Sec 5 226T B Performance

8/17/2019 Sec 5 226T B Performance

1/78

TABLE OF CONTENTS

PERFORMANCE

Item

Page

Introduction ........................................................................ 5-l

Wind Component Chart .......... ............ ........... ........... ............ .....

5-3

Compressibility and Position Error Correction to Indicated OAT (IOAT).

.................. 5-4

Flyover Noise Level ............ ........... ........... ............ ........... ........

5-4

Relationship of Outside Air Temperature to ISA Temperature

...........................

5-5

Takeoff Power Check Chart, Airspeed Zero, Bleed Air Off

..............................

5-6

Takeoff Power Check Chart, Airspeed Zero, Bleed Air On

..............................

5-7

Maximum Continuous Power Check Chart, 200 KTAS

.................................

5-8

Airspeed Calibrations, Normal System

................................................

5-9

Altimeter Calibrations, Normal System

.............................................. 5-10

Airspeed Calibrations, Alternate System

............................................. 5-l 1

Altimeter Calibrations, Alternate System

............................................. 5-l 2

Stall Speeds, Zero Thrust ........................................................... 5-13

Takeoff Speeds, VR and V50

........................................................ 5-14

Two Engine Best Angle and Rate of Climb Speeds

.................................... 5-15

Single Engine Best Angle and Rate of Climb Speeds

.................................. 5-16

Maximum Weight for Continued Takeoff After

Engine Failure at VR

...........................................................

5-17

Two Engine Takeoff Distance - Bleed Air On

........................................ 5-18

Two Engine Takeoff Distance - Bleed Air Off

........................................

5-20

Two Engine Takeoff Distance with Fuel Imbalance

................................... 5-22

Accelerate Stop Distance - Bleed Air On

........................................... 5-24

Accelerate - Go Distance (Engine Failure During Takeoff,

Takeoff Continued).

............................................................

5-26

Single Engine Climb Gradient at V50 ................................................ 5-28

Two Engine Takeoff Climb Gradient at V50

.......................................... 5-29

Two Engine - Rate of Climb

........................................................

5-30

Single Engine - Rate of Climb

.....................................................

5-32

Cabin Altitude for Various Flight Altitudes

...........................................

5-34

Two Engine Service Ceiling

.........................................................

5-35

Single Engine Service Ceiling

.......................................................

5-36

Time, Fuel, and Distance to Climb

...................................................

5-38

Range Profile - Standard Day

Long Range Cruise Power

.......................................................

5-41

Range Profile - Standard Day

Maximum CruiseSpeed

........................................................

5-42

Range Profile - ISA + 15°C

Long Range Cruise Power

......................................................

5-43

Range Profile - ISA + 15°C

Maximum Cruise Speed ............ ........... ............ ........... ...........

5-44

Endurance Profile - Standard Day

Long Range Cruise At 98% RPM

................................................

5-45

I

ssued :

November 3, 1978

Reissued: November 2, 1979

I

PERFORMANCE

I

5-i

I


2/78

MERLIN~B

1

TABLE OF CONTENTS

PERFORMANCE (continued)

Item

Page

Endurance Profile - Standard Day

Maximum Cruise Speed At 98% RPM ...........................................

5-46

Holding Time.. .................................................................... 5-47

Fuel Flow, Specific Range, and Cruise Speeds,

Weight 8,000 Pounds, ISA, 98% RPM

...........................................

5-48



.......................................... 5-49



..........................................

5-50


Weight 8,000 Pounds, ISA +15”C, 98% RPM .................................... 5-51


Weight 10,000 Pounds, ISA +15’C, 98% RPM ................................... 5-52


Weight 12,000 Pounds, ISA +15”C, 98% RPM ...................................

5-53


Weight 8,000 Pounds, ISA, 96% RPM ...........................................

5-54


Weight 10,000 Pounds, ISA, 96% RPM ..........................................

5-55



..........................................

5-56


Weight 8,000 Pounds, ISA +15”C, 96% RPM ....................................

5-57


Weight 10,000 Pounds, ISA +15”C, 96% RPM ................................... 5-58


Weight 12,000 Pounds, ISA +15”C, 96% RPM

...................................

5-59

Time, Fuel, and Distance to Descend ................................................ 5-60

Rate-of-Climb - Balked Landing

....................................................

5-62

Single Engine Landing Distance Without

Reversing or Anti-Skid Brakes .................................................. 5-65

Two Engine Landing Without Reversing

or Anti-Skid Brakes ............................................................ 5-66

Two Engine Landing Distance With Flaps Up

......................................... 5-67

Two Engine Short-Field Landing Without Reverse ....................................

5-68

Sample Flight......................................................................5-6 9

5-ii

PERFORMANCE

Issued:

November 3, 1978



3/78

INTRODUCTION

In general, sufficient information is provided with each data chart to acquaint the operator with the

conditions and procedures upon which the chart is based.

All performance information in this section that is dependent upon engine power includes the effects

of temperature, altitude, engine accessory loads, and instal lation losses. All OAT’s noted in perfor-

mance charts are true temperatures, or indicated OAT corrected for the ram air rise and position

error given in Figure V-2 (assumes zero instrument error). IOAT’s obtained when parked or taxiing

may not be accurate.

It is assumed that a total electrical load of 300 amperes is being used at all times. The effects of

reduced power due to bleed air extraction for operation of pressurization and anti-ice systems have

been included where appl icable . The operating status of the bleed air systems is noted on the ap-

propriate charts. Figure V-4, V-5, and V-6 may be used to verify minimum engine power output

equivalent to that used in preparation of the performance charts.

A sample fligh t plan is contained at the end of the Performance Section.

The following performance data in this section has been FAA approved.

(1) Takeoff (Figures V-16, V-17, and V-18) and landing (Figure V-50) performance to 8,000

feet pressure altitude and associated speeds.

(2) Rates of climb for:

a. Single engine enroute at VyS5.

b.

Two engine normal climb at Vy.

c. Balked landing climb at 105 KIAS (107 KCAS).

(3) All airspeed position and altimeter corrections.

(4) OAT calibration.

(5) Stal l and VMCA speeds.

(6) Maximum demonstrated crosswind.

(7) Minimum installed power.

All other data in this section are manufacturer’s data.

T

Issued: November 3, 1978


PERFORMANCE

5-l


4/78

THIS PAGE INTENTIONALLY LEFT BLANK

I

5-2

I

PERFORMANCE

I

ssued : November 3, 1978


I


5/78

WIND COMPONENT CHART

.

NOTE

Maximum demonstrated crosswind component is 22 Knots.

w

. Wind Velocity = 25 Knots

at 40 degrees of runway heading

Obtain: Headwind Component = 19 Knots

Crosswind Component = 16 Knots

m

-

0 5 10 15 20 25 30 35 40

CROSSWIND COMPONENT

(KNOTS)

Figure V-l

Issued:

November 3,1978


I

PERFORMANCE


6/78

COMPRESSIBILITY AND POSITION ERROR CORRECTION

TO INDICATED OAT (IOAT)

I NoTE-

l

All OAT’s referenced in performance charts are true tem-

peratures, or IOAT corrected for the ram air rise and the

position error given in this figure.

l

Airspeed and alti tude indications assume zero instrument error.

l

IOAT’s obtained when parked or taxiing may not be accurate.

l

Assumes zero OAT instrument error.

