flight planning and performance manual - · pdf fileflight planning and performance manual ......

FLIGHT PLANNING AND PERFORMANCE MANUAL

Takeoff and Landing........................................................................ Chapter 1 Flight Planning ................................................................................. Chapter 2 Enroute .............................................................................................. Chapter 3 Appendix ........................................................................................... Chapter 4

PERFORMANCE DATA FOR 727-200 JT8D-15

FAA LBS/°C

August 01, 2009 Copyright by Ralf M. Dittmer

Boeing 727-200 TAKEOFF AND LANDING Flight Planning and Performance Manual

September 01, 2009 727-200/JT8D-15 1.1

1.1 TAKEOFF AND LANDING-Text

TAKEOFF AND LANDING Chapter 1 Text ......................................................................................................................................................................... 3

Introduction......................................................................................................................................................... 3 Takeoff................................................................................................................................................................ 3 Landing ............................................................................................................................................................... 5 Airport Analysis.................................................................................................................................................. 5

Takeoff.................................................................................................................................................................... 7 Altimeter Setting to Station Pressure .................................................................................................................. 7 Wind Component ................................................................................................................................................ 8 Takeoff Field Corrections ................................................................................................................................... 9 Takeoff Field Limit ........................................................................................................................................... 10 Takeoff Climb Limit ......................................................................................................................................... 11 Slush/Standing Water Takeoff .......................................................................................................................... 12 Takeoff Speeds.................................................................................................................................................. 13 Takeoff EPR...................................................................................................................................................... 15 Takeoff N1 ........................................................................................................................................................ 16 Stab Trim Setting .............................................................................................................................................. 17

Landing ................................................................................................................................................................. 18 Landing Field Length Limit .............................................................................................................................. 18 Landing Climb Limit ........................................................................................................................................ 19 Landing Speeds ................................................................................................................................................. 20

Airport Analysis.................................................................................................................................................... 21 Sample .............................................................................................................................................................. 21

TAKEOFF AND LANDING Boeing 727-200 Flight Planning and Performance Manual

1.2 727-200/JT8D-15 September 01, 2009

Intentionally Blank


September 01, 2009 727-200/JT8D-15 1.3

Text

Introduction This chapter contains data to determine takeoff and landing performance limitations, based on engine bleed effects for normal air conditioning operation and antiice off, i.e., two packs on, one pack bleed from each engine. The data is presented in simplified form and is therefore conservative. In the event of any conflict between data presented in this section and those contained in the Approved Airplane Flight Manual, the Flight Manual shall always take precedence.

Takeoff The maximum brake release weight is the least of the field length, climb, and structural limit weights.

Altimeter Setting To Station Pressure The determination of thrust setting and takeoff/landing performance generally requires station pressure altitude. If station pressure or station pressure altitude are not available, enter the chart with altimeter setting (QNH) and read the pressure altitude adjustment. Apply this adjustment to the station elevation to obtain station pressure altitude. For boundary QNH values, read the midpoint between tabulated adjustments to elevation, e.g., for QNH of 29.66 inches (1004 mb), the elevation adjustment is 250 ft. Alternatively, station pressure altitude may be determined by setting the cockpit altimeter to 29.92 inches (1013.2 mb); the altimeter will then read station pressure altitude.

Wind Component The Wind Component chart provides crosswind and head/tail wind components, appropriate to the runway headings, reported wind velocity and direction. To use the chart, find the intersection between reported wind velocity in knots (circular lines) and the angle in degrees between reported wind direction and the runway (radial lines). Then read head/tail wind component to the left and crosswind component from the bottom scale.

Takeoff Field Corrections These tables provide corrections to the field length available for the effects of runway slope and wind component along the runway. Enter the Slope Correction table with the available field length and runway slope to determine the slope corrected field length. Now enter the Wind Correction table with slope corrected field length and wind component to determine the slope and wind corrected field length.

Takeoff Field Limit Maximum field length limited brake release weights are presented for one certified takeoff flap setting. The field length available is the amount of paved surface which may be used to accelerate to the decision speed and either stop at the end of the runway or climb to 35 ft. The field limited weight does not account for clearway or stopway. The reference takeoff condition is flap position 15, zero slope, and zero wind. To determine the field length limit brake release weight, enter the chart with OAT, move horizontally to airport pressure altitude and project a line vertically down. Now enter the chart with the Field Length corrected for wind and slope and move horizontally until the vertically line from the airport pressure altitude is intersected. At the intersection of both lines read the Field Length Limited Weight. Adjust the field length limit weight according to the notes below the chart to account for the appropriate engine bleed configuration.

Takeoff Climb Limit Maximum climb limited brake release weights are presented for one certified takeoff flap setting. The weights are limited by second segment climb performance and do not account for obstacles. To determine the climb limit weight, enter the chart with OAT, move vertically to airport pressure altitude. Move horizontally and read the climb limit weight to the left. Adjust the climb limit weight according to the notes below the chart to account for the appropriate engine bleed configuration.

Slush/Standing Water Takeoff Experience has shown that aircraft performance may deteriorate significantly on runways covered with snow, slush, standing water, or ice. Therefore a reduction in dry field length/obstacle limited takeoff weight and revised takeoff speeds is necessary. The information provided is intended for guidance in accordance with advisory


1.4 727-200/JT8D-15 September 01, 2009

material. The performance is based on an engine failure at the critical point during takeoff and a 15 ft. screen height at the end of the runway. Tables are provided for dispatch with all three thrust reversers operative. The entire runway is assumed to be completely covered by a contaminant of uniform thickness and density. Therefore this information is conservative when operating under typical colder weather conditions where patches of slush exist and some degree of sanding is common. Takeoffs in slush depths greater than 13mm (0.5 inches) are not recommended because of possible airplane damage as a result of slush impingement on the airplane structure. Maximum depths for slush, snow and standing water covering an appreciable part of the runway are as follows:

Takeoff Landing Slush or wet snow 0.5 inch (12 mm) 1 inch (25 mm) Standing water 0.25 inch (6 mm) 1 inch (25 mm) Dry snow 3.5 inch (90 mm) 3.5 inch (90 mm) The use of assumed temperature method for reduced thrust is not allowed on contaminated runways. Interpolation for slush/standing water depths between the values shown is permitted. Instructions for Using Tables:

1. Determine the field limit weight for the takeoff flap setting. 2. Enter the Weight Adjustment table with the pressure altitude and the corrected runway length to obtain

the weight reduction for the slush/standing water depth. 3. Reduce the field limit weight by the reduction shown.

Takeoff speeds determination:

1. Determine takeoff speeds V1, VR and V2 for actual brake release weight using the Takeoff Speeds table in this section.

2. Enter the Weight Adjustment table with the pressure altitude and the corrected runway length to obtain the speed reduction for the slush/standing water depth.

3. Reduce the V1 by the reduction shown.

Takeoff Speeds The speeds presented in the Takeoff Speeds table can be used for all performance conditions except where adjustments must be made to V1 for clearway, stopway, brake deactivation, improved climb, contaminated runway situations, unbalanced for brake energy or obstacle clearance with unbalanced V1. These speeds may be used for weights less than or equal to the performance limited weight. Normal takeoff speeds, V1, VR, and V2, with anti-skid on, are read from the table by entering with takeoff flap setting, brake release weight, and appropriate column.

Anti-Skid Inoperative For antiskid inoperative, the runway limited maximum takeoff weight at breake release and the V1 speed must be reduced to allow for the effect on accelerate stop performance as detailed in the FAA Approved Airplane Flight Manual. Enter the table with flap setting and read weight reduction. Enter table with flap setting and runway length and read speed reduction.

Dispatch with Tailskid Extended In order to compensate for the increased drag resulting from an extended tail skid, the following adjustments are recommended.

• Increase climb time, fuel and distance to cruise altitude by 25 percent. • Increase cruise fuel flows by 10 Percent (range reduction 10 percent). • Reduce thrust limited cruise weights by 20,000 lb.

Takeoff EPR To find Takeoff EPR based on normal engine bleed, enter Takeoff EPR Table with airport pressure altitude and airport OAT and read EPR. Apply adjustments as shown.


September 01, 2009 727-200/JT8D-15 1.5

Takeoff %N1 To find Max Takeoff %N1 based on normal engine bleed for air conditioning, 2 bleeds/2 packs, enter Takeoff %N1 Table with airport pressure altitude and airport OAT and read %N1. For packs off apply the %N1 adjustment shown below the table. No takeoff %N1 adjustment is required for engine or wing anti-ice.

Stab Trim Setting To find takeoff stabilizer trim setting, enter the Stab Trim Setting table with flap setting and center of gravity (C.G. % MAC) and read required stabilizer trim units.

Landing Charts are provided for determining the maximum landing weight as limited by field length or climb requirements for flap positions 30 and 40. Maximum performance landing weight is the smaller of the field length limit weight and climb limit weight; do not exceed maximum structural landing weight. Normally the flap setting for landing is 30 degrees. A flap 30 landing is required when the airport elevation is above 2000 ft. The use of flap 40 is recommended when landing under adverse conditions such as:

• Slippery Runway • Runway Length 7000 ft or less • Braking action reported less then good

Landing Field Length Limit To determine the landing field limit enter the table with gross weight and airport pressure altitude and read field length required.

Landing Climb Limit Enter table with OAT and airport pressure altitude and read climb limited gross weight.

Airport Analysis Airport Analysis for selected airports within the route network are presented in the appendix. The Airport Analysis Chart shows the Climb Limited Takeoff Weight as a function of the outside air temperature (OAT). The chart also shows the Field Limited, Obstacle Limited, Tire Speed Limited, and Brake Energy Limited Takeoff Weight as a function of both OAT and wind. For the field limited, obstacle limited, tire speed limited, and brake energy limited takeoff weights the associated takeoff speeds V1, VR, and V2 are also shown on the chart. The weight limtations are shown as LBSx1000 and to the speeds 100 must be added to obtain the takeoff speeds.

Limitation Codes Following Limitation Codes are used: F = FIELD, T = TIRE SPEED, B = BRAKE ENERGY, * = OBSTACLE, ** = IMPROVED CLIMB This codes are also shown on each chart.

Flap Setting All charts are calculated for a flap setting of 15 degress.

Chart Description The airport elevation is shown in the upper left corner followed by the airport name and the runway designation. On the bottom part of the chart the maximum structural limited weight, the runway length and the runway slope are presented. If a clearway and/or a stopway has been accounted for in the calculation the respective amaount is also shown. The four letter code and the three letter code for the airport are shown on the lower left side of the chart followed by the printing date.


1.6 727-200/JT8D-15 September 01, 2009

Determination of the Maximum Takeoff Weight The maximum takeoff weight limitation for the combination of airport, flap setting, temperature, runway and wind is the LESSER of the weights in steps A and B below. The Climb Limited Takeoff Weight and the Runway Limited Takeoff Weight are calculated separately because they are two different limitations (but neither one may exceed the structural limited takeoff weight). If the runway selected does not permit sufficient takeoff weight, consider the possibility of using a different runway. This will involve repeating step B for the new choice of runway. STEP A Enter the runway weight chart with the ambient temperature (°C) and proceed along the temperature line to the column labeled “CLIMB” and read the Climb Limited Weight. Correct the obtained weight for QNH as shown in the table to the right. STEP B Runway Limit – The next weight to be determined is the maximum takeoff weight for the particular runway to be used. Again enter the table with the ambient temperature. Proceed along the temperature line to its intersection with the column identified by the determinated head or tail wind component. Interpolate between two wind values if necessary. Read the runway limited weight. Correct the obtained weight for QNH as shown in the table to the right. The Maximum Takeoff Weight is the LESSER of the following weights:

- Structural Limited Takeoff Weight (MTOW) - Climb Limited Weight from step A - Runway Limited Weight form step B

QNH CORRECTION QNH corrections for the climb limited takeoff weight and the field limited takeoff weight are shown in the the following table.

