A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-i

SECTION 5

PERFORMANCE

TABLE OF CONTENTS

PARAGRAPH PAGE

5.1 GENERAL 5-1

5.2 INTRODUCTION - PERFORMANCE CHARTS 5-1

5.3 FLIGHT PLANNING EXAMPLE 5-2

5.4 AIRSPEED CALIBRATION 5-8

5.5 ALTIMETER CORRECTION 5-9

5.6 ALTERNATE STATIC SOURCE 5-9

5.7 TEMPERATURE CORRECTION CHART 5-9

5.8 WIND COMPONENT 5-9

5.9 STALL SPEED 5-12

5.10 TAKE-OFF DISTANCE 5-13

5.11 TWIN ENGINE CLIMB - MCP CLIMB 5-15

5.12 ONE ENGINE INOPERATIVE CLIMB 5-17

5.13 BALKED LANDING CLIMB 5-19

5.14 TIME, FUEL AND DISTANCE TO CLIMB - MCP 

CLIMB

5-21
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-ii DATE: 23 April 2015

SECTION 5

PERFORMANCE

TABLE OF CONTENTS

PARAGRAPH PAGE

5.15 CRUISE PERFORMANCE - BEST ECONOMY 

MIXTURE

• SEA LEVEL 5-23

• 3000 FT 5-24

• 6000 FT 5-25

• 9000 FT 5-26

• 12000 FT 5-27

5.16 OPERATING ENVELOPE 5-28

5.17 RANGE PROFILE 5-29

5.18 TIME, FUEL AND DISTANCE TO DESCENT 5-31

5.19 LANDING DISTANCE TO CLEAR 50 FT 

OBSTACLE

5-33
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-1

SECTION 5

PERFORMANCE

5.1 GENERAL

This section provides performance information applicable to the P.68R, 

required by certification regulations and useful for flight planning.

Performance information associated with those optional systems and 

equipment which required flight manual supplements are provided by Section 

8 (Supplements).

5.2 INTRODUCTION - PERFORMANCE CHARTS

Performance data charts presented in this Section may be used to know what 

to expect from the aircraft under various conditions, and also to facilitate the 

planning of flights with reasonable accuracy.

The performance charts are unfactored and do not make any allowance for 

varying degrees of pilot proficiency or airframe material or mechanical 

deterioration.

NOTE

Performance loss should be expected when 

incorporating external modifications causing a 

significant increase in the aerodynamic drag.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-2 DATE: 23 April 2015

5.3 FLIGHT PLANNING EXAMPLE

This paragraph provides information to facilitate the flight planning by using 

the pertinent performance data charts presented in this Section.

The following example illustrates the correct use of the performance charts.

NOTE

To obtain the fuel quantity in US Gal divide the 

fuel quantity expressed in lbs by 6.01.

Associated Conditions:

AIRCRAFT

Take-Off Weight 4200 lbs

Usable fuel 587.3 lbs (97.7 US Gal)

TAKE-OFF AIRPORT

Outside Air Temperature 21°C (ISA +10°C)

Pressure altitude 2000 ft

Wind direction and speed 180° at 8 Kts

Runway direction 330°

CRUISE

Outside Air Temperature ISA

Pressure altitude 6000 ft

En-Route Distance 400 nM

ARRIVAL AIRPORT

Outside Air Temperature 21°C (ISA +10°C)

Pressure altitude 2000 ft

Wind direction and speed 330° at 12 Kts

Runway direction 300°

Procedure:

Take-Off Distance

The measured take-off distances are reported as a function of ambient 

temperature, including variations for weight change and wind influence.