PRESSURE ALTITUDE (FEET)

Airspeed ,

Corrections To Be Added (OC)

(KCAS) 0 5,000

10,000 15,000 20,000

25,000 30,000

100 -2

-3 -3 -4

-5 -7 -8

150 -3

-4 -5 -6 -8 -9 -11

200

-5 -6 -7

-9

-10 -12

-15

250 -7 -8

-10 -12 -14

-16 -19

Figure V-2

FLYOVER NOISE LEVELS

Flyover Noise leve l measured in accordance with Appendix F to FAR 36 is 72.8 dB (A).

NOTE

No determination has been made by the Federal Aviation Admin-

istration that the noise levels of this airplane are or should be

acceptable for operation at, into, or out of, any airport.

.

.

. *

5-4

PERFORMANCE

Issued : November 3, 1978



7/78

RELATIONSHIP OF OUTSIDE AIR TEMPERATURE

TO ISA TEMPERATURE

50

40

30

20

G

0

e

I-

d

-10

-60

OAT = -25°C

S.L. 5 10 15 20 25 30

PRESSURE ALTITUDE (1,000 FEET)

Figure V-3



PERFORMANCE

90

80

70

60

50

40

30 c

e

20

k

0

10

0

-10

-20

-30

-40

-50

-60


8/78

TAKEOFF POWER CHECK CHART

ASSOCIATED CONDITIONS:

RPM ......................................... 100%

SRLET.......................................65 m

INLET ANTI-ICE ................................

OFF

AIR SPEED .................................... ZERO

BLEED Alk” ....................................

OFF

lilr*i.lUiil*T.cAu

O’NOT OPERATE BOTH ENGINES AT FULL POWER SI

MULTANEOUSLY. AIRPLANE MAY TEND TO SLIDE AT

TORQUE LIMIT (100%)

-20 -10 0 10 20 30 40

50 60

OAT (OC)

Figure V-4

60

.

5-6 PERFORMANCE

issued: November 3,197B

Reissued: November 2,1979


9/78

TAKEOFF POWER CHECK CHART


-~ ~~~~

RPM ......................................... 100%

SRL ET ....................................... 650°C

INLET ANTI-ICE

................................ OFF

Al RSPEED .................................... ZERO

BLEED AIR ................................... ..O N

I-’ -

N

I

I

pp- CAUTION m

DO NOT OPERATE BOTH ENGINES AT FULL POWER S1-

MULTANEOUSLY. AIRPLANE MAY TEND TO SLIDE AT

LIGHTER WEIGHTS.

TORQUE LIMIT (100%)

I 80

/ 60

50

-30 -20 -10 0 10 20 30 40 50 60

OAT (OC)

Figure V-5

I

ssued:

November 3,197B


I

PERFORMANCE


10/78

AXIMUM CONTINUOUS POWER CHECK CHART


RPM

.................... .....................

100%

SRL ET

...................................... .650=-C

IN LET ANTI-ICE

................................ OFF

AIRSPEED

................................ 200 KTAS

OBTAIN OAT FROM IOAT (FIGURE V-2)

Dc--

TORQUE LIMIT (100%)

100

I

90

i 60

/

40

30

Figure V-6

.

4

5-8

PERFORMANCE

Issued:

November 3,197B



11/78

AIRSPEED CALIBRATION - NORMAL SYSTEM

indicated airspeed assumes zero instrument error.

For flaps up.or takeoff, gear is up or down.

Example: FLAPS TAKEOFF POSITION

Given: Indicated airspeed = 200 KIAS

Find:

Calibrated airspeed = 203 KCAS

KIAS 110 120 140 160 180 200 220 240 260

FLAPS UP KCAS 112 123 143 163 184 204 224 244 264

KIAS 100 120 140 160 180 200 212

FLAPS T.O. KCAS 102 122 143 163 183 203 215

KIAS 80 100 120 140 153

FLAPS

DOWN KCAS 82 101 121 140 153

L

c

NOTE

l

This is in-flight calibration. The ground calibration error is zero

up to 110 KIAS.

Figure V-7

.



PERFORMANCE 5-9


12/78

ALTIMETER CORRECTION - NORMAL SYSTEM

IAS and indicated altitude assume zero instrument error.

For flaps up and takeoff, gear is up or down.

Example:

FLAPS UP

Given : Indicated airspeed = 220 KIAS

Indicated altitude = 10,000 Feet

Find :

Correction = +’ 113 Feet

Corrected altitude = 10,113 Feet

FLAPS UP

Correction To Be Added (Feet)

KIAS

Indicated

Altitude

(Feet)

0

10,000

100

20

26

FLAPS TAKEOFF

Correction To Be Added (Feet)

KIAS

120 140

160 180 200 220

27 34

42 49 56 63

36 47

57 67 76 85

FLAPS DOWN

1 Corrections To Be Added (Feet)

10,000 19 16 11 5

Figure V-B

1 5-10 1

PERFORMANCE

I

Issued:ovember 3,197B


I


13/78

AIRSPEED CALIBRATION - ALTERNATE SYSTEM

c

NOTE

l

Zero instrument error.

l For flaps up gear is up.

l For flaps down gear is down.

l The copilot’s static pressure instruments are not connected

to the alternate static pressure source.

l Do not dump pressurization when using the alternate static

pressure source.

l The airspeed calibration shown below is not valid if the dump

valve is open.

Example: FLAPS DOWN

Given: Indicated airspeed = 100 KIAS

Find: Calibrated airspeed = 105 KCAS

KIAS

100 120 140 160

180 200 220 240 260

FLAPS UP KCAS 105

122 141 160 179 198 217 236 255

KIAS 80 100 120

140 151

FLAPS DOWN KCAS 87 105 123

142 153

Figure V-9

r

Issued : November 3 1978

Reissued: November 2 1979

PERFORMANCE 5-11

t


14/78

EIERLIMIZIIB

ALTIMETER CORRECTION - ALTERNATE SYSTEM

NOTE

l IAS and indicated altitude assume zero instrument error.

l

For flaps up, gear is up.

l

For flaps down, gear is down.

l The copilot’s static pressure instruments are not connected to

the alternate static pressure source.

l Do not dump pressurization when using the alternate static

pressure source.

l The altimeter correction shown below is not valid if the dump

valve is open.

L

Example: FLAPS UP

Given:

Indicated airspeed = 220 KIAS

Indicated altitude = 10,000 Feet

Find:

Correction

=- BBFeet

Corrected altitude = 9,912 Feet

FLAPS DOWN

Corrections To Be Added (Feet)

I nd icated

Altitude

(Feet)

0

1 54 1 49 1 37 1 19 1

10,000 1 73 1 66 1 50 1 26 1

Figure V-l 0

PERFORMANCE

I

ssued :

November 3, 1978


I


15/78

STALL SPEEDS - ZERO THRUST

NOTE

l Maximum altitude loss during power-off stall recovery is ap-

proximately 600 feet.

l

Maximum nose down pitch attitude, and altitude loss during

recovery from single-engine power-on stalls are approximately

lo" and 820 feet, respectively.

l Landing gear is down.