QNH Limit above

1013 below 1013

Climb + 130 LBS - 130 LBS Field + 140 LBS - 140 LBS per 1 MBAR

EXAMPLE The following example demonstrate the use of the Airport Analysis Chart. Given: SAMPLEFIELD, Runway 07L, OAT = 30°C, Wind = 10 KN HW, and QNH = 1020.4 MBAR Find: Climb Limited Weight = 195000 LBS, QNH Correction = +962 LBS, Corrected Climb Limited Weight = 195962 LBS. Field Length Limited Weight = 172620 LBS, QNH Correction = 1561 LBS, Corrected Field Length Limited Weight = 174181 LBS. Structural Limited Weight = 190500 LBS. The lesser of this three weights is the field limited weigh, use this weight as the maximum takeoff weight. The takeoff speeds are obtained from the Airport Analysis Chart: V1 = 136 KN VR = 136 KN V2 = 149 KN


September 01, 2009 727-200/JT8D-15 1.7

Takeoff

Altimeter Setting to Station Pressure

QNH IN. HG. Correction to Elevation for Pressure Altitude QNH MILLIBARS

28.81 to 28.91 1000 976 to 979

28.91 to 29.02 900 979 to 983

29.02 to 29.12 800 983 to 986

29.12 to 29.23 700 986 to 990

29.23 to 29.34 600 990 to 994

29.34 to 29.44 500 994 to 997

29.44 to 29.55 400 997 to 1001

29.55 to 29.66 300 1001 to 1004

29.66 to 29.76 200 1004 to 1008

29.76 to 29.87 100 1008 to 1012

29.87 to 29.97 0 1012 to 1015

29.97 to 30.08 -100 1015 to 1019

30.08 to 30.19 -200 1019 to 1022

30.19 to 30.30 -300 1022 to 1026

30.30 to 30.41 -400 1026 to 1030

30.41 to 30.52 -500 1030 to 1034

30.52 to 30.63 -600 1034 to 1037

30.63 to 30.74 -700 1037 to 1041

30.74 to 30.85 -800 1041 to 1045

30.85 to 30.96 -900 1045 to 1048

30.96 to 31.07 -1000 1048 to 1052

Example : Elevation = 2500 FT QNH = 29.48 IN.HG. Correction = 400 FT Pressure Altitude = 2900 FT


1.8 727-200/JT8D-15 September 01, 2009

Wind Component


September 01, 2009 727-200/JT8D-15 1.9

Takeoff Field Corrections

Slope Corrected Field Length (FT)

Runway Slope (%) Field Length Available (FT)

-2 0 +2 5000 5400 5000 6000 6600 6000 5400 7000 7800 7000 6200 8000 8900 8000 7000 9000 10100 9000 7800 10000 11200 10000 8700 11000 12400 11000 9500 12000 13600 12000 10300 13000 13000 11000 14000 14000 11800

Corrected Field Length (FT) Wind Component (KTS)

Slope Corr’d Field Length

(FT) -10 0 20 40 5000 5000 5500 6100 6000 5100 6000 6600 7200 7000 6200 7000 7700 8400 8000 7000 8000 8800 9600 9000 7900 9000 9800 10600 10000 8700 10000 10900 11600 11000 9600 11000 12000 12800 12000 10500 12000 13000 14000 13000 11500 13000 14000 14000 12500 14000


1.10 727-200/JT8D-15 September 01, 2009

Takeoff Field Limit

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

23000

24000

25000

26000

27000

28000

29000

30000

-50

-45

-40

-35

-30

-25

-20

-15

-10

-5

0

5

10

15

20

25

30

35

40

45

50

Cor

rect

ed F

ield

Len

gth

- fee

t

2000 4000 6000 8000Pressure Altitude - feet 0

Gro

ss W

eigh

t - 1

000

LBS

LBS

130

140

150

160

170

180

190195

OA

T - °

C

Flaps 15

Example: For 25°C OAT, 2000 ft pressure altitude and 7000 ft Corrected Field Length, the Runway Limited Takeoff Weight is 160,000 lb.

BASED ON:- Anti-skid operative- A/C bleed ON- Autopack Trip Operative- Engine Failure Warning System Operative

CORRECTIONS:For Anti-Ice System ON reduce weight 1000 lb

&below


September 01, 2009 727-200/JT8D-15 1.11

Takeoff Climb Limit

130

135

140

145

150

155

160

165

170

175

180

185

190

195

200

10 15 20 25 30 35 40 45 50

FLAPS 152nd Segment Weight Limitation

Gro

ss W

eigh

t - 1

000

LBS

OAT - °C

Pressure Altitude - feet 0

100020003000

4000

5000

6000

7000

8000

Example: For 25°C OAT and 2000 feet pressure altitude, the 2nd Segment Limited Weight is 196,800 lb.

BASED ON:- A/C bleed ON- Autopack Trip Operative- Engine Failure Warning System Operative

CORRECTIONS:For Anti-Ice System ON reduce weight 2650 lb

& below


1.12 727-200/JT8D-15 September 01, 2009

Slush/Standing Water Takeoff 1/4 Inch Slush Corrections

Weight Reduction - pounds V1 Reduction - KTS Flaps 5 Flaps 15 Flaps 20,25 Flaps 5,15 Flaps 20,25

Runway Length

FT S.L. 4000 S.L. 4000 S.L. 4000 S.L. 4000 S.L. 4000 5000 12000 12000 15000 14000 16000 15000 33 33 32 31 7000 15000 13000 17000 16000 19000 18000 30 29 29 28 9000 17000 15000 20000 18000 21000 20000 29 27 27 27 11000 18000 16000 22000 20000 24000 22000 28 27 26 26 13000 20000 18000 24000 22000 - - 26 25 - -

1/2 Inch Slush Corrections

Weight Reduction - pounds V1 Reduction - KTS Flaps 5 Flaps 15 Flaps 20,25 Flaps 5,15 Flaps 20,25

Runway Length

FT S.L. 4000 S.L. 4000 S.L. 4000 S.L. 4000 S.L. 4000 5000 20000 20000 22000 21000 24000 22000 29 27 27 26 7000 22000 22000 26000 24000 28000 26000 26 25 25 25 9000 25000 23000 28000 26000 30000 28000 26 25 25 24 11000 27000 25000 30000 28000 32000 30000 26 25 25 24 13000 29000 27000 32000 30000 - - 26 26 - -


September 01, 2009 727-200/JT8D-15 1.13

Takeoff Speeds Press

Alt 1000 ft

OAT

°F -65 to -14 -13 to 33 34 to 86 9 to 10

°C -54 to -26 -25 to 0 1 to 30 °F - 65 to -36 -35 to 112 13 to 75 76 to 100

7 to 9 °C -54 to -38 -37 to -11 -10 to 24 25 to 38 °F 65 to 2 3 to 40 41 to 96 97 to 109

5 to 7 °C -54 to -17 -16 to 4 5 to 35 36 to 42 °F -65 to 32 33 to 88 89 to 112

3 to 5 °C -54 to 0 1 to 31 32 to 44 °F -65 to 84 85 to 104 105 to 120

1 to 3 °C -54 to 29 30 to 40 41 to 49 °F -65 to 100 101 to 120

-1 to 1 °C -54 to 38 39 to 49

WEIGHT FLAPS

lb V1 = VR V2 V1 = VR V2 V1 = VR V2 V1 = VR V2

210000 165 175 167 175 200000 159 170 161 170 190000 154 166 156 166 158 166 180000 148 161 150 161 152 161 5 170000 142 157 144 157 146 156 148 156 160000 137 151 138 151 140 156 142 150 150000 131 146 132 146 133 145 136 144 140000 128 143 129 143 129 142 131 142 130000 125 141 126 141 127 140 129 140 120000 119 136 120 135 121 134 122 133 210000 155 166 157 166 200000 150 161 152 161 190000 145 157 147 157 149 157 180000 139 152 141 152 143 152

15 170000 134 148 136 148 138 147 140 147 160000 129 143 130 143 132 143 134 142 150000 123 138 124 138 126 137 128 137 140000 121 137 122 136 123 135 125 134 130000 118 134 119 133 120 132 122 132 120000 112 128 113 128 114 127 115 126 210000 150 161 152 161 200000 145 157 147 157 190000 140 152 142 152 144 152 180000 135 148 137 148 139 148

20 170000 130 144 131 144 133 143 135 143 160000 125 139 126 139 128 138 130 138 150000 119 134 120 134 122 133 124 133 140000 116 131 117 131 118 130 120 130 130000 114 129 115 129 116 128 118 128 120000 109 124 109 124 110 123 111 122 210000 143 155 146 155 200000 141 152 143 152 190000 136 148 138 148 139 148 180000 130 144 132 144 134 144

25 170000 125 139 127 139 129 139 131 139 160000 120 135 122 135 124 134 125 134 150000 115 130 116 130 118 130 120 129 140000 112 128 113 127 114 127 116 127 130000 110 126 111 125 112 125 114 125 120000 105 121 106 120 106 120 107 119

SPEEDS NOT VALID WHEN WEIGHTS ARE PREDICATED ON USE OF CLEARWAY, STOWAY, IMPROVED CLIMB OR ARE LIMITED BY BRAKE ENERGY.


1.14 727-200/JT8D-15 September 01, 2009

Anti-Skid Inoperative

Flap Setting Weight Reduction – pounds 5° 4000

15° 6300 20° 8500 25° 10000

Flap Setting Runway Length - FT V1 Reduction – KTS

10000 13 5° 12000 14 6000 21 7000 18 8000 17 9000 16

15°

10000 15 7000 18 8000 16 9000 16 20°

10000 15 6000 21 7000 18 25° 8000 16


September 01, 2009 727-200/JT8D-15 1.15

Takeoff EPR

TAKEOFF EPR PRESS OAT °F -4 5 14 23 32 41 50 59 68 77 86 95 104 113 120

ALT °C -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 49 -1000 1 & 3 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.03 1.99 1.94 1.91

2 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.06 2.05 2.00 1.96 1.92S.L. 1 & 3 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.10 2.08 2.03 1.99 1.94 1.91

2 2.11 2.11 2.11 2.11 2.11 2.11 2.11 2.11 2.11 2.11 2.11 2.10 2.05 2.00 1.96 1.921000 1 & 3 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.13 2.12 2.12 2.11 2.08 2.03 1.99 1.94 1.91

2 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.15 2.13 2.13 2.12 2.10 2.05 2.00 1.96 1.922000 1 & 3 2.21 2.21 2.21 2.21 2.21 2.20 2.17 2.14 2.14 2.14 2.11 2.08 2.03 1.99 1.94 1.91

2 2.22 2.22 2.22 2.22 2.22 2.21 2.18 2.16 2.16 2.15 2.12 2.10 2.05 2.00 1.96 1.923000 1 & 3 2.26 2.26 2.26 2.25 2.23 2.20 2.17 2.14 2.14 2.14 2.11 2.08 2.03 1.99 1.94 1.91