1. Calculate the angle between wind direction and runway direction

180°-330°= -50°

2. Calculate the wind component parallel to runway (from Figure 5-3)

5 Kts - tailwind
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-3

3. Enter Figure 5-5 at 21° OAT

4. Proceed horizontally right up to the 2000 ft airport altitude line

5. Proceed vertically downwards to the reference line

6. Follow the slope of the adiacent take-off lines until intersecting the 

horizontal 4200 lbs line

7. Proceed vertically downwards to the reference line

8. Follow the slope of the adiacent take-off lines until intersecting the 

horizontal 5 Kts - tailwind line

9. Proceed vertically downwards to obtain the required take-off distance of 

1680 ft (512 m)

Rate of climb – AEO MCP climb

1. Enter Figure 5-6 at 21° OAT

2. Proceed vertically upwards until intersecting the 2000 ft rate-of-climb 

graph

3. Proceed horizontally right up to the reference line

4. Follow the slope of the adiacent rate of climb lines until intersecting the 

vertical 4200 lbs line

5. Proceed horizontally right to obtain the AEO MCP rate of climb of 1170 

ft/min

Rate of climb – OEI climb

1. Enter Figure 5-7 at 2000 ft airport altitude

2. Proceed horizontally right up to the rate of climb at ISA +10°C

3. Proceed vertically downwards to the reference line

4. Follow the slope of the adiacent rate-of-climb lines until intersecting the 

horizontal 4200 lbs line

5. Proceed vertically downwards to obtain the OEI rate of climb of 250

ft/min

Rate of climb – Balked landing climb

1. Enter Figure 5-8 at 2000 ft airport altitude

2. Proceed horizontally right up to the rate of climb at ISA +10°C

3. Proceed vertically downwards the reference line

4. Follow the slope of the adiacent rate-of-climb lines until intersecting the 

horizontal 4200 lbs line

5. Proceed vertically downwards to obtain the OEI rate of climb of 770 

ft/min
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-4 DATE: 23 April 2015

Time, Fuel and Distance to Climb – MCP climb

Time, fuel and distance to climb are determined by calculating the difference 

between the airport and cruise conditions, thus the indicated procedure must 

be followed twice: the first for the airport conditions and the second for the 

cruise conditions.

1. Enter Figure 5-9 at the given altitude (airport or cruise)

2. Proceed horizontally right up to the time-to-climb line at given 

temperature

3. Proceed vertically downwards to the reference line

4. Follow the slope of the adiacent time-to-climb lines until intersecting the 

horizontal 4200 lbs line

5. Proceed vertically downwards to obtain the time to climb at the given 

altitude

6. Repeat the steps from 1 to 5 to calculate the fuel to climb at the given 

altitude

7. Repeat the steps from 1 to 5 to calculate the distance to climb at the given 

altitude

In this example the calculation gives the following results:

Airport Time to Climb 1.5 min

Cruise Time to Climb 5.2 min

Time to Climb 5.2 - 1.5 = 3.7 min

Airport Fuel to Climb 4.4 lbs

Cruise Fuel to Climb 13.9 lbs

Fuel to Climb 13.9 - 4.4 = 9.5 lbs (1.6 US Gal)

Airport Distance to Climb 3.0 nM

Cruise Distance to Climb 7.0 nM

Distance to Climb 7.0 - 3.0 = 4.0 nM

Time, Fuel and Distance to Descent

Time, fuel and distance to descent are determined by calculating the 

difference between the cruise and landing airport conditions, thus the 

indicated procedure must be followed twice: the first for the cruise conditions 

and the second for the landing airport conditions.

1. Enter Figure 5-13 at the given altitude (cruise or airport)

2. Proceed vertically up to the time-to-descent line relating to selected R/S 

and read the required time to descent
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-5

3. Proceed vertically up to the fuel-to-descent line relating to selected R/S 

and read the required fuel to descent

4. Proceed vertically up to the distance-to-descent line relating to selected 

R/S and read the required distance to descent

In this example the calculation gives the following results, with a selected 

R/S of 500 fpm:

Landing Airport Time to Descent 4.0 min

Cruise Fuel to Descent 12.5 min

Time to Descent 12.5 - 4.0 = 8.5 min

Landing Airport Fuel to Descent 3.5 lbs

Cruise Fuel to Descent 11.5 lbs

Fuel to Descent 11.5 - 3.5 = 8.0 lbs (1.3 US Gal)

Landing Airport Distance to Descent 12.1 nM

Cruise Distance to Descent 36.5 nM

Distance to Descent 36.5 - 12.1 = 24.4 nM

Cruise Performance – Best Economy Mixture

The cruise distance is obtained by subtracting the calculated distance to climb 

and distance to descent from the total en-route distance:

Cruise Distance = En-route Distance - Climb Distance - Descent Distance

= 400 - 4.0 - 24.4 = 371.6 nM

The cruise power setting should be determined on the basis of the required 

and available fuel load.