FOR GEAR UP, INCREASE

SPEED 1% KNOTS

\

s mw s INDICATED AIRSPEED

izLu

CALl8RATED Al RSPEED

52

w

12 11

10

9 0

10

20 30 40 50 61

WEIGHT (1,000 POUNDS)

ANGLE OF BANK (DEGREES)

130

I

s

6

110 5

90

80

170

D

Figure V-l 1

9

Issued

:

November 3,1978

Reissued: November 2, 1979 PERFORMANCE

5-13


16/78

SPEEDS

TAKEOFF ROTATE SPEED, VR

Takao ff rotate spaad, VR. is the greata of VMCA or VS,

MINIMUM CONTROL SPEED, VMCA (KCAS = KIAS ON THE GROUND)

Conditions:

l Flaps up or takeoff l Windmilling propeler on inoperative engine

l Anti-ice off with NTS operative

l Bleed Air Of f (Use same SDeeds for Bleed l Takeo ff power on the operating engine

Air On) l 5” of bank toward the operating engine

I

[ ISA 1 ISA

ISA

-1vC

ISA

+30

107

107

107

107

106

1W

96

95

93

92

90

89

STALL SPEED, VS1. (KCAS = KIAS ON THE GROUND)

Conditions.

l Gear Down

l Flaps takeoff

l Zero thrust

GiS%%:3ht

.500 9,000

9,500 10,DOO 10,500 11,000

11,500 12.000 12.500

VS1 IKCAS) 80 82 85

87 89 92 94 96 99

TAKEOFF SPEED A T 50 FOO T HEIGHT, Vgj (KIAS’)

VS~ IS THE GREATER OF 1.1 VMCA, OR 1.3 VS1, BUT NOT

GREATER THAN 116 KIAS

1-l lCA

ISA

ISA ISA ISA ISA ISA ISA

Altitude (Fee t) -30°C -2BC

-1BC

ISA

+1Qc +2 O=C +30x +40x

S.L. 115 115 115 115 115 109 103 99

2.~ 115

115 115 115 113

107

102 97

4,ooo 115 115 115

115 110 105 100 96

6.ooO 115 115

115 113 108 104 99 94

8,000

115 115 115 110

106

102 97 93

10,DDo 115

115 112 lea 103

loo

96

92

1.3 Vs OR 116 KIAS

Weight (Pounds) 8,500 9,OD O 9,500 10,cMo 10,500 ll,ODD-12,500

1.3 VSJ or

116 KIAS 102 105 108 111 114 116

‘For KCAS in flight, with the normal airspeed syste m. add 2KTS.

Assumes no instrument error.

Figure V-12

5-14 PERFORMANCE

,

Issued:

November 3,1978

Reissued: November 2,197g


17/78

CLIMB SPEEDS

TWO ENGINE BEST ANGLE (Vjo

AND BEST RATE OF CLIMB (Vy) SPEEDS


POWER

...................... MAXIMUM CONTINUOUS

FLAPS.. ..................................... ..U P

LANDING GEAR ................................. UP

ELECTRICAL LOAD ............ .300 AMPERES (TOTAL)

BLEEDAIR.. ................................. ..O N

ANTI-ICE ............................. AS REQUIRED

TWO ENGINE BEST ANGLE OF CLIMB SPEEDS

VX

The two-engine best angle of climb

speed, VX, is limited by VMCA (107 KCAS,

105 KIAS) at all altitudes from sea level

through 12,000 feet on cold days.

Use 105 KIAS for VX at

all gross weights.

TWO ENGINE BEST RATE OF CLIMB SPEEDS

Vy (KIAS)

Pressure

Altitude

(Feet)

GROSS WEIGHT (Pounds)

8,500

I

10,500

I

12,500

S.L. 138 139 141

5,000 131 134

137

10,000 125 129 133

15,000 119

124

129

20,000 113

119

125

25,000

108 114

121

Figure V-l 3

.

Issued :

November 3,1978


PERFORMANCE

5-15

,


18/78

CLIMB SPEEDS

SINGLE ENGINE BEST ANGLE (VXSE)

AND BEST RATE OF CLIMB (VYSE) SPEEDS


POWER. MAXIMUM CONTINUOUS ON OPERAT ING ENGINE

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..UP

LANDING GEAR.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

ELECTRICAL LOAD.. . . . . . . . . . . . . . . . . . . . .300 AMPERES

BLEEDAIR.....................................OFF

ANTI-ICE .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

INOPERATIVE ENGINE.. . . . . . . PROPELLER FEATHERED

,

SINGLE ENGINE BES T ANGLE OF CLIMB S PEEDS

VXSE (KIAS)

Pressure

Altitude

GROSS WEIGHT /Pounds)

(Feet) 8,500’

10,500

12,500

0

105

107 116

5,oBo 105

108 118

10,000 105

110 120

15,000

100 111 121

20,000 100

113 123

25,000

100 114 124

l VXSE is limited by VMCAat lower altitudes.

SINGLE ENGINE BES T RATE OF CLIMB SPEEDS

VySE

(KIAS)

Pressure

Altitude

(Feet)

S.L.

5,000

10,000

15,000

20,000

25,000


8,500 10,500 12,500

123 128 135

118 124 130

115 120 126

110 116

122

106 113 118

102

109 114

NOTE

To achieve the published single engine performance, the airplane

must be flown with minimum side slip and yaw as determined

from the turn and bank indica tor. Up to 5” of bank into the

operating engine may be required at maximum continuous power

and airspeeds near VMCA.

Figure V-14

I

5-16

I

PERFORMANCE

I

ssued: November 3, 1978


I


19/78

MAXIMUM WEIGHT FOR CONTINUED TAKEOFF AFTER ENGINE FAILURE AT VR


POWER.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKEOFF

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKEOFF

LANDING GEAR.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN

BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

ANTI-ICE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

SPEEDS . . . . . . . . . . . . . . . . . . . . . . .

VR

PER FIGURE V-12

1

NOTE

l This chart represents the capability to maintain altitude in the

takeoff configuration at VR with one engine inoperative, pro-

peller in NTS mode, and no ground effect.

l To successfully comple te a critical single-engine takeoff the

land ing gear must be retracted as soon as possible after lifto ff.

Maintain minimum obstacle clearance height until singie-

engine best rate-ofclimb speed is attained.

a

i=

8,000

E

u

10,000

6,000

2,000

MAXIMUM TAKEOFF WEIGHT (1,000 POUNDS)

Figure V-l 5

r

issued: November 3, 1978


PERFORMANCE

5-17

b


20/78

TWO-ENGINE TAKEOFF DISTANCE - BLEED AIR ON TAKEOFF SPEEDS


POWER ............. ........... TAKEOFF POWER SET

BEFORE BRAKE RELEASE (SEE NOTE BELOW)

FLAPS ............. ..... TAKEOFF; RETRACT AT V56

LANDING GEAR ........... RETRACT AFTER LIFT-OFF

RUNWAY .... .... .... .. PAVED, LEVEL, DRY SURFACE

BLEED AIR ............ ............ ............ .ON

ANTI-ICE ........... ............. ............ . .OFF

SPEEDS ............ ............ ..... SEE SCHEDULE

MAXIMUM FUEL IMBALANCE .... .... .... ,156 POUNDS

INOTE 1

tatic takeoff power not to exceed 97 torque.