2 2.28 2.28 2.28 2.27 2.24 2.21 2.18 2.16 2.16 2.15 2.12 2.10 2.05 2.00 1.96 1.923856 & 1 & 3 2.31 2.29 2.27 2.25 2.23 2.20 2.17 2.14 2.14 2.14 2.11 2.08 2.03 1.99 1.94 1.91ABOVE 2 2.32 2.31 2.29 2.27 2.24 2.21 2.18 2.16 2.16 2.15 2.12 2.10 2.05 2.00 1.96 1.92

ENG 1 & 3 ENG 2 EPR BLEED CORRECTIONS AIR CONDITIONING OFF +.04 - ENGINE A/I ON ZERO -0.3 IN SHADED AREA COLDER -0.3 -0.6 THAN 0°F (-18°C) MOD 'A' INLET - 0.1


1.16 727-200/JT8D-15 September 01, 2009

Takeoff N1 A/C BLEED ON

TAKEOFF N1 PRESS OAT - °C

ALT -54 -45 -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 49 -1000 83.2 84.8 85.7 86.5 87.4 88.3 89.2 90.1 91.0 91.9 92.7 93.5 94.3 95.2 95.9 96.7 97.5 98.1 97.2 96.3 95.6S.L. 84.7 86.3 87.2 88.1 89.1 90.0 90.9 91.8 92.7 93.6 94.4 95.3 96.1 96.9 97.8 98.5 99.0 98.1 97.2 96.3 95.61000 86.4 88.0 88.9 89.9 90.8 91.7 92.7 93.6 94.5 95.4 96.3 97.1 97.4 97.8 98.6 99.2 99.0 98.1 97.2 96.3 95.62000 88.1 89.8 90.8 91.7 92.7 93.6 94.6 95.5 96.4 97.3 97.9 97.8 97.7 98.5 99.2 99.2 99.0 98.1 97.2 96.3 95.63000 89.8 91.6 92.6 93.5 94.5 95.5 96.5 97.5 98.0 98.0 97.9 97.8 97.7 98.5 99.2 99.2 99.0 98.1 97.2 96.3 95.63856

& ABOVE

91.2 93.1 94.1 95.1 96.1 97.1 97.7 97.8 98.0 98.0 97.9 97.8 97.7 98.5 99.2 99.2 99.0 98.1 97.2 96.3 95.6

NO BLEED CORRECTION : + 1.3 % N1


September 01, 2009 727-200/JT8D-15 1.17

Stab Trim Setting

FLAPS 5 15 / 20 25 CG % UNITS AIRPLANE NOSE UP

10 6 3/4 7 1/2 8 1/4 12 6 1/2 7 1/4 8 14 6 1/4 7 7 3/4 16 6 6 3/4 7 1/2 18 5 3/4 6 1/2 7 20 5 1/2 6 6 1/2 22 5 5 3/4 6 1/4 24 4 3/4 5 1/4 5 3/4 26 4 1/2 4 3/4 5 1/4 28 4 4 1/2 4 3/4 30 3 3/4 4 4 1/4 32 3 1/2 3 3/4 4 34 3 1/4 3 1/4 3 1/2 36 2 3/4 3 3 38 2 1/2 2 1/2 2 1/2 40 2 1/2 2 1/2 2 1/2 42 2 1/2 2 1/2 2 1/2


1.18 727-200/JT8D-15 September 01, 2009

Landing

Landing Field Length Limit Field Limited Landing Weight Flaps 30

WEIGHT AIRPORT ELEVATION (FEET) 1000 LBS 0 1000 2000 3000 4000 5000 6000 7000 8000

Runway Length Required feet x 1000 110 4.140 4.200 4.270 4.340 4.420 4.510 4.600 4.700 4.800 115 4.240 4.310 4.380 4.460 4.540 4.640 4.730 4.830 4.930 120 4.350 4.420 4.500 4.580 4.670 4.770 4.860 4.960 5.060 125 4.460 4.540 4.630 4.710 4.810 4.900 5.000 5.100 5.210 130 4.580 4.670 4.760 4.850 4.950 5.050 5.150 5.250 5.360 135 4.710 4.800 4.900 4.990 5.090 5.190 5.300 5.410 5.520 140 4.840 4.940 5.040 5.140 5.250 5.350 5.460 5.570 5.690 145 4.970 5.090 5.200 5.300 5.400 5.510 5.620 5.740 5.870 150 5.120 5.240 5.360 5.460 5.570 5.680 5.790 5.910 6.050 155 5.260 5.400 5.520 5.630 5.740 5.850 5.960 6.090 6.250 160 5.420 5.570 5.700 5.810 5.920 6.030 6.150 6.280 6.450

Field Limited Landing Weight Flaps 40

WEIGHT AIRPORT ELEVALTION (FEET) 1000 LBS 0 1000 2000 3000 4000 5000 6000 7000 8000

Runway Length Required feet x 1000 110 4.000 4.100 4.100 4.270 4.350 4.440 4.530 4.640 4.770 115 4.150 4.240 4.310 4.420 4.510 4.610 4.710 4.820 4.950 120 4.300 4.390 4.490 4.580 4.680 4.780 4.880 5.000 5.130 125 4.450 4.550 4.640 4.740 4.850 4.950 5.070 5.190 5.320 130 4.610 4.710 4.810 4.910 5.020 5.130 5.250 5.380 5.510 135 4.760 4.870 4.980 5.090 5.200 5.320 5.440 5.570 5.700 140 4.920 5.040 5.150 5.270 5.390 5.510 5.640 5.760 5.900 145 5.030 5.210 5.330 5.460 5.580 5.710 5.830 5.960 6.100


September 01, 2009 727-200/JT8D-15 1.19

Landing Climb Limit Climb Limited Landing Weight Flaps 30

OAT AIRPORT ELEVATION (FEET) °F 0 1000 2000 3000 4000 5000 6000 7000 8000 Landing Climb Limited Weight pounds x 1000

50 160 160 160 160 160 160 160 160 160 55 160 160 160 160 160 160 160 160 160 60 160 160 160 160 160 160 160 160 160 65 160 160 160 160 160 160 160 160 160 70 160 160 160 160 160 160 160 160 160 75 160 160 160 160 160 160 160 160 160 80 160 160 160 160 160 160 160 160 160 85 160 160 160 160 160 160 160 160 160 90 160 160 160 160 160 160 160 160 158.6 95 160 160 160 160 160 160 160 160 155.5 100 160 160 160 160 160 160 160 157.9 151.9 105 160 160 160 160 160 160 159.7 153.7 147.9 110 160 160 160 160 160 160 154 149.1 143.5

Climb Limited Landing Weight Flaps 40

OAT AIRPORT ELEVATION (FEET) °F 0 1000 2000 3000 4000 5000 6000 7000 8000 Landing Climb Limited Weight pounds x 1000

50 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 55 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 60 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 65 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 70 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 75 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 80 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 85 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 141.6 90 142.5 142.5 142.5 142.5 142.5 142.5 142.5 142.5 139.3 95 142.5 142.5 142.5 142.5 142.5 142.5 142.5 141.7 136.6

100 142.5 142.5 142.5 142.5 142.5 142.5 142.5 133.5 133.5 105 142.5 142.5 142.5 142.5 142.5 142.5 140.2 134.9 129.9 110 142.5 142.5 142.5 142.5 142.5 141.3 136.1 130.9 126


1.20 727-200/JT8D-15 September 01, 2009

Landing Speeds

Flaps 30 Flaps 40

Weight Vref Weight Vref lb kn lb kn

160000 137 145000 126 155000 135 140000 123 150000 132 135000 121 145000 130 130000 119 140000 128 125000 117 135000 126 120000 114 130000 123 115000 112 125000 121 110000 109 120000 118 105000 107 115000 116 100000 104 110000 113 105000 111


September 01, 2009 727-200/JT8D-15 1.21

Airport Analysis

Sample ELEVATION 0 SAMPLEFIELD RUNWAY 07L ***FLAPS 15*** A/C ON 727-200 ADV JT8D-15 ENGINES 210 MPH TIRES OAT CLIMB WIND COMPONENT IN KNOTS (MINUS DENOTES TAILWIND) C 1000 LBS -10 0 20 40 44 183.7 145.3F/23-23-38 156.3F/28-28-42 164.2F/31-31-46 170.3F/34-34-48 42 185.3 147.0F/24-24-39 158.1F/29-29-43 166.0F/32-32-46 172.2F/35-35-49 40 186.9 148.6F/24-24-39 159.8F/29-29-44 167.7F/33-33-47 174.1F/36-36-50 38 188.5 150.3F/25-25-40 161.5F/30-30-45 169.5F/34-34-48 175.9F/37-37-51 36 190.1 152.0F/26-26-41 163.3F/31-31-45 171.3F/35-35-49 177.8F/38-38-51 34 191.7 153.7F/27-27-41 165.0F/32-32-46 173.1F/36-36-49 179.6F/39-39-52 32 193.3 155.4F/27-27-42 166.7F/33-33-47 174.9F/37-37-50 181.5F/40-40-53 30 195.0 157.0F/28-28-43 168.5F/34-34-47 176.7F/38-38-51 183.4F/41-41-54 28 196.6 158.7F/29-29-43 170.2F/34-34-48 178.5F/39-39-52 185.2F/42-42-55 26 198.2 160.4F/30-30-44 172.0F/35-35-49 180.3F/40-40-53 187.1F/43-43-56 24 199.8 162.1F/30-30-45 173.7F/36-36-50 182.1F/40-40-53 189.0F/44-44-57 22 201.5 163.8F/31-31-45 175.5F/37-37-50 184.0F/41-41-54 190.8F/45-45-57 20 203.1 165.5F/32-32-46 177.2F/38-38-51 185.8F/42-42-55 192.7F/46-46-58 18 204.7 167.2F/33-33-47 178.9F/39-39-52 187.6F/43-43-56 194.6F/47-47-59 16 205.6 168.5F/34-34-47 180.3F/40-40-53 189.0F/44-44-57 196.0F/48-48-60 14 205.6 169.4F/34-34-48 181.2F/40-40-53 189.8F/45-45-57 196.9F/48-48-60 12 205.6 170.2F/34-34-48 182.1F/40-40-53 190.7F/45-45-57 197.8F/49-49-61 10 205.6 171.1F/35-35-49 182.9F/41-41-54 191.6F/46-46-58 198.6F/49-49-61 8 205.6 172.0F/35-35-49 183.8F/41-41-54 192.5F/46-46-58 199.5F/50-50-62 6 205.6 172.9F/36-36-49 184.7F/42-42-55 193.4F/47-47-59 200.4F/50-50-62 4 205.6 173.8F/36-36-50 185.6F/42-42-55 194.2F/47-47-59 201.3F/51-51-62 2 205.6 174.6F/37-37-50 186.5F/43-43-55 195.1F/47-47-59 202.2F/51-51-63 0 205.6 175.5F/37-37-50 187.4F/43-43-56 196.0F/48-48-60 203.1F/52-52-63 -2 205.6 176.4F/38-38-51 188.2F/44-44-56 196.9F/48-48-60 203.9F/53-53-64 -4 205.6 177.3F/38-38-51 189.1F/44-44-57 197.8F/49-49-61 204.8F/53-53-64 -6 205.6 178.2F/38-38-52 190.0F/45-45-57 198.7F/49-49-61 205.7F/54-54-65 -8 205.6 179.1F/39-39-52 190.9F/45-45-57 199.5F/50-50-62 206.6F/54-54-65 -10 205.6 179.9F/39-39-52 191.8F/46-46-58 200.4F/50-50-62 207.5F/55-55-65 -12 205.6 180.8F/40-40-53 192.6F/46-46-58 201.3F/51-51-62 208.3F/55-55-66 -14 205.6 181.7F/40-40-53 193.5F/47-47-59 202.2F/51-51-63 209.2F/56-56-66 -16 205.6 182.6F/41-41-54 194.4F/47-47-59 203.1F/52-52-63 210.1F/56-56-67 -18 205.6 183.5F/41-41-54 195.3F/48-48-60 203.9F/53-53-64 211.0F/57-57-67 -20 205.6 184.3F/42-42-54 196.2F/48-48-60 204.8F/53-53-64 211.9F/57-57-68 -22 205.6 185.2F/42-42-55 197.1F/49-49-60 205.7F/54-54-65 212.8F/58-58-68 -24 205.6 186.1F/43-43-55 197.9F/49-49-61 206.6F/54-54-65 213.6F/58-58-69 -26 205.6 187.0F/43-43-56 198.8F/50-50-61 207.5F/55-55-65 214.5F/59-59-69 -28 205.6 187.9F/44-44-56 199.7F/50-50-62 208.4F/55-55-66 215.4F/59-59-69 -30 205.6 188.8F/44-44-56 200.6F/51-51-62 209.2F/56-56-66 216.3F/60-60-70 -32 205.6 189.6F/44-44-57 201.5F/51-51-62 210.1F/56-56-67 217.2F/60-60-70 -34 205.6 190.5F/45-45-57 202.3F/52-52-63 211.0F/57-57-67 218.0F/61-61-71 -36 205.6 191.4F/45-45-58 203.2F/52-52-63 211.9F/57-57-68 218.9F/61-61-71 -38 205.6 192.3F/46-46-58 204.1F/53-53-64 212.8F/58-58-68 219.8F/62-62-72 -40 205.6 193.2F/46-46-59 205.0F/53-53-64 213.6F/58-58-69 220.7F/63-63-72 MAX BRAKE RELEASE WEIGHT MUST NOT EXCEED STRUCTURAL LIMIT OF 190500 LBS MINIMUM FLAP RETRACTION HEIGHT IS 400 FT LIMIT CODE IS F = FIELD, T = TIRE SPEED, B = BRAKE ENERGY, * = OBSTACLE RUNWAY IS 8500 FT LONG WITH 0 FT CLEARWAY AND 0 FT STOPWAY RUNWAY SLOPE IS 0.00 PERCENT AND OBSTACLES CONSIDERED ARE - 250/25000 HERR/CHR 07-26-2009


