70 75 80 85 90 95 100 105 110 120

-1 82.2 83.2 84.2 85.1 86.1 87.0 87.9 88.8 89.7 90.6 91.5 92.0 92.4 92.8 93.2 93.7 94.1 94.2 93.7 93.3 92.9 92.0
SL 83.5 84.5 85.5 86.5 87.4 88.3 89.3 90.2 91.1 92.0 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0

1 85.4 86.4 87.3 88.3 89.2 90.2 91.1 92.0 92.9 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0
2 86.8 87.8 88.9 89.9 90.9 91.9 92.8 93.8 93.6 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0

3 88.4 89.5 90.5 91.5 92.5 93.5 94.0 93.8 93.6 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0
4 90.1 91.2 92.3 93.3 94.0 94.0 94.0 93.8 93.6 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0

5
92.0 93.1 93.7 93.9 94.0 94.0 94.0 93.8 93.6 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0
5660
&
93.2 93.5 93.7 93.9 94.0 94.0 94.0 93.8 93.6 93.3 93.0 93.4 93.9 94.3 94.7 95.0 94.6 94.2 93.7 93.3 92.9 92.0
ABOVE

ADJUSTMENTS:
ENGINE ANTI-ICE ON - No. 1 & 3, ADD 0.7% - No. 2, ADD 0.2%

3
Climb EPR
NOTE: N1 RPM may be used for initial climb power setting if desired; use 92% when TAT is below 0° C and 90% when
TAT is above 0° C. Use tables below to obtain final climb EPR settings.
ENGINES NO. 1 & NO. 3, A/C BLEED ON, ANTI-ICING OFF
TAT
PRESS
°C -40 -30 -20 -10 0 10 20 30 40
ALT - FT
-50
S.L. 1.97 1.97 1.88 1.81 1.75 1.70
1500 2.05 2.05 1.98 1.88 1.81 1.75 1.70
2000 2.08 2.08 1.98 1.88 1.81 1.75 1.70
4000 2.19 2.14 2.08 1.98 1.88 1.81 1.75 1.70
5660-
2.27 2.23 2.19 2.14 2.08 1.98 1.88 1.81 1.75 1.70
25000
30000 2.25 2.21 2.17 2.12 2.06 1.96 1.86
39000 2.23 2.19 2.15 2.10 2.04 1.94 1.84

ENGINES NO. 2, A/C BLEED OFF, ANTI-ICING OFF

PRESS TAT
ALT - °C -40 -30 -20 -10 0 10 20 30 40
FT -50
S.L. 2.00 2.00 1.91 1.84 1.78 1.72
1500 2.07 2.00 2.00 1.91 1.84 1.78 1.72
2000 2.10 2.10 2.01 1.91 1.84 1.78 1.72
4000 2.22 2.17 2.10 2.01 1.91 1.84 1.78 1.72
5660-
2.31 2.27 2.23 2.17 2.10 2.01 1.91 1.84 1.78 1.72
39000

4
TAKEOFF CHARTS
727-200 Takeoff Vspeeds
V1 - Vr - V2 Speeds
PRESS ALT
OUTSIDE AIR TEMPERATURE - °F
1000 FT
9 to 10 -66 to -18 -17 to 33 34 to 91
7 to 9 -65 to -38 -37 to 12 13 to 54 55 to 104
5 to 7 -65 to 2 3 to 40 41 to 96 97 to 120
3 to 5 -65 to 32 33 to 88 89 to 112
1 to 3 -65 to 84 85 to 104 105 to 120
-1 to 1 -65 to 100 101 to 120
WEIGHT
V1 Vr V2 V1 Vr V2 V1 Vr V2 V1 Vr V2
FLAPS 1000 LB
110,000 104 127 106 125 108 124 109 123
120 110 131 112 130 114 128 115 127
130 116 135 118 134 119 133 121 132
140 122 139 123 138 125 137 126 136
150 127 143 129 142 130 141 132 140
15° 160 132 147 134 146 135 145 136
170 137 151 139 150 140 149 142
180 142 155 143 154 145
190
147 149 150
200 &
152 153
above
110,000 97 119 99 118 101 117 102 116
120 103 123 105 122 106 121 108 120
130 109 127 110 126 112 125 113 124
140 114 131 116 130 117 129 118 128
150 119 135 121 134 122 133 123
25° 160 124 139 125 138 127 137 128
170 129 142 130 142 132
180 133 146 134 145 137
190
139 140
200 &
144 144
above
110,000 109 133 111 132 113 131 115 130
120 116 135 118 137 120 136 122 135
130 122 143 124 142 126 141 128 140
140 128 147 130 146 132 146 134 145
150 134 152 136 151 138 150 140 150
5° 160 140 156 142 155 143 155 144
170 145 161 147 160 149 159 150
180 150 165 152 164 153
190 155 157 158
200 & above 160 162