I

I

AT LIGHTER WEIGHTS, AIRPLANE MAY TEND TO SLIDE

WITH MAXIMUM STATIC POWER SET.

I

ROTATE SPEED, VR (KCAS = KIAS) IS THE

GREATER OF VMCA OR VSt

VMCA

ISA ISA ISA ISA

ISA ISA ISA

Alttude (Feet) -3BC -20°C -1Bx ISA +1t?c +2c?x t 30°C +4oT

S.L. 107 107 107 107 to7 101 96 92

%ooo

107 107 107 107 105 loo 95 90

4.6fXf 107 107 107 107 102 98 93 89

6.ooO 107 107 107 lB4 100 96 92 BB

B.000 107 107 106 102 98 94 90 87

10,696 107 107 164 196 96 93 69 85

VST, TAKEOFF FLAPS

G y&W’J;rjht

6,566 9,000 9,500 10,000 10,5cm 11,606 11.5aJ 12,fXxl 12.500

VSl (KCAS) 60 82 85 87 89 92 94 96 99

TAKEOFF SPEED AT 50 FOOT HEIGHT, V50 (KIAS”‘)

V56 IS THE GREATER OF 1.1 VMCA, OR 1.3 VSt, BUT N OT


10,clcKl 115 115

112 196 103 loo 96 92

1.3 VS, OR 116 KIAS

Weight (Pounds) 8.500 9,BDC t 9,500 10,000 10.5B6 11,6BB 12,500

1.3 VSt or

116 KIAS 102 165 108 111 114 116

‘For KCAS in flight, with the normal arspeed system, add 2 KTS .



21/78

7

I

s

N

m

b

3

1

R

s

N

m

b

2

1

P

R

O

M

N

5

1


22/78

TWO-ENGINE TAKEOFF DISTANCE - BLEED AIR OFF TAKEOFF SPEEDS


POWER ............ ............ TAKEOFF POWER SET

BEFORE BRAKE RELEASE fSEE NOTE BELOW)

FLAPS ..................

TAKEOFF; RETRACT AT V59

LANDING GEAR ........... RETRACT AFTER LIFT-OFF

RUNWAY .... .... .... .. PAVED, LEVEL, DRY SURFACE

BLEEDAIR....................................OF F

ANTI-ICE

.....................................

.OFF

SPEEDS ............ ............ ..... SEE SCHEDULE

MAXIMUM FUEL IMBALANCE .... .... .... .150 POUNDS

I

NOTE

1

ROT ATE SPEED, VR lKCAS = KIAS) IS THE

GREATER OF VMCA OR VSl

VMCA

ISA ISA ISA ISA ISA

ISA

ISA

Alttude (Feet) -30

-29°C

-1DC

ISA t1vc +2Lrc t3vc +4uC

S.L. 107 107 107 107 107 101 96 92

2.000 107 107 107 107 105 199 95 90

4.990 107 107 107 107 102 98 93 89

6.000 101 107 107 194 166 96 92 88

8,000 107 107 196 102 98 94 90 87

10,000 107 107 194 196 96 93 89 85

VSl, TAKEOFF FLAPS

Static takeoff power not to exceed 97 torque. I G i~~“~~ ~ 9 h t

8,500 9,000 9,500 10,906 10,566 11,BBB 11,596 12,099 12,5c ttJ

VSl IKCA SI 80 82 85 87 89 92 94 96 99

AT LIGHTER WEIGHTS, AIRPLANE MAY TEND TO

SLIDE

TAKEOFF SPEED AT 50 FOOT HEIGHT, V50 (KIAS”)

WITH MAXIMUM STAT IC POWER SET . V5B IS THE GREATER OF 1.1 VMCA, OR 1.3 VSl, BUT NOT


1.1 MCA

1.3 VS, OR 116 KIAS

ISA ISA ISA ISA

+toC t2tPc

+3vc t4vc

115 169 103 99

113 107 102 97

110 105 100 96

199 104 99 94

196 102 97 93

103 100 96 92

Weight (Pounds1 8.569 9,000 9,500 10,066 10.500 11,999 12,599

1.3 vst or

116 KIAS 102 105 108 111 114

116

‘For KCAS in flight, with the normal arspeed system, add 2 KTS.



23/78


24/78

TWO-ENGINE TAKEOFF DISTANCE WITH FUEL

IMBALANCE (500 POUNDS MAXIMUM)


POWER.. . . . . . . . . . . . . . . . , . . . . TAKEOFF POWER SET

BEFORE BRAKE RELEASE ISEE NOTE BELOW)

FLAPS.................. TAKEOFF; RETRACT AT V5D

LANDING GEAR.. . . . . RETRACT AFTER LIFT-OFF

RUNWAY. . . . . . . . . .

PAVED, LEVEL, DRY SURFACE

BLEEDAIR....................................OFF

ANTI-ICE.. . . . . , . . . . . . . . . . . . . . . . . . .OFF

SPEEDS . .

NORMAL SPEED PLUS 10 KTS; SEE SCHEDULE

FUEL IMBALA NCE.. . . . . . . 150 TO 500 POUNDS

NOTE

Static takeoff power not to exceed 91 torque.

l

WITH MAXIMUM STAT IC POWER SET.

TAKEOFF SPEEDS WITH FUEL IMBALANCE

ROTATE SPEED, VR (KCAS = KIAS) IS THE

ISA

--3VC

117

117

117

117

117

117

GREATER OF ti&A +I0 OR VS1 +lO

ISA

-2vc

117

117

117

117

117

117

hCA +‘O

ISA

+40-c

102

100

99

98

97

95

Weight (Pounds)

8.500 9,000 9,500 10.000 10,500 11,DO fJ

11,500 12,000 12,500

VSj +lOKlAS 90 92 95 97

99 102 104 106 109

TAKEOFF SPEED AT 50 FOOT HEIGHT, V50 (KIAS”)

V50 IS THE GREATER OF 1.1 VMCA +lO, OR 1.3 VSl +lO, BUT NOT


1.1 VMCA +lO

ISA ISA

ISA ISA ISA

-1vc ISA +tvc

+2vc +3vc +4vc

125 125 125 119 113 109

125 125 123 117

112

107

125 125 120 115

110 106

125 123 118 113 109 104

125

120 116 112 107 103

122 118 113 110 105 102

1.3 VS +lO, OR 126 KIAS

Weight (Pounds)

8,500

9,ODlJ

9,500

10.000 10.500

11.000 12.500

1.3 vs1+ 10

or 126 KIAS 112

115 118 121 124

-

126

*For KCAS in flight, with the normal arspeed system, add 2 KTS .



25/78

WIND WMPONENT

OBSTACLE WEIGMT

(KNOTSI

(FEET)

Figure V-18


26/78

ACCELERATE-STOP DISTANCE - BLEED AIR ON

ENGINE FAILURE SPEED:

VR FROM FIGURE V-12


POWER. , . . . . . . . . ..(l ) TAKEOFF POWER SET BEFORE

BRAKE RELEASE.

(2) GROUND IDLE AT ENGINE

FAILURE SPEED.

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKEOFF

BRAKING................................ MAXIMUM

RUNWAY. . . . . . . . , . . . . . PAVED, LEVEL, DRY SURFACE

t

NOTE

m

I

Distance includes a failure recognition time of 3 seconds.