1.22 727-200/JT8D-15 September 01, 2009

Intentionally Blank

Boeing 727-200 FLIGHT PLANNING Flight Planning and Performance Manual

September 01, 2009 727-200/JT8D-15 2.1


FLIGHT PLANNING Chapter 2 Text ......................................................................................................................................................................... 3

Introduction......................................................................................................................................................... 3 Simplified Flight Planning .................................................................................................................................. 3

Simplified Flight Planning ...................................................................................................................................... 4 Optimum Altitude ............................................................................................................................................... 4 Time-Fuel-Table ................................................................................................................................................. 5 Holding Planning ................................................................................................................................................ 7

FLIGHT PLANNING Boeing 727-200 Flight Planning and Performance Manual

2.2 727-200/JT8D-15 September 01, 2009

Intentionally Blank


September 01, 2009 727-200/JT8D-15 2.3

Text

Introduction This chapter contains flight planning data to determine trip fuel/time, reserve fuel and enroute terrain clearance capability. The data includes engine bleed effects for normal air conditioning operation.

Simplified Flight Planning

Flight Planning Allowances Simplified Flight Planning charts enable rapid determination of estimated trip time and fuel from brake release to landing. Additional flight planning information including maneuver allowances is summarized below.

Ground Operations Fuel can be saved by minimizing APU utilization. Average APU fuel flow rates under normal operation are 230 lbs per hour on the ground. Taxi fuel allowance is approximately 500 lbs.

Optimum Altitude Optimum altitude for best fuel mileage is presented for .78M speed schedule.

Time-Fuel-Table A Time-Fuel-Table is provided for .78M speed schedule at constant altitude to determine trip fuel and time from brake release to touchdown. APU usage, taxi, inflight flaps down maneuvering (other than straight in approach) and reserve fuel should be added to the trip fuel obtained from the trip fuel and time table to obtain the total fuel required. These fuel allowances are presented under Flight Planning Allowances. Additional fuel for extended inflight traffic delays should be determined from the holding table. The following example illustrates the use of the Time-Fuel-Table. Given: Distance = 500 NM Flight Level = 350 OAT = -49 °C Wind = 10 kts HEADWIND Find: Flight Time and tripfuel Solution: 1. Read below FL 350 the ISA cruise TAS = 450 kts. 2. Above FL 350 proceed to given OAT and read on the left side the temperature deviation

from ISA: ISA +5°C. 3. Increase ISA Cruise TAS by 5 kts according to the note on the top of the table: Corrected

TAS = 455 kts. 4. Calculate Ground Speed which is 445 kts. 5. Calculate flight ime from overhead departure to overhead destination by the equation

1h7min1.12h445500

d(kts)GroundspeeM)Distance(Nt ====

6. Add the additional time for acceleration and climb, ADD CLIMB TIME = 3 min, and for

approach and descent DESC/ADD = 10 min. Total Flight Time = 1h 20 min 7. Enter with the total flight time the proper column for temperature deviation, proceed to the

right and read the column below the selected flight level the total trip fuel = 21222 pounds. Holding Planning This table provides total fuel flow information necessary for planning holding and reserve fuel requirements. The chart is based on 30 minutes holding in a racetrack pattern in clean configuration and minimum drag airspeed.


2.4 727-200/JT8D-15 September 01, 2009

Simplified Flight Planning

Optimum Altitude

25

27

29

31

33

35

37

39

41

100 110 120 130 140 150 160 170 180

Gross Weight - 1000 lbs

Alti

tude

- 10

00 fe

et


September 01, 2009 727-200/JT8D-15 2.5

Time-Fuel-Table CRUISE PROCEDURE BASED ON LW 154500 POUNDS

TIME - FUEL TABLE (00:19 - 03:00) 250/350/M.78 RESPECTIVELY TOW 190500 POUNDS

-10 -13 -17 -21 -25 -29 -33 -37 -41 -44 -48 -52 -56 -60 -64 -66 -66 INCREASE ISA CRUISE TAS 1 KT PER 1 C ABOVE ISA -5 -8 -12 -16 -20 -24 -28 -32 -36 -39 -43 -47 -51 -55 -59 -61 -61

ISA -3 -7 -11 -15 -19 -23 -27 -31 -34 -38 -42 -46 -50 -54 -56 -56 DECREASE ISA CRUISE TAS 1 KT PER 1 C BELOW ISA +5 2 -2 -6 -10 -14 -18 -22 -26 -29 -33 -37 -41 -45 -49 -51 -51

+10 7 3 -1 -5 -9 -13 -17 -21 -24 -28 -32 -36 -40 -44 -46 -46

+15 12 8 4 0 -4 -8 -12 -16 -19 -23 -27 -31 -35 -39 -41 -41 ADD CLIM/ADD TIME AND 10 MIN DESC/ADD TIME TO CALCULATED CRUISE TIME +20 17 13 9 5 1 -3 -7 -11 -14 -18 -22 -26 -30 -34 -36 -36

-10 -5 ISA +5 +10 +15 +20 FL 90 110 130 150 170 190 210 230 250 270 290 310 330 350 370 390

ISA CRUISE TAS (KTS) 285 407 419 431 444 456 470 474 470 466 462 458 454 450 447 447

CLIMB/ADD TIME (MIN) 2 2 2 2 3 3 3 3 4 4 4 3 3 3 3 3

20 20 20 20 19 19 19 5009 6941 7233 7629 8046 8227 8664 5009 9442 9705 10003 10555 11496 12167 10780 9932

22 22 22 22 21 21 21 5245 7326 7615 8006 8420 8597 9034 9582 9791 10037 10320 10861 11797 12469 11064 10187

24 24 24 24 23 23 23 5481 7711 7996 8383 8795 8968 9405 9952 10140 10368 10637 11167 12098 12771 11349 10442

26 26 26 25 25 25 25 5718 8097 8378 8760 9170 9339 9775 10322 10488 10699 10954 11473 12399 13073 11633 10697

28 28 28 27 27 27 27 5954 8482 8760 9137 9545 9710 10146 10692 10837 11030 11270 11779 12700 13374 11917 10951

30 30 30 29 29 29 29 6190 8868 9141 9514 9919 10080 10516 11062 11186 11361 11587 12085 13001 13676 12202 11206

32 32 32 31 31 31 30 6427 9253 9523 9891 10294 10451 10886 11432 11535 11693 11904 12391 13301 13978 12486 11461

34 34 34 33 33 33 32 6663 9639 9904 10268 10669 10822 11257 11802 11884 12024 12221 12697 13602 14280 12771 11715

36 36 36 35 35 35 34 6899 10024 10286 10645 11043 11193 11627 12172 12233 12355 12538 13003 13903 14582 13055 11970

38 38 38 37 37 36 36 7136 10409 10668 11023 11418 11563 11997 12542 12582 12686 12855 13309 14204 14883 13339 12225

40 40 40 39 39 38 38 7372 10795 11049 11400 11793 11934 12368 12912 12931 13017 13172 13615 14505 15185 13624 12479

42 42 42 41 41 40 40 7608 11180 11431 11777 12167 12305 12738 13282 13280 13349 13489 13920 14806 15487 13908 12734

44 44 44 43 43 42 42 7845 11566 11812 12154 12542 12676 13108 13652 13629 13680 13805 14226 15107 15789 14192 12989

46 46 46 45 45 44 44 8081 11951 12194 12531 12917 13046 13479 14022 13978 14011 14122 14532 15408 16091 14477 13244

48 48 48 47 47 46 46 8317 12336 12576 12908 13291 13417 13849 14392 14327 14342 14439 14838 15708 16393 14761 13498

50 50 50 49 49 48 48 8553 12722 12957 13285 13666 13788 14220 14762 14676 14673 14756 15144 16009 16694 15045 13753

52 52 52 51 50 50 49 8790 13107 13339 13662 14041 14158 14590 15132 15024 15005 15073 15450 16310 16996 15330 14008

54 54 54 53 52 52 51 9026 13493 13720 14039 14415 14529 14960 15502 15373 15336 15390 15756 16611 17298 15614 14262

56 56 56 55 54 54 53 9262 13878 14102 14416 14790 14900 15331 15872 15722 15667 15707 16062 16912 17600 15898 14517

58 58 58 57 56 56 55 9499 14264 14484 14793 15165 15271 15701 16242 16071 15998 16024 16368 17213 17902 16183 14772

100 100 100 59 58 57 57 9735 14649 14865 15170 15539 15641 16071 16612 16420 16329 16340 16674 17514 18203 16467 15026

02 02 02 101 100 59 59 9971 15034 15247 15547 15914 16012 16442 16982 16769 16661 16657 16980 17814 18505 16751 15281

04 04 04 04 04 101 101 10208 15420 15628 15925 16289 16383 16812 17352 17118 16992 16974 17286 18115 18807 17036 15536

06 06 06 06 06 06 06 10444 15805 16010 16302 16664 16754 17183 17722 17467 17323 17291 17592 18416 19109 17320 15791