From the Cruise Performance Table (figure 5-10), at a cruise altitude of 6000 

ft (ISA) and a power rating of 65.5% (2350 RPM and 22" Hg), the cruise 

airspeed is 159 KTAS at MTOW. Due to the lower take-off weight the cruise 

airspeed must be increased by 1 Kt.

From the same table, the fuel flow is 18.1 GPH (108.8 lbs/hr) total.

Cruise time and fuel may be calculated by the following formulas:

Cruise Time = Cruise Distance / Cruise Speed

= 371.6 / 160 = 2.32 hours or 139.3 min

Cruise Fuel = Fuel Flow x Cruise Time

= 18.1 x 2.32 = 42.0 US Gal (252.4 lbs)
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-6 DATE: 23 April 2015

Total Flight Time

The total flight time is determined by adding time to climb, cruise time, and 

time to descent:

Total Flight Time = Time to Climb + Cruise Time + Time to Descent

= 3.7 + 139.3 + 8.5 = 151.5 min

Total Required Fuel 

The total required fuel is obtained by adding fuel for start, taxi and take-off

(20 lbs), fuel to climb, cruise fuel, and fuel to descent:

Total Required Fuel = Fuel for Start, Taxi and Take-Off + Fuel to Climb + 

Cruise Fuel + Fuel to Descent

= 20.0 + 9.5 + 252.4 + 8.0 = 289.9 lbs (48.2 US Gal)

Reserve Fuel

The reserve fuel is determined by subtracting the calculated total required 

fuel from the usable fuel:

Reserve Fuel = Usable Fuel - Total Required Fuel

= 587.3 – 289.9 = 297.4 lbs (49.5 US Gal)

Reserve fuel must exceed 60 lbs to allow a minimum of 45 minutes of flight 

time at 45% power (2200 RPM).

Landing Distance

The measured landing distances (over 50 ft obstacle) are reported as a 

function of ambient temperature, including variations for weight change and 

wind influence.

1. Calculate the landing weight by substracting the total required fuel from 

the take-off weight

= 4200 - 289.9 = 3910.1 lbs

2. Calculate the angle between wind direction and runway direction

330°-300°= 30°

3. Calculate the wind component parallel to runway (from Figure 5-3)

10 Kts - headwind

4. Enter Figure 5-14 at 21° OAT

5. Proceed horizontally right up to the 2000 ft landing airport altitude line

6. Proceed vertically downwards to the reference line

7. Follow the slope of the adiacent landing distance lines until intersecting 

the horizontal 3910 lbs line
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-7

8. Proceed vertically downwards to the reference line

9. Follow the slope of the adiacent take-off lines until intersecting the 

horizontal 10 Kts - headwind line

10. Proceed vertically downwards to obtain the required landing distance of 

1360 ft (414 m)
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-8 DATE: 23 April 2015

5.4 AIRSPEED CALIBRATION

a. Airspeed Indicator System Error vs. I.A.S.

b. Airspeed Indicator System Error vs. C.A.S.

Figure 5-1

AIRSPEED CALIBRATION
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-9

5.5 ALTIMETER CORRECTION

The maximum static error correction to be applied to the altimeter reading 

does not exceed 30 feet.

5.6 ALTERNATE STATIC SOURCE

The alternate source valve is located on the left side of the control pedestal. 

No static error correction must be applied to the altitude and airspeed 

indicator readings when static air is supplied by the alternate static source.

5.7 TEMPERATURE CORRECTION CHART

See Figure 5-2.

5.8 WIND COMPONENT

See Figure 5-3.