5
CRUISE CHARTS
727-200 Low Altitude Cruise
Based On
250 KIAS to 10,000 Ft.
350 KIAS above 10,000 Ft.

PRESS STD IAS STD GROSS WEIGHT - 1000 LBS

ALT TAS KTS SAT
1000' KTS °C 175 170 165 160 155 150 145 140 135 130 125 120 115 110

1.76 1.75 1.74 1.73 1.72 1.71 1.70 1.69 1.69 1.68 1.67 1.66 1.66 1.65
23 484 350 -31
42.0 42.5 43.0 43.4 43.9 44.3 44.8 45.2 45.6 46.1 46.5 46.9 47.3 47.7
1.70 1.69 1.68 1.67 1.67 1.66 1.65 1.64 1.64 1.63 1.62 1.62 1.61 1.60
21 470 350 -27
41.1 41.5 41.9 42.3 42.7 43.1 43.5 43.9 44.3 44.6 45.0 45.4 45.7 46.1
1.65 1.65 1.64 1.63 1.62 1.61 1.61 1.60 1.59 1.59 1.58 1.58 1.57 1.56
19 456 350 -23
39.9 40.2 40.6 41.0 41.3 41.7 42.0 42.3 42.7 43.0 43.3 43.7 44.0 44.3
1.61 1.61 1.60 1.59 1.58 1.58 1.57 1.56 1.56 1.55 1.55 1.54 1.53 1.53
17 444 350 -19
38.4 38.8 39.2 39.5 39.9 40.2 40.5 40.9 41.2 41.5 41.8 42.1 42.4 42.7
1.57 1.57 1.56 1.55 1.55 1.54 1.53 1.53 1.52 1.52 1.51 1.50 1.50 1.49
15 431 350 -15
37.1 37.4 37.8 38.1 38.4 38.7 39.0 39.3 39.6 39.9 40.2 40.5 40.7 41.0
1.53 1.53 1.52 1.51 1.51 1.50 1.50 1.49 1.49 1.48 1.48 1.47 1.47 1.46
13 419 350 -11
35.7 36.0 36.3 36.6 36.9 37.2 37.5 37.7 38.0 38.3 38.5 38.8 39.1 39.3
1.49 1.49 1.48 1.48 1.47 1.47 1.46 1.46 1.45 1.45 1.44 1.44 1.43 1.43
11 407 350 -7
34.4 34.6 34.2 35.2 35.4 35.7 36.0 36.2 36.5 36.7 37.0 37.2 37.4 37.7
1.38 1.37 1.36 1.35 1.34 1.33 1.31 1.30 1.29 1.28 1.28 1.27 1.26 1.25
9 285 250 -3
38.7 39.2 39.7 40.2 40.7 41.1 41.6 42.0 42.5 43.0 43.4 43.8 44.3 44.7
1.36 1.35 1.33 1.32 1.31 1.30 1.29 1.28 1.27 1.26 1.25 1.24 1.23 1.22
7 276 250 1
36.8 37.2 37.7 38.1 38.6 39.0 39.5 39.9 40.3 40.7 41.2 41.6 42.0 42.4
1.33 1.32 1.31 1.30 1.29 1.28 1.27 1.26 1.25 1.24 1.23 1.22 1.21 1.20
5 268 250 5
35.0 35.4 35.9 36.3 36.7 37.1 37.5 37.9 38.3 38.7 39.1 39.5 39.9 40.2
1.30 1.29 1.28 1.27 1.26 1.25 1.24 1.23 1.22 1.21 1.21 1.20 1.19 1.18
3 261 250 9
33.4 33.8 34.2 34.5 34.9 35.3 35.7 36.1 36.4 36.8 37.2 37.5 37.9 38.2
EPR Required
Specific Range (NM/1000 lbs)