08 08 08 08 08 08 08 10680 16191 16392 16679 17038 17124 17553 18092 17816 17654 17608 17898 18717 19411 17604 16045

10 10 10 10 10 10 10 10917 16576 16773 17056 17413 17495 17923 18462 18165 17985 17925 18204 19018 19712 17889 16300

12 12 12 12 12 12 11 11153 16961 17155 17433 17788 17866 18294 18832 18514 18317 18242 18510 19319 20014 18173 16555

14 14 14 14 14 13 13 11389 17347 17536 17810 18162 18237 18664 19202 18863 18648 18559 18816 19620 20316 18458 16809

16 16 16 16 16 15 15 11626 17732 17918 18187 18537 18607 19034 19572 19212 18979 18875 19122 19920 20618 18742 17064

18 18 18 18 17 17 17 11862 18118 18300 18564 18912 18978 19405 19942 19560 19310 19192 19428 20221 20920 19026 17319

20 20 20 20 19 19 19 12098 18503 18681 18941 19286 19349 19775 20312 19909 19641 19509 19733 20522 21222 19311 17573

22 22 22 22 21 21 21 12335 18889 19063 19318 19661 19719 20146 20682 20258 19973 19826 20039 20823 21523 19595 17828

24 24 24 24 23 23 23 12571 19274 19444 19695 20036 20090 20516 21052 20607 20304 20143 20345 21124 21825 19879 18083

26 26 26 25 25 25 25 12807 19659 19826 20072 20410 20461 20886 21423 20956 20635 20460 20651 21425 22127 20164 18338

28 28 28 27 27 27 27 13044 20045 20208 20449 20785 20832 21257 21793 21305 20966 20777 20957 21726 22429 20448 18592

30 30 30 29 29 29 29 13280 20430 20589 20827 21160 21202 21627 22163 21654 21297 21094 21263 22026 22731 20732 18847

32 32 32 31 31 31 30 13516 20816 20971 21204 21534 21573 21997 22533 22003 21629 21410 21569 22327 23032 21017 19102

34 34 34 33 33 33 32 13752 21201 21352 21581 21909 21944 22368 22903 22352 21960 21727 21875 22628 23334 21301 19356

36 36 36 35 35 35 34 13989 21586 21734 21958 22284 22315 22738 23273 22701 22291 22044 22181 22929 23636 21585 19611

38 38 38 37 37 36 36 14225 21972 22116 22335 22658 22685 23108 23643 23050 22622 22361 22487 23230 23938 21870 19866

40 40 40 39 39 38 38 14461 22357 22497 22712 23033 23056 23479 24013 23399 22953 22678 22793 23531 24240 22154 20120

42 42 42 41 41 40 40 14698 22743 22879 23089 23408 23427 23849 24383 23748 23285 22995 23099 23832 24541 22438 20375

44 44 44 43 43 42 42 14934 23128 23260 23466 23783 23797 24220 24753 24096 23616 23312 23405 24133 24843 22723 20630

46 46 46 45 45 44 44 15170 23514 23642 23843 24157 24168 24590 25123 24445 23947 23628 23711 24433 25145 23007 20885

48 48 48 47 47 46 46 15407 23899 24024 24220 24532 24539 24960 25493 24794 24278 23945 24017 24734 25447 23292 21139

50 50 50 49 49 48 48 15643 24284 24405 24597 24907 24910 25331 25863 25143 24609 24262 24323 25035 25749 23576 21394

52 52 52 51 50 50 49 15879 24670 24787 24974 25281 25280 25701 26233 25492 24941 24579 24629 25336 26050 23860 21649

54 54 54 53 52 52 51 16116 25055 25168 25351 25656 25651 26071 26603 25841 25272 24896 24935 25637 26352 24145 21903

56 56 56 55 54 54 53 16352 25441 25550 25729 26031 26022 26442 26973 26190 25603 25213 25240 25938 26654 24429 22158

58 58 58 57 56 56 55 16588 25826 25932 26106 26405 26393 26812 27343 26539 25934 25530 25546 26239 26956 24713 22413

200 ## ## 58 57 57 56 16825 26211 26313 26483 26780 26763 27183 27713 26888 26265 25847 25852 26539 27258 24998 22667

02 02 02 ## 59 58 57 17061 26597 26695 26860 27155 27134 27553 28083 27237 26597 26163 26158 26840 27560 25282 22922

04 04 04 04 201 59 58 17297 26982 27077 27237 27529 27505 27923 28453 27586 26928 26480 26464 27141 27861 25566 23177

06 06 06 06 06 201 201 17534 27368 27458 27614 27904 27876 28294 28823 27935 27259 26797 26770 27442 28163 25851 23432

08 08 08 08 08 08 08 17770 27753 27840 27991 28279 28246 28664 29193 28284 27590 27114 27076 27743 28465 26135 23686

10 10 10 10 10 10 10 18006 28139 28221 28368 28653 28617 29034 29563 28632 27921 27431 27382 28044 28767 26419 23941

12 12 12 12 12 12 11 18243 28524 28603 28745 29028 28988 29405 29933 28981 28253 27748 27688 28345 29069 26704 24196

14 14 14 14 14 13 13 18479 28909 28985 29122 29403 29358 29775 30303 29330 28584 28065 27994 28645 29370 26988 24450

16 16 16 16 16 15 15 18715 29295 29366 29499 29777 29729 30146 30673 29679 28915 28382 28300 28946 29672 27272 24705

18 18 18 18 17 17 17 18951 29680 29748 29876 30152 30100 30516 31043 30028 29246 28698 28606 29247 29974 27557 24960

20 20 20 20 19 19 19 19188 30066 30129 30254 30527 30471 30886 31413 30377 29577 29015 28912 29548 30276 27841 25214

22 22 22 22 21 21 21 19424 30451 30511 30631 30902 30841 31257 31783 30726 29909 29332 29218 29849 30578 28125 25469

24 24 24 24 23 23 23 19660 30836 30893 31008 31276 31212 31627 32153 31075 30240 29649 29524 30150 30879 28410 25724

26 26 26 25 25 25 25 19897 31222 31274 31385 31651 31583 31997 32523 31424 30571 29966 29830 30451 31181 28694 25979

28 28 28 27 27 27 27 20133 31607 31656 31762 32026 31954 32368 32893 31773 30902 30283 30136 30751 31483 28979 26233

30 30 30 29 29 29 29

TOTAL FLIGHT TIME H/MIN TOTAL TRIP FUEL POUNDS

20369 31993 32037 32139 32400 32324 32738 33263 32122 31233 30600 30442 31052 31785 29263 26488


2.6 727-200/JT8D-15 September 01, 2009

CRUISE PROCEDURE BASED ON LW 154500 POUNDS

TIME - FUEL TABLE (00:19 - 03:00) 250/350/M.78 RESPECTIVELY TOW 190500 POUNDS

-10 -13 -17 -21 -25 -29 -33 -37 -41 -44 -48 -52 -56 -60 -64 -66 -66 INCREASE ISA CRUISE TAS 1 KT PER 1 C ABOVE ISA -5 -8 -12 -16 -20 -24 -28 -32 -36 -39 -43 -47 -51 -55 -59 -61 -61

ISA -3 -7 -11 -15 -19 -23 -27 -31 -34 -38 -42 -46 -50 -54 -56 -56 DECREASE ISA CRUISE TAS 1 KT PER 1 C BELOW ISA +5 2 -2 -6 -10 -14 -18 -22 -26 -29 -33 -37 -41 -45 -49 -51 -51

+10 7 3 -1 -5 -9 -13 -17 -21 -24 -28 -32 -36 -40 -44 -46 -46

+15 12 8 4 0 -4 -8 -12 -16 -19 -23 -27 -31 -35 -39 -41 -41 ADD CLIM/ADD TIME AND 10 MIN DESC/ADD TIME TO CALCULATED CRUISE TIME +20 17 13 9 5 1 -3 -7 -11 -14 -18 -22 -26 -30 -34 -36 -36

-10 -5 ISA +5 +10 +15 +20 FL 90 110 130 150 170 190 210 230 250 270 290 310 330 350 370 390

32 32 32 31 31 31 30 20606 32378 32419 32516 32775 32695 33108 33633 32471 31565 30917 30747 31353 32087 29547 26743

34 34 34 33 33 33 32 20842 32764 32801 32893 33150 33066 33479 34003 32820 31896 31233 31053 31654 32389 29832 26997

36 36 36 35 35 35 34 21078 33149 33182 33270 33524 33437 33849 34373 33168 32227 31550 31359 31955 32690 30116 27252

38 38 38 37 37 36 36 21315 33534 33564 33647 33899 33807 34220 34743 33517 32558 31867 31665 32256 32992 30400 27507

40 40 40 39 39 38 38 21551 33920 33945 34024 34274 34178 34590 35113 33866 32889 32184 31971 32557 33294 30685 27761

42 42 42 41 41 40 40 21787 34305 34327 34401 34648 34549 34960 35483 34215 33221 32501 32277 32857 33596 30969 28016

44 44 44 43 43 42 42 22024 34691 34709 34778 35023 34919 35331 35853 34564 33552 32818 32583 33158 33898 31253 28271

46 46 46 45 45 44 44 22260 35076 35090 35156 35398 35290 35701 36223 34913 33883 33135 32889 33459 34199 31538 28526

48 48 48 47 47 46 46 22496 35461 35472 35533 35772 35661 36071 36593 35262 34214 33452 33195 33760 34501 31822 28780

50 50 50 49 49 48 48 22733 35847 35853 35910 36147 36032 36442 36963 35611 34545 33768 33501 34061 34803 32106 29035

52 52 52 51 50 50 49 22969 36232 36235 36287 36522 36402 36812 37334 35960 34877 34085 33807 34362 35105 32391 29290

54 54 54 53 52 52 51 23205 36618 36617 36664 36896 36773 37183 37704 36309 35208 34402 34113 34663 35407 32675 29544

56 56 56 55 54 54 53 23442 37003 36998 37041 37271 37144 37553 38074 36658 35539 34719 34419 34964 35708 32959 29799

58 58 58 57 56 56 55 23678 37389 37380 37418 37646 37515 37923 38444 37007 35870 35036 34725 35264 36010 33244 30054

300 ## ## 58 57 57 56

23914 37774 37761 37795 38020 37885 38294 38814 37356 36201 35353 35031 35565 36312 33528 30308


September 01, 2009 727-200/JT8D-15 2.7

Holding Planning Pressure Zero Fuel Weight - pounds x 1000 Altitude 140 130 120 110

ft Holding Fuel - pounds 9000 3392 3315 3254 3188 8000 3425 3351 3284 3221 7000 3460 3388 3317 3256 6000 3496 3426 3353 3293 5000 3534 3465 3393 3332 4000 3574 3505 3435 3373 3000 3615 3545 3480 3417 2000 3659 3587 3528 3462 1000 3703 3629 3579 3509

0 3750 3672 3633 3558


2.8 727-200/JT8D-15 September 01, 2009

Intentionally Blank

Boeing 727-200 ENROUTE Flight Planning and Performance Manual

September 01, 2009 727-200/JT8D-15 3.1


ENROUTE Chapter 3 Text ......................................................................................................................................................................... 3

Introduction......................................................................................................................................................... 3 General................................................................................................................................................................ 3 All Engine ........................................................................................................................................................... 3 Engine Inoperative .............................................................................................................................................. 4

General.................................................................................................................................................................... 5 Flight Limitations................................................................................................................................................ 5 Temperature Conversion..................................................................................................................................... 6

All Engine ............................................................................................................................................................... 7 Climb Speeds ...................................................................................................................................................... 7 Climb EPR .......................................................................................................................................................... 8 .78M Cruise Table............................................................................................................................................... 9 True Air Speed Table........................................................................................................................................ 10 Turbulent Air Penetration ................................................................................................................................. 10 Maximum Cruise EPR ...................................................................................................................................... 11 Engine Parameter .............................................................................................................................................. 12 Holding Fuel Flow ............................................................................................................................................ 14 Descent.............................................................................................................................................................. 15 Go-Around EPR................................................................................................................................................ 16

Engine Inoperative ................................................................................................................................................ 17 One Engine Out................................................................................................................................................. 17 Two Engine Out ................................................................................................................................................ 18 Maximum Continuous EPR .............................................................................................................................. 19

ENROUTE Boeing 727-200 Flight Planning and Performance Manual

3.2 727-200/JT8D-15 September 01, 2009

Intentionally Blank


September 01, 2009 727-200/JT8D-15 3.3

Text

Introduction This chapter contains inflight data for use as general reference in airplane performance monitoring, flight planning studies and as a supplement to information provided in the Operations Manual.