I

i

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27/78

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28/78

ACCELERATE-GO DISTANCE (ENGINE FAILURE DURING TAKEOFF, TAKEOFF CONTINUED)


Power. .TAKEOFF POWER SET BEFORE BRAKE RELEASE

Flaps....................

TAKEOFF, RETRACT AT V50

Landing Gear.. . . . . . . . . . . . . . RETRACT AFTER LIFT-OFF

Runway . . . . . . . . . . . . . . . .


Bleed Air. . . . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Anti-Ice.. . , . . . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

Speeds. . . . . . . . . . . .

. .ENGINE FAILURE ASSUMED AT VR

(See schedule, page 5-18)

Maximum Fuel Imbalance. . . . . . , . . . . . . . . . . . .150 POUNDS

NOTE

l As soon as practical after lift-of f (1) retract gear, (2) feather

propeller, (3) turn b leed air off.

l Avoid over-rotation. Accelerate to best rate of climb speed

while maintaining minim um clearance above obstacles.


29/78

I

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30/78

SINGLE ENGINE CLIMB GRADIENT AT VBo


POWER

.................................. .TAKEOFF

LANDING GEAR ................................. UP

FLAPS

.................................. .TAKEOFF

BLEEDAIR....................................OF F

ANTI-ICE

..................................... .OFF

INOPERATIVE PROPELLER

.............. FEATHERED

CLIMB SPEED

.................

.VBo PER FIGURE V-12

OAT (%I

WEIGHT (1,WO POUNDS)

Figure V-21

5-28

I

PERFORMANCE

I

Issued:

ovember 3, 1978

Reissued: November 2, 1979.

I


31/78

TWO:ENGINE TAKEOFF CLIMB GRADIENT AT V50


POWER ........ ........ ......... ........ . .TAKEOFF

LANDING GEAR

................................. UP

FLAPS ........ ........ ......... ........ . *TAKEOFF

BLEED AIR

.................................... .ON

ANTI-ICE ......... ........ ........ ........ ..... OFF

CLIMBSPEED ........ ......... .V50 PER FIGURE V-12

OAT (%I

WEIGHT (1,000 POUNDS)

Figure V-22


32/78

RATE-OF-CLIMB -TWO ENGINE

ASSOCIATED CONDITIONS;

POWER.

... ..... . MAXIMUM CONTINUOUS

FLAPS .............................

UP

LANDING GEAR ....... ........ ...... UP

BLEED AIR

........................ .ON

ANTI-ICE .........................

.OFF

I

._--

With anti-ice on, reduce two engine normal rate of climb

by 450 fpm.

I

OBTAIN OAT FROM IOAT (Figure V-2)

I

BEST RATE OF CLIMB SPEEDS. KIAS

I

8,000 128 131 134

12,000 123 127

131

16,000 118 124 128

I 20,000 113 119

125

24,000 109 116

122

28,000 104

111 119


33/78

0

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34/78

RATE-OF-CLIMB - SINGLE ENGINE


POWER ..... ..... MAXIMUM CONTINUOUS

FLAPS .............................

UP

LANDING GEAR

.....................

UP

BLEED AIR

.......................

.OFF

ANTI-ICE

..........................

OFF

INOPERATIVE ENGINE ..... . PROPELLER FEATHERED

rr NOTE ‘-,

I

With anti-ice on, reduce single engine rate of climb by 200 fpm.

I


Pr. Alt.

(Feet)

S.L.

5,000

SINGLE-ENGINE BEST

RATE OF CLIMB SPEEDS, KIAS


8,500 10,500

12,500

123 128 135

118 124

130

10,000

I

11s

I

120

126

15,000 110 116 122

20,000 106

113 118

25,000 105

109 114


35/78

Ec

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\


36/78

v s

CABIN ALTITUDE FOR VARIOUS FLIGHT ALTITUDES

CABIN DIFFERENTIAL

PRESSURE, PSI

0

5 10

15

20 25 30

FLIGHT PRESSURE ALTITUDE (1,000 FEET)

Figure V-25

I

5-34

I

PERFORMANCE

I

ssued: November 3,1978


I


37/78

TWO-ENGINE -SERVICE CEILING


POWER.. . . . . . . . . . . . . . . . . . . . .MAXIMUM CONTINUOUS

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

UP

BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ON

ANTI-ICE . . . .

. . . . . . . . . . . . . . . . . ..*..............

OFF

(TWO-ENGINE BEST RATE-OF-CLIMB SPEED PER

FIGURE 23).

the airplane has the capability to climb at 100 feet/minute.

w

5

26,099

Issued: November 3,1978


Revised: March 12,1981

PERFORMANCE

5-35


38/78

SINGLE ENGINE SERVICE CEILING


POWER.. . . . . . . . . . . . . . . . . . . . .MAXIMUM CONTINUOUS

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..UP

LANDING GEAR.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

ANTI-ICE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

INOPERATIVE PROPELLER . . . . . . . . . . . . . . FEATHERED

(SINGLE-ENGINE BEST RATE-OF-CLIMB SPEED PER

FIGURE 24).

NOTE

l

The singleengine service ceiling is the pressure altitude at

which the airplane has the capability to climb at 50

feet/minute.

l Additional performance may be obtained by turning bleed air

OFF.

1 5-36 1 PERFORMANCE

I



Revised: March 12, 1981

I


39/78

_ _-- ----- --

SINGLE ENGINE SERVICE CEILING

24,WO

Figure V-27

Issued:

November 3,1978


PERFORMANCE

5-37


40/78

TIME, FUEL, AND DISTANCE TO CLIMB


RPM ......... ......... ........ ......... ...... 100%

EGT.. ......... ........ ......... ......... .. ..65CP C

OR TORQUE ........ ......... ......... ....... 100%

iNoTE ‘F)

dd up to 100 pounds for Start, Taxi, and Takeoff.

Examole:

OAT AtTakeoff

................................

.22”C

OAT At Cruise

.................................

.-7X

Airport Press. Alt.,

..........................

3,000 Feet

Cruise Altitude

............................

17,000 Feet

Takeoff Weight. .........................

11,000 Pounds

Time To Climb (8-l)

........................

.7 Minutes

Fuel To Climb (108-18).

.....................

90 Pounds

Distance To Climb (21-2.5).

......... ........ . .18.5 N.M.

. . . . . . . . . . . . . . . .._......................................

. . . . . ..__-


41/78

OAT (cc)

Altitude

Feet

S.L.

5,000

10,000

15,000

20,000

25,000

CLIMB SPEED - KNOTS. IAS j

8,500 1 10,500 12,500

138 I 139 141

I 1

TIME,(MINUTES) 1 1

-

l*l,l, I( I,1 ,I II

0 50 100 150 200 300 350

I ’

l25O1

[FUEL (POUNDS)

i ,I ,I, J ,I, ,I, :J

o lo 20 30 405060708090100

Figure V-28

DISTANCE (NAUTICAL MILES)

(ZERO WIND)


42/78

MERlINI1IIB


PERFORMANCE

I

IssuedNovember 3, 1978


I


43/78

RANGE PROFILE -STANDARD DAY

LONG RANGE CRUISE POWER


WEIGHT ............................. 12,500 POUNDS

FUEL

........................