Fuel consumption (1000 pound/hour) = TAS for actual temperature / (NAM/1000 pounds)

6
727-200 Mach .78 Cruise
M Indicated = M True

PRESS STD IAS STD GROSS WEIGHT - 1000 LBS

ALT TAS KTS SAT
1000' KTS °C 175 170 165 160 155 150 145 140 135 130 125 120 115 110

2.09 2.04 1.99 1.95 1.91 1.88

39 447 241 -57
58.5 61.4 64.3 67.1 69.9 72.6
2.11 2.06 2.01 1.97 1.93 1.90 1.87 1.84 1.82
37 447 252 -57
52.4 54.9 57.3 59.6 61.9 64.2 66.4 68.6 70.7
2.11 2.06 2.02 1.98 1.95 1.91 1.89 1.86 1.83 1.81 1.79 1.77
35 450 264 -54
47.7 49.7 51.7 53.6 55.5 57.4 59.3 61.1 62.9 64.6 66.3 68.0
2.06 2.02 1.98 1.95 1.92 1.89 1.87 1.85 1.82 1.80 1.79 1.77 1.75 1.74
33 454 277 -50
45.5 47.1 48.7 50.3 51.9 53.4 54.9 56.4 57.9 59.3 60.7 62.1 63.4 64.8
1.95 1.92 1.90 1.87 1.85 1.83 1.81 1.79 1.78 1.76 1.75 1.73 1.72 1.71
31 458 289 -46
46.0 47.3 48.6 49.9 51.1 52.3 53.5 54.7 55.8 57.0 58.1 59.2 60.3 61.3
1.87 1.85 1.83 1.82 1.80 1.78 1.77 1.76 1.74 1.73 1.72 1.71 1.69 1.68
29 462 302 -42
45.6 46.6 47.6 48.6 49.6 50.6 51.5 52.5 53.4 54.3 55.2 56.1 56.9 57.8
1.82 1.80 1.79 1.77 1.76 1.75 1.74 1.72 1.71 1.70 1.69 1.68 1.67 1.66
27 466 315 -38
44.4 45.3 46.1 46.9 47.7 48.4 49.2 50.0 50.7 51.4 52.2 52.9 53.6 54.2
1.77 1.76 1.75 1.74 1.73 1.72 1.71 1.70 1.69 1.68 1.67 1.66 1.66 1.65
25 470 329 -35
42.9 43.6 44.2 44.9 45.5 46.1 46.7 47.3 47.9 48.5 49.1 49.7 50.2 50.8
1.74 1.73 1.72 1.71 1.70 1.69 1.69 1.68 1.67 1.66 1.66 1.65 1.64 1.63
23 474 342 -31
41.1 41.6 42.1 42.7 43.2 43.7 44.2 44.7 45.2 45.6 46.1 46.6 47.0 47.5
EPR Required
Specific Range (NM/1000 lbs)

Fuel consumption (1000 pound/hour) = TAS for actual temperature / (NAM/1000 pounds)
SAT °C 0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -55 -60 -65 -70
TAT °C 32 27 21 16 10 4 -1 -7 -13 -18 -23 -29 -35 -41 -46
Use table above to determine altitude capability at M.78 by:

1. Estimate SAT for desired altitude by noting deviation from standard temperature at present altitude.

2. Enter SAT °C/TAT °C table with SAT and read anticipated TAT.

3. Compare anticipated TAT to TAT on the cruise table at desired altitude and top-of-climb gross weight.

4. Mach .78 can be achieved if anticipated TAT is equal or cooler than cruise table TAT. If anticipated TAT is
warmer, altitude is achievable but Mach .78 is not.