General

Flight Limitations These tables present the Stall Speeds and the Stick Shaker Speeds as a function of gross weight and flap setting.

Temperature Conversion Use the table to convert Total Air Temperature (TAT) to Outside Air Temperature (OAT).

All Engine

Climb Speed Economic climb speeds are presented as a function of gross weight.

Climb EPR To find Climb EPR based on normal engine bleed, enter Climb EPR Table with pressure altitude and TAT and read EPR. Apply adjustments as shown.

.78M Cruise Table The table presents the required EPR and the Specific Range (SR) as a function of gross weight and flight level. Fuel Flow (FF) can be calculated from the Specific Range (SR) by the following equation:

x1000SRTASFF =

To convert Nautical Miles (NM) into Nautical Air Miles (NAM) use the following equation, where GS is the Ground Speed:

GSTASNMNAM =

True Airspeed Table The table provides the True Airspeed for two Mach numbers.

Maximum Cruise EPR To find Maximum Cruise EPR based on normal engine bleed, enter table with pressure altitude and TAT and read EPR. Apply adjustments as shown.

Engine Parameter Use these tables to check engine parameter during stabilized cruise.

Holding Target EPR and fuel flow per engine information is tabulated for holding with flaps up based on the minimum drag airspeed. Enter the table with weight and pressure altitude to read EPR and fuel flow per engine.

Descent Distance and time for descent are shown for a .78M/280 KIAS descent speed schedule. Enter the table with top of descent pressure altitude and read distance in nautical miles and time in minutes.

Go-Around EPR To find Go-Around EPR based on normal engine bleed, enter table with pressure altitude and OAT or TAT and read EPR. Apply adjustments as shown.


3.4 727-200/JT8D-15 September 01, 2009

Engine Inoperative

One Engine Out The table shows maximum altitude that can be maintained at a given weight and air temperature, based on long range cruise speed and maximum continuous thrust. In some cases following engine failure, a descent to a lower altitude and reduction in airspeed may be necessary. In these circumstances, a driftdown procedure should be adopted in order to minimize the loss in specific range. The turbulent air penetration speed schedule is recommended. For driftdown following engine failure, set up maximum continuous thrust and establish a speed schedule of 280 KIAS or M = .80, whichever is lower.

Two Engine Out After failure of the second engine, set maximum continuous limit EPR and allow the airplane to descent at the airspeed shown in the driftdown table. The airplane should level off at approximately the altitude and weight shown in the table. EPR must be checked frequently during the driftdown to ensure that the maximum continuous limit EPR is not exceeded. When the airplane has leveled off, constant altitude should be maintained. This will allow the airplane to slowly accelerate to the optimum range speed as weight reduces due to fuel burnoff. When the optimum range speed shown in the climbing cruise table is achieved, the airplane should follow a climbing cruise procedure, flying at the airspeed appropriate to the gross weight. The pressure altitudes achievable under these weight and speed conditions are shown in the table.


September 01, 2009 727-200/JT8D-15 3.5

General

Flight Limitations

Stall Speeds Flap Setting

Gross Weight up 5 15 25 30 40 pounds x 1000 Stall Speed KIAS

170 163 130 121 111 107 110 165 160 128 118 109 106 108 160 157 125 116 107 104 105 155 154 123 114 105 102 102 150 151 121 112 103 100 100 145 148 118 109 101 98 97 140 145 116 107 99 96 94 135 142 113 105 97 94 92 130 139 111 102 95 92 89 125 136 109 100 92 89 87 120 133 106 98 90 87 84 115 130 104 95 88 85 82 110 126 101 93 86 83 80 105 123 99 91 84 82 77 100 120 96 89 82 80 75

Stick Shaker Speeds Flap Setting

Gross Weight up 5 15 25 30 40 pounds x 1000 Stick Shaker Speed KIAS

170 175 143 134 125 124 118 165 173 141 132 123 122 116 160 170 139 130 121 120 114 155 167 137 128 119 117 112 150 164 134 126 117 115 109 145 162 132 124 115 113 107 140 159 130 122 113 110 105 135 156 127 120 111 108 103 130 153 125 117 109 106 100 125 150 123 115 107 103 98 120 147 120 113 105 101 96 115 144 118 111 102 98 94 110 141 115 108 100 96 91 105 138 112 106 98 93 89 100 134 110 103 95 90 86

Speeds applicable to takeoff and landing altitudes only. Values are based on most forward C.G.


3.6 727-200/JT8D-15 September 01, 2009

Temperature Conversion

INDICATED MACH NUMBER .30 .40 .50 .60 .70 .76 .78 .80 .82 .84 IND TAT - °C TRUE OUTSIDE AIR TEMPERATURE - DEGREES C

70 47 39 34 33 31 29 28 65 49 42 35 30 28 27 25 23 60 50 44 38 30 25 24 22 21 19 55 49 45 39 33 26 21 19 18 16 14 50 44 40 35 28 21 17 15 13 12 10 45 39 35 30 24 17 12 10 9 7 6 40 34 30 25 19 12 8 6 4 3 1 35 30 25 20 14 7 3 2 0 -2 -3 30 25 21 16 10 3 -1 -3 -4 -6 -7 25 20 16 11 5 -2 -6 -7 -9 -10 -12 20 15 11 6 0 -6 -10 -12 -13 -15 -16 15 10 6 1 -4 -11 -15 -16 -18 -19 -21 10 5 1 -3 -9 -15 -19 -21 -22 -24 -25

5 0 -4 -8 -14 -20 -24 -25 -27 -28 -29 0 -5 -8 -13 -18 -24 -28 -30 -31 -32 -34

-5 -10 -13 -18 -23 -29 -33 -34 -35 -37 -38 -10 -15 -18 -23 -28 -33 -37 -39 -40 -41 -43 -15 -20 -23 -27 -32 -38 -42 -43 -44 -46 -47 -20 -24 -28 -32 -37 -43 -46 -47 -49 -50 -51 -25 -29 -33 -37 -42 -47 -51 -52 -53 -54 -56 -30 -34 -38 -42 -46 -52 -55 -56 -58 -59 -60 -35 -39 -42 -46 -51 -56 -60 -61 -62 -63 -64 -40 -44 -47 -51 -56 -61 -64 -65 -66 -68 -69


September 01, 2009 727-200/JT8D-15 3.7

All Engine

Climb Speeds

Gross Weight

lb knots 120000 280 130000 285 140000 290 150000 295 160000 300 170000 305 180000 310 190000 315 200000 320 210000 325


3.8 727-200/JT8D-15 September 01, 2009

Climb EPR

Pressure TAT °C

Altitude ENG -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 S.L. 1 & 3 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.03 1.97 1.93 1.88 1.84 1.79 1.75 1.72 1.68 1.64 2 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 1000 1 & 3 2.13 2.13 2.13 2.13 2.13 2.13 2.13 2.13 2.08 2.03 1.97 1.93 1.88 1.84 1.79 1.75 1.72 1.68 1.64 2 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 2000 1 & 3 2.19 2.19 2.19 2.19 2.19 2.19 2.18 2.13 2.08 2.03 1.97 1.93 1.88 1.84 1.79 1.75 1.72 1.68 1.64 2 2.21 2.21 2.21 2.21 2.21 2.21 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 3000 1 & 3 2.24 2.24 2.24 2.24 2.23 2.21 2.17 2.13 2.08 2.02 1.97 1.92 1.88 1.83 1.79 1.75 1.71 1.67 1.63 2 2.26 2.26 2.26 2.26 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 3900 to 1 & 3 2.29 2.28 2.27 2.25 2.23 2.20 2.17 2.13 2.08 2.02 1.97 1.92 1.87 1.83 1.79 1.75 1.71 1.67 1.63 5000 2 2.32 2.31 2.29 2.28 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 10000 1 & 3 2.28 2.27 2.26 2.24 2.22 2.20 2.16 2.12 2.07 2.01 1.96 1.91 1.86 1.82 1.78 1.74 1.70 1.66 1.62 2 2.32 2.31 2.29 2.28 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 20000 1 & 3 2.27 2.26 2.24 2.23 2.21 2.18 2.15 2.10 2.05 2.00 1.94 1.90 1.85 1.81 1.76 1.72 1.69 1.65 1.61 2 2.32 2.31 2.29 2.28 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 30000 1 & 3 2.25 2.24 2.23 2.21 2.19 2.17 2.13 2.09 2.04 1.98 1.93 1.88 1.83 1.79 1.75 1.71 1.67 1.63 1.59 2 2.32 2.31 2.29 2.28 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67 40000 & 1 & 3 2.23 2.22 2.20 2.19 2.17 2.14 2.11 2.06 2.01 1.96 1.90 1.86 1.81 1.77 1.72 1.68 1.65 1.61 1.57 ABOVE 2 2.32 2.31 2.29 2.28 2.26 2.23 2.20 2.16 2.11 2.05 2.00 1.95 1.90 1.86 1.82 1.78 1.74 1.70 1.67

EPR BLEED CORRECTIONS ENG 1 & 3 ENG 2 S.L. OFF + .04 ON - .04

10000 FT OFF + .05 ON - .05 20000 FT OFF + .07 ON - .07 30000 FT OFF + .08 ON - .08

AIR CONDITIONING

AIR BLEED 40000 FT OFF + .11 ON - .10

ENGINE ANTI-ICE ON - .08 - .12 TWO ENG BLEEDS - .17 ENG AND WING

ANTI-ICE ONE ENG BLEED - .17 - .12


September 01, 2009 727-200/JT8D-15 3.9

.78M Cruise Table EPR required Specific Range NAM/1000lbs

CRUISE EPR required 250/350/M.78

Press STD STD STD Alt TAS IAS SAT TAT M

GROSS WEIGHT - 1000 LBS

-1000 KTS KTS °C °C 175 170 165 160 155 150 145 140 135 130 125 120 115 110 FT

2.09 2.04 1.99 1.95 1.91 1.8839 447 241 -57 -31 .78

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 -31 .78 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 -27 .78 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 1.7433 454 277 -50 -23 .78

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 64.81.95 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 -18 .78 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 61.31.87 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 -14 .78 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 57.81.82 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 -9 .78 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 54.21.77 1.76 1.75 1.75 1.73 1.72 1.71 1.70 1.69 1.68 1.67 1.66 1.66 1.65

25 470 329 -35 -6 .78 42.9 43.6 44.2 44.9 45.4 46.1 46.7 47.3 47.9 48.5 49.1 49.7 50.2 50.81.74 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 -2 .78 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 47.51.70 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 1 .76 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 46.11.65 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 2 .71 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 44.31.61 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 7 .71 38.4 38.8 39.2 39.5 39.9 40.1 40.5 40.9 41.2 41.5 41.8 42.1 42.4 42.71.57 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 9 .68 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 41.01.53 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 12 .66 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 39.31.49 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 15 .64 34.3 34.6 34.1 35.2 35.4 35.7 36.0 36.2 36.5 36.7 37.0 37.2 37.4 37.71.38 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 7 .44 38.7 39.2 39.7 40.2 40.7 41.1 41.6 42.0 42.5 43.0 43.3 43.8 44.3 44.71.36 1.35 1.33 1.31 1.31 1.30 1.29 1.28 1.27 1.26 1.25 1.24 1.23 1.22

7 276 250 1 11 .43 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 42.41.33 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 14 .41 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 40.21.30 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 6 15 .40 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

Notes: - A/C bleed from pod engines "ON" - No bleed from center engine - Shaded area indicates optimum altitude


3.10 727-200/JT8D-15 September 01, 2009

True Air Speed Table Use the following table to convert mach number into true airspeed (TAS).