.AVIATION KEROSENE

RPM..........................................98

AIRSPEED

.......... ...... FOR 99 MAXIMUM RANGE

Range include s S tart, Tax i, Clim b, and Descent with 45 minutes

reserve fuel at holding speed and power at 5,000 feet. Do not

exceed service ceiling.

RANGE (NAUTICAL MILES)

Figure V-29


44/78

C

~

o

m

Z

A

~

g

i

E

8

z

i

r

L

2

1

2

x

-

F

s

:

9

:

2

.

.

........

5

4

P

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45/78

RANGE PROFILE - ISA +WC

I

MAXIMUM CRUISE SPEED


WEIGHT .. . . . . . . . . . . . . . . . . . . . . . . . . . . . 12,500 POUNDS

FUEL.. . . . . . . . . . . . . . . . . . . . . . . . AVIATION KEROSENE

RPM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ...99

AIRSPEED .. . . . . . . . . . . . . . . FOR 99 MAXIMUM RANGE

RANGE (NAUTICAL MILES)

Figure V-31


46/78

.

.

.

.

.

.

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.

.

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.

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.

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.

.

.

.

.

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.

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.

.

.

.

.

.

.

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1

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47/78

>d

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.


48/78

ENDURANCE PROFILE -STANDARD DAY

MAXIMUM CRUISE SPEED AT 99% RPM

Conditions:

l Engine power and atmospheric condil

l Electrical load of 100 amperes (total)

l

Bleed air on

l Anti-ice off

l Flaps up

l Gear up

l 12,500 pound takeoff gross weight

ns as noted on chart

NOTE

Range Includes:

l

Reserve fuel for 45 minutes holding speed and power at 5,000

feet.

l

Climb (per appl icable Time, Fuel and Distance to climb chart,

Figure V-28).

6 Descent (per Figure V-48).

30,000

25,900

20,BBo

15,000

10,000

5,t3fJO

0

0 1 2 3

END”& WHO”&

6 7 8 9

Figure V-34


49/78

HOLDING TIME


WEIGHT.. . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,000 POUNDS

OAT...........................................ISA

RPM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ...98%

TORQUE/ET . . . . . . . . . . . . . . . . . . . . . FOR LEVEL FLIGHT

SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.4VS

(SEE SPECIFIC RANGE CHARTS)

BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

ANTI-ICE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

Examples:

1. Fuel Available 1,500 Pounds

Pressure Altitude 10,000 Feet

Holding Time

3 Hours 23 Minutes

2. Required Holding Time

1+ 30 Hours

Holding Altitude 5,000 Feet

Fuel Required

750 Pounds

Fuel

Requirement

Or

Available

(Pounds) S.L.

HOLDING TIME (HOURS: MINUTES)

Pressure Alt itude (Feet)

5,000

10,000 15,000 20,000 25,000 30,000

250

0:27 0:31 0:34 0:38 0:41 0:45 0:45

500 0:55 1:02

1:08 1:16 1:22 1:29 1:31

750 1:23 1:34

1:42 1:54 2:03 2:14 2:16

1,000 1:51 2:05 2:16 2:32

2:45 2:59 3:02

1,250 2:19 2:36 2:49 3:lO

3:26 3:44 3:47

1,500 2:47 3:08

3:23 3:48 4:07 4:29 4:33

1,750 3:14 3:39

3:57 4:27 4~48 5:14 5:18

2,000 3:42 4:ll 4:31 5:05 5:30 5:58 6:04

2,250 4:lO 4:42 5:05 5:43

6:ll 6:43 6:49

2,500

4:38 5:13 5:39 6:21 6:52 7~28 7:35

2,750 5:06 5:45 6:13 6:59 7:33 8:13 8:20

3,000 5:33 6:16 6:47 7:37 8:15 8:58 9:06

Total

Fuel Flow

(pounds/hour)

540 480 440 395 365 335 330

-

Figure V-35

.



PERFORMANCE

5-47


50/78

FUEL FLOW, SPECIFIC RANGE, AND CRUISE SPEEDS,

WEIGHT 8,000 POUNDS, ISA, 9896 RPM

TRUE AIRSPEED (KNOTS)

Figure V-36

PERFORMANCE

I

Is Ned:ovember 3, 1978


I


51/78


WEIGHT 10,000 POUNDS, ISA, 98% RPM

.--

l-20 140 160 180 200 220 240 260 280 300


Figure V-37

SSWd: November 3, 1978


I

PERFORMANCE

5-49

I


52/78

FUEL FLOW, SPECIFIC RANGE, AND CRUISE SPEEDS



Figure V-38

PERFORMANCE

I

Issued:ovember 3, i978


I


53/78

FUEL FLOW, SPECIFIC RANGE, AND CRUISE SPEEDS

WEIGHT 8,000 POUNDS, ISA +15”c, 9896 RPM

120 140 160 180 200 220 240 260 280 300


Figure V-39

ssued:

November 3, 1978


I

PERFORMANCE

5-51

I


54/78


WEIGH-T 10,000 POUNDS, ISA +15X, 98% RPM

Figure V-40

5-52

PERFORMANCE



,


55/78


56/78




Figure V-42

I

5-54

I

PERFORMANCE

I

ssued:

November 3,1978


I


57/78

MERLIN lIB




Figure V-43

ssued:

November 3,1978


I

PERFORMANCE


58/78

MERLINJKB-

.

F

UEL FLOW, SPECIFIC RANGE, AND CRUISE SPEEDS,



Figure V-44

PERFORMANCE

I

Issued:ovember 3, 1978


I


59/78

FUEL FLOW, SPECIFIC RANGE,AND CRUISE SPEEDS,

WEIGHT 8,000 POUNDS, ISA +15%, 9596 RPM


Figure V45

November 3,1978


PERFORMANCE


60/78

UEL FLOW, SPECIFIC RANGE, AND CRUISE SPEEDS,

WEIGHT 10,000 POUNDS, ISA +15”C, 95% RPM

Figure V-46

5-58 1

PERFORMANCE

I




61/78


WEIGHT 12,000 POUNDS, ISA +15”c, 96% RPM


Figure V-47



PERFORMANCE

5-59


62/78

TIME, FUEL, AND DISTANCE TO DESCEND


RATE OF DESCENT ....................

1,500 FTJMIN.

AIRSPEED ................................ 215 KCAS

POWER ...............................

AS REQUIRED

LANDING GEAR .................................

UP

FLAPS.. .....................................

..U P

RPM..........................................98 %

Example:

Initial Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25,000 Feet

Final Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,000 Feet

Time To Descent (16.8-6.6).

................ 10.2 Minutes

Fuel To Descend (133-58). ................... 75 Pounds

Descent Distance (74-28). ......................

46 N.M.

I

5-60

I

PERFORMANCE

I



I


63/78

TIME, FUEL, AND DISTANCE TO DESCEND

I

I

I

1 TIME TO DESCEND (MINUTES) ; 1

I

,’ ,’ 1 ’ 1 1 1 II I

0 10 20 30

1 I

40 501 601 70 80 90 1001

I

I I

; DESCENT,DISTFNCE ((NAUTICAL MI LE,S)

I

I

I I

I

I

,

I

0

I

20 40 60 80 100 120 140 160 180

FUEL USED TO DESCEND (POUNDS)

Figure V-48

7

Issued : November 3,1978


PERFORMANCE 5-61


64/78

RATE-OF-CLIMB - BALKED LANDING


POWER

.... .... ....... .... ... MAXIMUM CONTINUOUS

FLAPS..