7
727-200 Mach .80 Cruise
M True = M Indicated

PRESS STD IAS STD GROSS WEIGHT - 1000 LBS

ALT TAS KTS SAT
1000' KTS °C 175 170 165 160 155 150 145 140 135 130 125 120 115 110

2.11 2.06 2.01 1.97 1.93 1.90

39 459 248 -57
58.7 61.2 63.6 66.0 68.4 70.7
2.12 2.07 2.03 1.99 1.95 1.92 1.89 1.86 1.84
37 459 260 -57
53.1 55.2 57.2 59.2 61.1 63.0 64.9 66.8 68.8
2.12 2.08 2.04 2.00 1.97 1.93 1.91 1.88 1.85 1.83 1.81 1.79
35 461 272 -54
48.7 50.3 52.0 53.6 55.2 56.8 58.4 59.9 61.4 62.9 64.4 65.9
2.07 2.03 2.00 1.97 1.94 1.91 1.89 1.87 1.84 1.82 1.81 1.79 1.77 1.76
33 465 285 -50
46.4 47.7 49.1 50.4 51.7 53.0 54.3 55.5 56.8 58.0 59.2 60.4 61.6 62.7
1.97 1.94 1.92 1.89 1.87 1.85 1.83 1.81 1.80 1.78 1.77 1.76 1.74 1.73
31 470 297 -46
46.4 47.4 48.5 49.5 50.6 51.6 52.6 53.6 54.6 55.6 56.5 57.5 58.4 59.4
1.89 1.87 1.85 1.84 1.82 1.80 1.79 1.78 1.76 1.75 1.74 1.73 1.72 1.70
29 474 311 -42
45.5 46.4 47.3 48.1 48.9 49.7 50.6 51.4 52.1 52.9 53.7 54.5 55.2 55.9
1.84 1.82 1.81 1.79 1.78 1.77 1.76 1.75 1.74 1.73 1.71 1.70 1.69 1.68
27 478 324 -38
44.2 44.9 45.6 46.3 46.9 47.6 48.2 48.9 49.5 50.1 50.7 51.4 52.0 52.6
1.79 1.78 1.77 1.76 1.75 1.74 1.73 1.72 1.71 1.70 1.69 1.68 1.68 1.67
25 482 338 -35
42.5 43.1 43.6 44.2 44.7 45.2 45.8 46.3 46.8 47.3 47.8 48.3 48.8 49.3
EPR Required
Specific Range (NM/1000 lbs)

Fuel consumption (1000 pound/hour) = TAS for actual temperature / (NAM/1000 pounds)
SAT
0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -55 -60 -65 -70 -75
°C
TAT
34 29 23 18 12 6 1 -5 -10 -16 -22 -27 -33 -39 -44 -50
°C
Use table above to determine altitude capability at M.80 by:

1. Estimate SAT for desired altitude by noting deviation from standard temperature at present altitude.

2. Enter SAT °C/TAT °C table with SAT and read anticipated TAT.

3. Compare anticipated TAT to TAT on the cruise table at desired altitude and top-of-climb gross weight.

4. Mach .80 can be achieved if anticipated TAT is equal or cooler than cruise table TAT. If anticipated TAT is
warmer, altitude is achievable but Mach .80 is not.

DESCENT CHART
Normal Descent
Based On:
• Sufficient thrust for pressurization requirements to maintain an approximate 300 fpm cabin
rate of descent.

• M.80 to FL 232

• 350 kts from FL 232 to 10,000 feet.

8
 • 250 kts or less below 10,000 feet.
• Clean configuration above 2,000 feet.

• Distance, time and fuel values include allowance for normal vectoring, approach and
landing.

TO SEA LEVEL
PRESS
ALT AVG
DIST TIME * FUEL
TAS
NM MINS LBS.
KTS
41000 338 133 23.6 1711
39000 334 127 22.8 1684
37000 329 121 22.1 1654
35000 324 115 21.3 1622
33000 318 109 20.6 1588
31000 312 104 19.9 1552
29000 306 98 19.2 1513
27000 300 93 18.6 1474
25000 293 88 18.0 1436
23000 287 83 17.4 1399
21000 278 78 16.7 1355
19000 269 72 16.0 1308
17000 259 66 15.2 1259
15000 249 60 14.4 1210
13000 238 54 13.7 1162
11000 227 49 12.9 1112
9000 203 36 10.6 1019
7000 193 30 9.4 974
5000 182 25 8.2 924
3000 165 18 6.5 848
*Fuel consumed during descent has been included in original flight plan; therefore, do not add fuel from above table to
computed fuel requirement.

NOTE:
Descent speeds have been picked as the most desirable considering economy and operational requiremets. If
turbulence is encountered, the turbulence penetration speeds should be used instead of normal descent speeds.

9
LANDING CHARTS
727-200 Vref and Stall Speeds

10