M = 0.78 M = .80 OAT °C

TAS KTS TAS KTS -15 488 501 -20 484 496 -25 479 491 -30 474 486 -35 469 481 -40 464 476 -45 459 471 -50 454 466 -55 449 460 -60 444 455 -65 438 450 -70 433 444

Turbulent Air Penetration

Gross Weight – 1000 pounds 175 170 165 160 155 150 145 Target Speed

IAS/Mach Flight Level Nominal N1 % 390 93 92 350 95 93 91 88 88 86 85 310 88 88 86 84 84 82 81 270 84 85 82 81 81 80 79 200 80 83 78 77 77 76 75

280/.80

100 75 76 74 74 74 73 72


September 01, 2009 727-200/JT8D-15 3.11

Maximum Cruise EPR FL ENG TAT °C

-50 -45 -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 050 2.24 2.23 2.22 2.21 2.20 2.18 2.15 2.13 2.09 2.04 1.99 1.93 1.87 1.80 1.75 1.70 1.65 1.61 1.57 1.53 100 2.24 2.23 2.22 2.20 2.19 2.18 2.16 2.13 2.09 2.04 1.99 1.93 1.86 1.80 1.74 1.69 1.65 1.60 1.56 1.52 200 2.23 2.22 2.21 2.19 2.18 2.17 2.14 2.12 2.08 2.03 1.98 1.92 1.85 1.79 1.73 1.68 1.64 1.59 1.55 1.51 300 2.22 2.21 2.0 2.18 2.17 2.16 2.13 2.10 2.07 2.02 1.97 1.91 1.84 1.78 1.72 1.67 1.63 1.58 1.54 1.50 400 2.19 2.18 2.17 2.16 2.15 2.13 2.11 2.08 2.04 2.00 1.94 1.89 1.82 1.76 1.70 1.65 1.60 1.56 1.52 1.48 420

1&3

2.19 2.18 2.17 2.16 2.14 2.13 2.11 2.08 2.04 1.99 1.94 1.88 1.82 1.75 1.69 1.64 1.60 1.56 1.52 1.48 050 420 2 2.25 2.24 2.23 2.22 2.21 2.19 2.17 2.14 2.10 2.06 2.01 1.95 1.89 1.82 1.76 1.72 1.67 1.63 1.59 1.55

EPR Bleed Correction

Flight Level ENG 1 & 3 ENG 2

050 OFF + .03 ON - .03 100 OFF + .04 ON - .04 200 OFF + .05 ON - .05 300 OFF + .06 ON - .06 400 OFF + .08 ON - .07

Air Conditioning

Air Bleed

420 OFF + .08 ON - .07 Engine Anti-Ice ON - .08 - .11

TWO ENG BLEEDS - .16 ENG and Wing Anti-Ice ONE ENG BLEED - .16 -. 11


3.12 727-200/JT8D-15 September 01, 2009

Engine Parameter N1, N2, EGT versus EPR Pod Engines

TAT - °C -40 -30 -20 -10 0 10 20 30 40

EPR

N1 % 72.7 74.2 75.7 77.2 78.6 80.1 81.5 82.9 84.2 N2 % 77.2 78.8 80.4 82.0 83.5 85.0 86.5 88.0 89.4 1.55 EGT °C 308 333 358 383 407 432 457 482 507 N1 % 74.0 75.6 77.1 78.6 80.1 81.5 83.0 84.4 85.7 N2 % 77.8 79.5 81.1 82.7 84.2 85.8 87.3 88.7 90.2 1.60 EGT °C 308 333 358 383 408 433 458 483 508 N1 % 75.2 76.8 78.4 79.9 81.4 82.9 84.3 85.8 87.2 N2 % 78.4 80.1 81.7 83.3 84.9 86.5 88.0 89.5 90.9 1.65 EGT °C 309 334 359 384 409 434 459 484 508 N1 % 76.4 78.0 79.6 81.1 82.7 84.2 85.6 87.1 88.5 N2 % 79.1 80.8 82.4 84.0 85.6 87.1 88.7 90.2 91.6 1.70 EGT °C 309 334 359 384 409 434 459 484 509 N1 % 77.5 79.1 80.8 82.3 83.9 85.4 86.9 88.4 89.8 N2 % 79.7 81.4 83.1 84.7 86.3 87.8 89.4 90.9 92.4 1.75 EGT °C 310 335 360 385 410 435 460 485 510 N1 % 78.6 80.3 81.9 83.5 85.1 86.6 88.1 89.6 91.1 N2 % 80.3 82.0 83.7 85.4 87.0 88.5 90.1 91.6 93.1 1.80 EGT °C 310 335 360 385 410 435 460 485 510 N1 % 79.7 81.4 83.1 84.7 86.3 87.8 89.4 90.9 92.4 N2 % 81.0 82.7 84.4 86.0 87.7 89.2 90.8 92.3 93.9 1.85 EGT °C 311 336 361 386 411 436 461 486 511 N1 % 80.9 82.6 84.3 85.9 87.5 89.1 90.7 92.2 93.7 N2 % 81.6 83.4 85.1 86.7 88.4 90.0 91.5 93.1 94.6 1.90 EGT °C 311 336 361 386 412 437 462 487 512 N1 % 82.0 83.8 85.5 87.2 88.8 90.4 92.0 93.6 95.1 N2 % 82.3 84.1 85.8 87.5 89.1 90.7 92.3 93.9 95.4 1.95 EGT °C 312 337 362 387 412 437 462 487 512 N1 % 83.3 85.1 86.8 88.5 90.2 91.8 93.4 95.0 96.6 N2 % 83.0 84.8 86.5 88.2 89.9 91.5 93.1 94.7 96.2 2.00 EGT °C 312 337 362 388 413 438 463 488 513 N1 % 84.7 86.5 88.3 90.0 91.7 93.3 95.0 96.6 98.2 N2 % 83.7 85.5 87.3 89.0 90.6 92.3 93.9 95.5 97.1 2.05 EGT °C 313 338 363 388 413 438 463 489 514 N1 % 86.2 88.0 89.8 91.6 93.3 95.0 96.6 98.3 99.9 N2 % 84.5 86.3 88.1 89.8 91.5 93.1 94.8 96.4 97.9 2.10 EGT °C 313 338 363 389 414 439 464 489 514 N1 % 87.8 89.7 91.5 93.3 95.1 96.8 98.5 100.2 101.8 N2 % 85.3 87.1 88.9 90.6 92.3 94.0 95.6 97.3 98.9 2.15 EGT °C 314 339 364 389 414 439 465 490 515


September 01, 2009 727-200/JT8D-15 3.13

Engine Parameter (con’t) N1, N2, EGT versus EPR Center Engine

TAT - °C

-40 -30 -20 -10 0 10 20 30 40 EPR

N1 % 73.1 74.6 76.2 77.6 79.1 80.5 82.0 83.3 84.7 N2 % 76.6 78.2 79.8 81.4 82.9 84.4 85.9 87.3 88.7 1.55 EGT °C 306 331 356 380 405 430 455 480 505 N1 % 74.2 75.7 77.3 78.8 80.3 81.7 83.2 84.6 85.9 N2 % 77.2 78.8 80.4 82.0 83.6 85.1 86.6 88.0 89.5 1.60 EGT °C 306 331 356 381 406 431 456 480 505 N1 % 75.2 76.8 78.3 79.9 81.4 82.9 84.3 85.7 87.1 N2 % 77.8 79.5 81.1 82.7 84.2 85.8 87.3 88.7 90.2 1.65 EGT °C 307 332 357 382 406 431 456 481 506 N1 % 76.2 77.8 79.4 80.9 82.5 84.0 85.4 86.9 88.3 N2 % 78.5 80.1 81.7 83.3 84.9 86.5 88.0 89.5 90.9 1.70 EGT °C 307 332 357 382 407 432 457 482 507 N1 % 77.2 78.8 80.4 82.0 83.5 85.0 86.5 88.0 89.4 N2 % 79.1 80.8 82.4 84.0 85.6 87.2 88.7 90.2 91.7 1.75 EGT °C 308 333 358 383 407 432 457 482 507 N1 % 78.2 79.8 81.5 83.1 84.6 86.1 87.7 89.1 90.6 N2 % 79.7 81.4 83.1 84.7 86.3 87.9 89.4 90.9 92.4 1.80 EGT °C 308 333 358 383 408 433 458 483 508 N1 % 79.2 80.9 82.5 84.2 85.7 87.3 88.8 90.3 91.8 N2 % 80.4 82.1 83.8 85.4 87.0 88.6 90.1 91.7 93.2 1.85 EGT °C 309 334 359 384 409 433 458 483 508 N1 % 80.3 82.0 83.7 85.3 86.9 88.5 90.0 91.6 93.1 N2 % 81.1 82.8 84.5 86.1 87.7 89.3 90.9 92.4 93.9 1.90 EGT °C 309 334 359 384 409 434 459 484 509 N1 % 81.5 83.2 84.9 86.6 88.2 89.8 91.4 92.9 94.4 N2 % 81.7 83.5 85.2 86.8 88.5 90.1 91.7 93.2 94.7 1.95 EGT °C 310 335 360 385 410 435 460 485 510 N1 % 82.7 84.5 86.2 87.9 89.6 91.2 92.8 94.4 95.9 N2 % 82.5 84.2 85.9 87.6 89.3 90.9 92.5 94.0 95.6 2.00 EGT °C 310 335 360 385 410 435 460 485 510 N1 % 84.1 85.9 87.7 89.4 91.1 92.7 94.3 95.9 97.5 N2 % 83.2 85.0 86.7 88.4 90.1 91.7 93.3 94.9 96.4 2.05 EGT °C 310 336 361 386 411 436 461 486 511 N1 % 85.7 87.5 89.3 91.0 92.7 94.4 96.1 97.7 99.3 N2 % 84.0 85.8 87.5 89.2 90.9 92.6 94.2 95.8 97.3 2.10 EGT °C 311 336 361 386 411 436 461 486 511 N1 % 87.4 89.2 91.0 92.8 94.6 96.3 98.0 99.6 101.2 N2 % 84.8 86.6 88.4 90.1 91.8 93.4 95.1 96.7 98.3 2.15 EGT °C 311 336 362 387 412 437 462 487 512