..................................

..DOW N

LANDING GEAR

.............................. DOWN

BLEED AIR

.................................... .ON

ANTI-ICE

......................................

OFF

CLIMB SPEED

........ ....... .... .105 KIAS (107 KCAS)

[rNoTE ‘1

ith antwce on, reduce balked landing rate of climb by 300 fpm.



65/78

I

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66/78


5-64

PERFORMANCE




67/78

SINGLE ENGINE LANDING DISTANCE WITHOUT REVERSING OR ANTI-SKID BRAKES


POWER ..........

FLAPS ..........

RUNWAY. .......

APPROACH SPEED

BRAKING. .......

BLEEDAIR.. ....

ANTI-ICE ........

..................

FLIGHT IDLE

........................

DOWN

. PAVED, LEVEL, DRY SURFACE

......... 1.3 VS AS TABULATED

.................... MAXIMUM

....................... ON/OFF

....................... ON/OFF

WEIGHT SPEED AT 50 FEET* IKNOTSI

[POUNDS) (KCAS) (KIAS)

12,500

116 115

11,500 110 109

10,500 105 104

9,500 99 97

8,500

93 91

*APPROACH AIRSPEED SHOULD NOT BE

LESS THAN VMCA UNT IL THE LANDING

IS ASSURED.

(FEET)

Figure V-50


68/78

TWO-ENGINE LANDING DISTANCE WITHOUT REVERSING OR ANTI-SKID BRAKES


POWER. . . . . . . . . . . . . . . . . .

FLIGHT IDLE, GROUNO IDLE

AFTER TOUCHDOWN

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..DOWN

RUNW AY. . . . . . , . . . . . . .


APPROACH SPEED.. . . . . . . . . . . . 1.3 VS AS TABULATED

BRAKING................................MAXlMUM

BLEED AIR . . . . . . . . . . . . . . :. . . . . . . . . . . . . . . . . .ON/OFF

ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON/OFF

WEIGHT

I

SPEED AT 50 FEET’

IPOUNDS) lKCASI (KIAS) I

OAT PCC)

WEIGHT (1,OOB POUNDS)

Figure V-5 1

WIND (KNOTS) OBSTACLE HEIGHT

(FEET)


69/78

1

TWO-ENGINE LANDING DISTANCE WITH FLAPS UP

ASSi)CIATED CONDITIONS:

POWER. . . . . . . . . . . . . . . . . . FLIGHT IDLE, GROUND IDLE

AFTER TOUCHDOWN

FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..UP

RUNW AY. . . . . . . . . . . . . . PAVED , LEVEL, DRY SURFACE

APPROACH SPEED .. . . . . . . . . . . . 1.3 VS, AS T ABULA TED

BRAKING................................ MAXIMUM

SPEED AT 50 FEET

12,500 132

130

11,500 126 123

10,500 121 119

9,500 115 113

6,500 109 107

OAT PC1 WEIGHT (1,OOOPOUNDS)

Figure V-52

WIND (KNOTS) OBSTACLE HEIGHT

(FEET)


70/78

TWO ENGINE SHORT-FIELD LANDING DISTANCE WITHOUT REVERSE


POWER., . . . . . . . . . . . . . . . . .

FLIGHT IDLE, GROUND IDLE

AFTER TOUCHDOWN

FLAPS......................................DOWN

RUNWA Y. . . . . . . . . . . . . .


APPROACH SPEED . . . . . . . . . . . . . 1.1 VS, AS T ABULA TED

BRAKING................................MAXlMUM

I

WEIGHT

SPEED AT 50 FEET

l

(POUNDS]

(KCASI (KIAS)

12,500 98 97

11,506 94 92

10,500 89 87

9,500 84 92

8,560 78 76

l

APPROACH SPEED SHOULD NOT BE

LESS THAN VMCA UNTIL LANDING IS

ASSURED.

OAT PC)

WEIGHT (1,ooO POUNDS)

WIND (KNOTS)

OBSTACLE HEIGHT

(FEET]

Figure V-53


71/78

SAMPLE FLIGHT

The following is an example of a typical flight using performance data in Section 5 and the weight

and balance data in Section 6.

AIRPLANE CONFIGURATION C (Figure VI-13):

Weight

Basic Operating Weight.

....................... .8,550

(Includes pilot, copilot & crew supplies)

Passengers 4 @ 170 Pounds each.

.................. .680

Passenger Baggage 6 @ 20 Pounds each

.............. .120

Fuel Load 485.07 Gallons

...................... 3,250

Ramp Weight

................................ 12,600

Arm

Moment/l

,000

157.47

1346.38

Takeoff Condition. . . . . . . . . . . . . . . . . . . . . . . . . . . . 12,500

2,056.94

GIVEN:

Departure Airport

Data (Assumed) :

Runwav Length..

...............................................

8,000 Feet (Runway 7)

Temperature

.......................................................

.21X (ISA +lOC)

Pressure Altitude

.............. ............... ............... ............. .2,000 Feet

Wind ..............................................................

llpat25Knots

Obstacles ....................................................................

None

Cruise Conditions (Assumed) :

Distance

........................................................

..900NauticalMile s

Cruise Altitude

.........................................................

.25,000 Feet

Temperature

.............. ............... ................ ......... .-20°C (ISA +15”C)

Wind..............................................................40KnotTailwin d

Power

............... ................ ............... .......... Maximum Cruise Speed

Destination Airport Data (Assumed) :

RunwayLength...........................................................6.000Fee t

Temperature

.............................................................

.9% (ISA)

Pressure Altitude.

........................................................

.3,000 Feet

Wind........................................................................Cal m

Landing Weight .............. ................ ............... ......... To Be Calculated

Obstacles ....................................................................

None

I

ssued : November 3,1978


I

PERFORMANCE


72/78

MERLIMLKB

SAMPLE FLIGHT (continued)

SAMPLE CALCULATIONS:

Wind Component Chart (Figure V-l ):

(1) The angle between the prevailing wind and the runway is 40 degrees.

(2) Enter Figure V-l on the 40 degree wind line and proceed in toward 0 unt il intersecting the 25

knot arc.

(3) Read horizontally to the left from this point. Headwind component 19 knots.

Two Engine Takeoff Distance (Bleed Air-On) [Figure V-161:

(1) Enter Figure V-16 at 21% and proceed up until intersecting the 2,000 foot line.

(2) Proceed horizon tally right to wind component reference line and follow the down sloping line

unt il it intersects 19 knots headwind.

(3) Proceed horizontally right to distance and read the ground distance of 2,400 feet.

(4) Return to the obstacle heigh t reference line.

(5) Follow the sloping lines up unt il the 50 foot heigh t scale is intersected and read the tota l takeoff

distance of 3,550 feet.

(6) Use the adjacent tables to determine the takeoff speed schedule: VR = 105 KIAS, V50 = 116

KIAS.

(7) Consult Figure V-15, V-19, and V-20 to evalua te the possibility of cont inuing the takeoff in the

event of an engine failure, and Figure V-19 to estimate the distance to accelerate to VR and stop.