3.14 727-200/JT8D-15 September 01, 2009

Holding Fuel Flow All engines 2 airbleeds fuel flow based on ISA adjust fuel flow +1% per +5°C ISA deviation Minimum Drag Airspeed (200 KTS Lower Limit) Press Altitude

Gross Weight - 1000 pounds

feet 160 150 140 130 120 110 ISA °C 40000 2200 2200 -57 2.02 2.00 35000 2530 2490 2300 2120 2120 -54 1.95 1.93 1.91 1.82 1.80 30000 2800 2510 2470 2280 2120 2120 -44 1.84 1.77 1.75 1.70 1.65 1.60 25000 2755 2558 2490 2240 2200 2200 -35 1.68 1.61 1.57 1.53 1.51 1.48 20000 2840 2670 2580 2270 2300 2300 -25 1.56 1.49 1.46 1.43 1.40 1.38 15000 2910 2780 2670 2310 2380 2380 -15 1.43 1.39 1.36 1.33 1.32 1.29 10000 3040 2850 2740 2460 2520 2520 -5 1.33 1.31 1.29 1.27 1.25 1.23 5000 3130 2960 2830 2510 2580 2580 5 1.27 1.24 1.22 1.21 1.20 1.19 1500 3200 3020 2010 2600 2670 2670 12 1.23 1.21 1.18 1.18 1.18 1.17

FF PER ENG – LB/HR EPR


September 01, 2009 727-200/JT8D-15 3.15

Descent Cruise Mach / 280 knot descent Based on: - Idle power on all engines throughout descent down to initial approach configuration - Cruise Mach 0.80 to to crossover then 350 knots to 10000 feet - 250 knots or less below 10000 feet - Clean configuraton above 2000 feet - Add 120 pounds fuel burn for each minute of terminal area maneuvering Press. Distance Time Fuel Altitude NM min lbs feet 41000 133 23.6 1711 39000 127 22.8 1684 37000 121 22.1 1654 35000 115 21.3 1622 33000 109 20.6 1588 31000 104 19.9 1552 29000 98 19.2 1513 27000 93 18.6 1474 25000 88 18.0 1436 23000 83 17.4 1399 21000 78 16.7 1355 19000 72 16.0 1308 17000 66 15.2 1259 15000 60 14.4 1210 13000 54 13.7 1162 11000 49 12.9 1112 9000 36 10.6 1019 7000 30 9.4 974 5000 25 8.2 924 3000 18 6.5 848


3.16 727-200/JT8D-15 September 01, 2009

Go-Around EPR GO AROUND EPR Pressure OAT °F -82 -10 0 10 18 27 38 47 55 69 73 83 91 100 110 119 Altitude °C -63 -23 -18 -13 -8 -3 3 8 13 18 23 28 33 38 43 48 TAT °C -60 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 -1000 1 & 3 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 2.02 1.99 1.94 1.89 2 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.04 2.01 1.97 1.91 1 & 3 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.04 1.99 1.94 1.89

Sea Level 2 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.06 2.01 1.97 1.91

1000 1 & 3 2.12 2.12 2.12 2.12 2.12 2.12 2.12 2.12 2.09 2.09 2.10 2.08 2.04 1.99 1.94 1.89 2 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.12 2.12 2.13 2.10 2.06 2.01 1.97 1.91 2000 1 & 3 2.18 2.18 2.18 2.18 2.18 2.18 2.17 2.13 2.12 2.12 2.10 2.08 2.04 1.99 1.94 1.89 2 2.20 2.20 2.20 2.20 2.20 2.20 2.19 2.16 2.15 2.15 2.13 2.10 2.06 2.01 1.97 1.91 3000 1 & 3 2.24 2.24 2.24 2.24 2.23 2.20 2.17 2.13 2.12 2.12 2.10 2.08 2.04 1.99 1.94 1.89 2 2.27 2.27 2.27 2.27 2.25 2.22 2.19 2.16 2.15 2.15 2.13 2.10 2.06 2.01 1.97 1.91 3900 & 1 & 3 2.30 2.30 2.28 2.26 2.23 2.20 2.17 2.13 2.12 2.12 2.10 2.08 2.04 1.99 1.94 1.89 ABOVE 2 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.15 2.15 2.13 2.10 2.06 2.01 1.97 1.91

EPR BLEED CORRECTIONS ENG 1 & 3 ENG 2 OFF ON A/C BLEEDS + .04 - .04 - - - .03 ENGINE ANTI-ICE ON - .03* - .06*

- .09 - .03 TWO ENGINE BLEEDS -. 12* - .06* - .10 - .03

ENGINE AND WING ANTI-ICE ONE ENGINE BLEED - .13* - .06* MOD ‘A’ INSTALLED - - + .01

* USE IN SHADED AREA, COLDER THAN -18°C TAT REDUCE ENG 2 EPR BY .05 WITH 6TH STAGE BLEED ON (IF INSTALLED) FOR 10°C (50°F) OAT AND WARMER


September 01, 2009 727-200/JT8D-15 3.17

Engine Inoperative

One Engine Out

Altitude Capability One Engine Inop

Gross Weight

Pressure Altitude - Feet

1000 lbs ISA-10°C ISA ISA+10°C ISA+20°C 200 21423 19995 16783 12158 190 22932 21684 18779 14551 180 24440 23374 20775 16943 170 25948 25063 22771 19336 160 27456 26753 24767 21729 150 28964 28443 26763 24122 140 30473 30132 28758 26514 130 31981 31822 30754 28907 120 33300 33512 32750 31300

The table shows maximum altitude that can be maintained at a given weight and air temperature, based on long range cruise speed and maximum continuous thrust. In some cases following engine failure, a descent to a lower altitude and reduction in airspeed may be necessary. In these circumstances, a driftdown procedure should be adopted in order to minimize the loss in specific range. The turbulent air penetration speed schedule is recommended. For driftdown following engine failure, set up maximum continuous thrust and establish a speed schedule of 280 KIAS or M = .80, whichever is lower.


3.18 727-200/JT8D-15 September 01, 2009

Two Engine Out

Climbing Cruise

Gross Optimum ISA Deviation °C Weight Range -10 0 10 20 LBS 1000 Speed KIAS Pressure Altitude - Feet 110 216 17553 16758 15468 13180 120 225 15249 14218 12497 9612 130 234 12944 11678 9526 6043 140 242 10640 9138 6555 2475 150 251 8336 6598 3584 160 260 6032 4058 170 269 3727 1518

Driftdown

Gross Weight LBS 1000 Driftdown Leveloff Press Alt - Feet

Start Approx Speed ISA Deviation °C Driftdown Level-Off KIAS -10 0 10 20

120 115 205 17539 16482 15014 12816130 124 213 15634 14382 12510 9795140 133 220 13728 12282 10006 6774150 142 228 11823 10182 7502 3753160 151 236 9918 8082 4998 732170 160 244 8013 5981 2494 180 169 251 6108 3881 190 178 259 4203 1781

After failure of the second engine, set maximum continuous limit EPR and allow the airplane to descent at the airspeed shown in the driftdown table. The airplane should level off at approximately the altitude and weight shown in the table. EPR must be checked frequently during the driftdown to ensure that the maximum continuous limit EPR is not exceeded. When the airplane has leveled off, constant altitude should be maintained. This will allow the airplane to slowly accelerate to the optimum range speed as weight reduces due to fuel burnoff. When the optimum range speed shown in the climbing cruise table is achieved, the airplane should follow a climbing cruise procedure, flying at the airspeed appropriate to the gross weight. The pressure altitudes achievable under these weight and speed conditions are shown in the table.


September 01, 2009 727-200/JT8D-15 3.19

Maximum Continuous EPR ENG 1 & 3 A/C BLEED ENG 2 NO BLEED

PRESS MAXIMUM CONTINUOUS EPR ALT TAT °C FT ENG -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50

1 & 3 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.07 2.03 1.98 1.93 1.88 1.84 1.84 1.84 1.84 1.80 1.75S.L. 2 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.09 2.05 2.00 1.95 1.91 1.87 1.86 1.86 1.86 1.83 1.78

1 & 3 2.13 2.13 2.13 2.13 2.13 2.13 2.13 2.13 2.09 2.03 1.98 1.93 1.88 1.84 1.84 1.84 1.84 1.80 1.751000 2 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.15 2.11 2.05 2.00 1.95 1.91 1.87 1.86 1.86 1.86 1.83 1.78

1 & 3 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.14 2.09 2.03 1.98 1.93 1.88 1.84 1.84 1.84 1.84 1.80 1.751499 2 2.17 2.17 2.17 2.17 2.17 2.17 2.17 2.16 2.11 2.05 2.00 1.95 1.91 1.87 1.86 1.86 1.86 1.83 1.78

1 & 3 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.14 2.10 2.05 2.01 1.96 1.91 1.86 1.80 1.751500 2 2.17 2.17 2.17 2.17 2.17 2.17 2.17 2.17 2.17 2.17 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.19 2.19 2.19 2.19 2.19 2.19 2.19 2.19 2.19 2.17 2.14 2.10 2.06 2.01 1.96 1.91 1.86 1.80 1.752000 2 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.24 2.24 2.24 2.24 2.24 2.24 2.24 2.23 2.20 2.17 2.13 2.09 2.05 2.00 1.95 1.90 1.85 1.80 1.753000 2 2.27 2.27 2.27 2.27 2.27 2.27 2.27 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.30 2.30 2.30 2.30 2.30 2.28 2.25 2.23 2.20 2.17 2.13 2.09 2.05 2.00 1.95 1.90 1.85 1.80 1.743900 TO 5000 2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.29 2.29 2.29 2.29 2.29 2.27 2.25 2.22 2.19 2.16 2.12 2.08 2.04 1.99 1.94 1.89 1.84 1.79 1.7410000 2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.27 2.27 2.27 2.27 2.27 2.25 2.23 2.21 2.18 2.14 2.11 2.07 2.02 1.98 1.93 1.88 1.83 1.77 1.7220000 2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.26 2.26 2.26 2.26 2.26 2.24 2.22 2.19 2.16 2.13 2.09 2.05 2.01 1.96 1.91 1.86 1.81 1.76 1.7130000 2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.24 2.24 2.24 2.24 2.24 2.22 2.19 2.17 2.14 2.11 2.07 2.03 1.98 1.94 1.89 1.84 1.79 1.74 1.6840000 2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78

1 & 3 2.23 2.23 2.23 2.23 2.23 2.21 2.19 2.16 2.13 2.10 2.06 2.02 1.98 1.93 1.88 1.83 1.78 1.73 1.6842000

2 2.32 2.32 2.32 2.32 2.32 2.30 2.28 2.25 2.22 2.19 2.16 2.12 2.07 2.03 1.98 1.93 1.88 1.83 1.78


3.20 727-200/JT8D-15 September 01, 2009

EPR BLEED CORRECTIONS ENG 1 &3 ENG 2

S.L. OFF + .04 ON - .0410000 FT OFF + .05 ON - .0520000 FT OFF + .07 ON - .0730000 FT OFF + .08 ON - .0840000 FT OFF + .10 ON - .09

AIR CONDITIONING AIR BLEED

42000 Ft OFF + .11 ON - .09ENGINE ANTI-ICE ON - .08 - .12

TWO BLEEDS - .17END AND WING ANTI-ICE ONE BLEED - .17

- .12

MOD 'A' INLET - + .01

flight planning and performance manual - · pdf fileflight planning and performance manual ......

Documents