Rate-of-Climb - Two Engine (Figure V-23):

(1) Enter Figure V-23 at 21°C and proceed up to 2,000 feet altitude (halfway between S.L. and

4,000 feet).

(2) Proceed horizontally right to weight reference line .

(3) Continue horizontally right to rate-of-climb line and read rate-of-climb of 2,425 feet per minute.

(4) Determine the best rate-of-climb speed schedule, using the adjacent table: 140 KIAS, decreasing

to 122 KIAS at 24,000 feet.

PERFORMANCE

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ssued: November 3, 1978


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73/78


Rate-of-Climb - Sing le Engine (Figure V-24):

(1) Enter Figure V-24 at 21°C and proceed up to 2,006 feet altitude.

(2) Proceed horizontally right to weight reference line (intersects at 12,500 pounds).

(3) Continue horizontally right to rate-of-climb line and read rate-of-climb of 575 feet per minute.

(4) Note the single engine climb speed: 133 KIAS.

Time, Fuel, and Distance To Climb (Figure V-28):

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

Enter Figure V-28 at 21°C and proceed up unt il intersecting the 2,000 foot line (this isTakeoff

Temperature and Altitude).

Proceed horizontally right until intersecting 12,500 pound weight line.

Proceed down unt il intersecting distance line.

Read all values: Time = .5 minutes; Fuel = 10 pounds; Distance = 2 nautical miles.

Reenter Figure V-28 at -2BC and proceed up unt il intersecting 25,000 foot line (this is Cruise

Temperature and Altitude).

Proceed horizontally right until intersecting 12,500 pound weight line.

Proceed down unt il intersecting distance line.

Read all values:

Time = 20.5 minutes; Fuel = 230 pounds; Distance = 58 nautical miles.

Now proceed as follows:

Subtract item number 4 values from item number 8 values:

EXAMPLE :

Time/Minutes

Fuel/Pounds

20.5 230

-. 5

-10

20.0

220

Time to climb to 25,000 feet is 20 minutes.

Fuel to climb to 25,000 feet is 220 pounds.

Distance traveled during climb is 56 nautical miles.

Distance/Nautical Miles

58

-2



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Fuel Flow, Specific Range and Cruise Speeds, Weight 12,000 Pounds ISA +15”c, 98% RPM (Figure

v-41 ) :

(1) Enter Figure V-41 where maximum cruise speed line on far right intersects 25,000 foot pressure

altitude line.

(2) This point is located between the 450 and 500 pounds/hour fuel flow lines. Fuel flow is about

460 pounds per hour.

(3) Proceed down unt il intersecting TAS line and read true airspeed of 254 knots.

(4) Proceed horizontally left (from entry point in item #l above) until intersecting specific range

line and read nautical miles per pound of fuel consumed. Read .55, approximately 2 pounds of

fuel to travel 1 nautical mile.

(5) The exact fuel flow may be calcula ted by dividing the true airspeed by the specific range: 254 f

0.55 = 462 pounds per hour.

Time, Fuel, and Distance To Descend (Figure V-48):

(1)

(2)

(3)

(4)

(5)

(6)

(7)

Enter Figure V-48 at 25,000 feet (this is flight altitude) and proceed horizontally right until

intersecting the reference line .

Proceed down unt il intersecting fuel used to descend line.

Read al l values: Time = 16.7 minutes; Distance = 73 naut ical miles; Fuel = 132 pounds.

Re-enter Figure V-48 at 3,000 feet (this is destination airport altitude) and proceed hor izontal ly

right until intersecting the reference line.

Proceed down unt il intersecting fuel used to descend line.

Read all values: Time = 2 minutes; Distance = 7 naut ical miles; Fuel = 18 pounds.

Proceed as follows:

Subtract item number 6 values from item 3 values:

EXAMPLE :

Time/Minutes Fuel/Pounds

16.7

132

-2

-18

14.7

114

Distance/Nautical Miles

73

-7

66

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PERFORMANCE

Issued:

November 3, 1978



75/78


76/78


Third, determine cruise fuel consumed as follows:

(1) Find time to travel 778 naut ical miles at 294 knots = 2 hours, 39 minutes.

(2) Mul tiply 462 pounds per hour by 2 hours, 39 minutes = 1,224 pounds.

Complete Computations:

Climb Fuel 220 pounds

Cruise Fuel 1224 pounds

Descent Fuel

114 pounds

Total Fuel 1558 pounds

Fuel At Takeoff

Flight Fuel

Fuel Remaining

At Destination

3150 pounds

1558

1592pounds

Climb Time

Cruise Time

Descent Time

Total Trip Time

20 minutes

159 minutes (2 hours, 39 minutes)

14.7 minutes

193.7 minutes (3 hours, 13.7 minutes)

Determine Landing Weight:

Takeoff Weight 12,500

Fuel Consumed

-1,558

Landing Weight

10,942

Landing Distance Without Reversing Or Anti-Skid Brakes (Figure V-51), Using Destination Airport

Data Repeated Below:

Temperature

Pressure Altitude

Wind

Obstacles

9°C (ISA)

3,000 feet

Calm

None

Proceed As Follows:

(1) Enter f igure V-51 at 9°C and proceed up to 3,000 feet altitude.

(2) Proceed horizontally right unt il intersecting the weight reference line.

(3) Follow the down sloping line unt il intersecting the line corresponding to a weight of 10,950

pounds.

(4) Proceed horizontal ly right to the wind reference line.

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PERFORMANCE

4

Issued:

November 3, 1978

Reissued: November 2,

1979


77/78


(5) Continue horizontally right unt il intersecting the distance line (it is not necessary to follow the

head wind or tai l wind slope as the wind is calm).

(6) Read the landing ground distance of 1,550 feet.

(7) Return to the obstacle height reference line .

(8) Follow the sloping lines up the right to the 50 foot height scale, and read the total landing

distance, 2,600 feet.

(9) Using the Figure V-51 schedule, note the correct land ing approach speed: 107 KIAS.

Balked Landing - Rate of Climb (Figure V-49):

(1) Enter Figure V-49 at 9°C and proceed up to 3,000 feet altitude. (In this case, intersecting with

the ISA line.)

(2) Proceed horizontally right until intersecting limi t landing weight line .

(3) Follow the up sloping line unt il intersecting 10,950 pounds.

(4) Proceed horizontally right until intersecting rate of climb line and read the value of 1,580 feet

per minute.

Holding Time (Figure V-35) :

GIVEN:

Fuel Remaining at Destination

1,592 pounds

Holding Altitude 10,000 feet

FIND:

Holding time leaving 500 pounds of fuel for maneuvering and landing.

(1) Subtract 500 pounds from fuel remaining at destination:

1,592 pounds

-500

1,092 pounds

(2). Enter Figure V-35 at 1,000 pounds and proceed horizontally right until reaching the 10,000

foot pressure a ltitude column.

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Issued:

ovember 3, 1978


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PERFORMANCE


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(3) Read time value of 2 hours, 16 minutes.

(4) Re-enter Figure V-35 at 1,250 pounds and read 2 hours, 49 minutes.

(5) Interpolate to get 2 hours, 28 minutes holding time for 1,092 pounds of fuel.

Sec 5 226T B Performance

Documents

Transcript of Sec 5 226T B Performance