Maximum demonstrated crosswind velocity for take-off and landing is 25 

Kts.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-10 DATE: 23 April 2015

Figure 5-2

TEMPERATURE CONVERSION
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-11

Figure 5-3

WIND COMPONENT
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-12 DATE: 23 April 2015

5.9 STALL SPEED

(Figure 5-4)

Associated Conditions:

Throttles IDLE

NOTE

Maximum altitude loss experienced during

conventional stall is 120 feet.

Maximum altitude loss experienced during one 

engine inoperative stall is 500 feet.

CONFIGURATION ANGLE OF BANK

0° 30° 60°

Weight 

(kg) FLAPS GEAR KIAS KIAS KIAS

2063

0° UP 67 72 95

0° DOWN 67 72 95

15° UP 64 69 91

15° DOWN 64 69 91

35° DOWN 61 65 86

1960

0° UP 65 70 93

0° DOWN 65 70 93

15° UP 62 67 89

15° DOWN 62 67 89

35° DOWN 60 64 84

Figure 5-4

STALL SPEED
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-13

5.10 TAKE-OFF DISTANCE

(Figure 5-5)

Associated Conditions:

Power 2700 RPM, full throttle, before brake release

Flaps 15°

Level, Hard Surface, Dry Runway

WARNING

Poor maintenance condition of the airplane, 

deviation from the given procedures as well as 

unfavorable external factors (e.g. high 

temperature, rain, unfavorable wind 

conditions, including cross-wind) will increase 

the take-off distance.

CAUTION

 The Ground Run is approx. 60% of Take-Off 

Distance.

 Increase Ground Run by 25% when operating 

from a grass surface.

These values are typical ones. On wet ground or 

wet soft grass covered runways, the Ground Run 

may become significantly longer than stated

above.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-14 DATE: 23 April 2015

Figure 5-5

TAKE-OFF DISTANCE 
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-15

5.11 TWIN ENGINE CLIMB - MCP CLIMB

(Figure 5-6)

Associated Conditions:

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft; at higher 

altitude LEAN for smooth operations.

Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate-of-Climb Speed 88 KIAS
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-16 DATE: 23 April 2015

Figure 5-6

TWIN ENGINE CLIMB - MCP CLIMB
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-17

5.12 ONE ENGINE INOPERATIVE CLIMB

(Figure 5-7)

Associated Conditions:

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft; at higher 

altitude LEAN for smooth operations.

Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate-of-Climb Speed 88 KIAS
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-18 DATE: 23 April 2015

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

11000

-100 0 100 200 300 400 500

ALTITUDE [ft]

ISA

ISA+10°C

ISA+20°C

ISA+30°C

3500

3700

3900

4100

4300

4500

4700

-100 0 100 200 300 400 500

RATE OF CLIMB [fpm]

WEIGHT [lbs]

REFERENCE LINE

Figure 5-7

ONE ENGINE INOPERATIVE CLIMB
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-19

5.13 BALKED LANDING CLIMB

(Figure 5-8)

Associated Conditions:

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft; at higher 

altitude LEAN for smooth operations.

Do not exceed 435°F (224°C) CHT

Flaps 35°

Landing Gear DOWN

Balked Landing Transition Speed 80 KIAS
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-20 DATE: 23 April 2015

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

ALTITUDE [ft]

ISA

ISA+10°C

ISA+20°C

ISA+30°C

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

RATE OF CLIMB [fpm]

WEIGHT [lbs]

REFERENCE LINE

0

2,000

4,000

8,000

10,000

4,500

4,300

3,900

3,700

3,500

Figure 5-8

BALKED LANDING CLIMB
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-21

5.14 TIME, FUEL AND DISTANCE TO CLIMB - MCP

CLIMB

(Figure 5-9)

Associated Conditions:

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft; at higher 

altitude LEAN for smooth operations.

Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate-of-Climb Speed 88 KIAS

NOTE

To obtain the total fuel used, add 20 lbs for start, 

taxi and take-off.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-22 DATE: 23 April 2015

Figure 5-9

TIME, FUEL AND DISTANCE TO CLIMB - MCP CLIMB
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-23

5.15 CRUISE PERFORMANCE - BEST ECONOMY 

MIXTURE 

 SEA LEVEL

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the 

fuel flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A. -20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH

SEA LEVEL

2450 25 77.7 160 21.1 75.0 161 20.5 72.5 162 20.0

2450 23 69.8 153 19.5 67.3 154 18.8 65.1 155 18.5

2450 21 61.2 146 17.5 59.0 146 17.1 57.1 147 16.6

2450 19 53.3 138 15.8 51.4 138 15.5 49.7 139 15.1

2400 25 76.2 158 20.6 73.5 160 20.0 71.7 161 19.5

2400 23 67.9 152 18.8 65.5 153 18.3 63.3 154 17.8

2400 21 60.4 145 17.1 58.3 146 16.8 56.4 146 16.3

2400 19 52.1 136 15.5 50.3 137 15.0 48.6 137 14.6

2350 25 74.1 157 20.0 71.5 158 19.5 69.1 159 19.0

2350 23 66.3 150 18.3 64.0 151 17.8 61.9 152 17.3

2350 21 58.6 143 16.6 56.5 144 16.1 54.6 144 15.8

2350 19 50.8 135 15.0 49 135 14.6 47.4 136 14.3

2300 25 72.6 155 19.5 70.0 156 19.0 67.7 157 111

2300 23 64.8 149 17.8 62.5 150 17.3 60.4 150 16.8

2300 21 57.0 141 16.1 55.0 142 15.6 53.2 143 15.3

2300 19 49.8 135 14.6 48.0 135 14.1 46.4 136 13.8

Figure 5-10

Sheet 1 of 5
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-24 DATE: 23 April 2015

 3000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the 

fuel flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A. -20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH

3000 feet

2450 25 81.3 166 22.0 78.4 167 21.3 75.8 168 20.6

2450 23 73.0 159 20.1 70.4 160 19.5 68.0 161 19.0

2450 21 64.5 152 18.3 62.2 152 17.8 60.1 153 17.3

2450 19 56.2 144 16.5 54.2 144 16.0 52.4 144 15.6

2400 24 75.2 161 20.5 72.5 162 19.8 70.1 163 19.3

2400 22 67.2 154 18.6 64.8 155 18.1 62.6 155 17.6

2400 20 58.6 146 16.8 56.5 146 16.3 54.6 147 16.0

2400 18 50.8 136 15.1 49.0 137 14.8 47.4 137 14.5

2350 24 73.1 159 19.8 70.5 160 19.3 68.1 161 18.6

2350 22 65.4 152 18.1 63.0 153 17.6 60.9 154 17.1

2350 20 57.3 145 16.3 55.2 145 16.0 53.4 145 15.5

2350 18 49.5 135 14.6 47.8 135 14.3 46.1 135 14.0

2300 24 71.6 158 19.3 69.0 159 18.8 66.7 159 18.3

2300 22 63.8 151 17.6 61.5 151 17.1 59.4 152 16.6

2300 20 56.0 143 16.0 54.0 143 15.5 52.2 144 15.1

2300 18 48.1 133 14.1 46.4 133 13.8 44.8 133 13.5

Figure 5-10

Sheet 2 of 5
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-25

 6000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the 

fuel flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A. -20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH

6000 feet

2450 24 79.9 170 21.6 77.0 170 21.0 74.4 171 20.5

2450 22 72.2 163 20.0 69.5 164 19.3 67.1 164 18.8

2450 20 63.3 155 18.0 61.0 155 17.5 58.9 155 17.0

2450 18 54.5 144 16.1 52.5 144 15.6 50.7 144 15.3

2400 24 78.4 168 21.1 75.5 169 20.5 72.9 169 20.0

2400 22 70.1 161 19.3 67.5 162 18.8 65.2 162 18.3

2400 20 61.3 154 17.5 59.0 154 17.0 57.0 154 16.5

2400 18 53.4 143 15.6 51.4 143 15.3 49.6 143 14.8

2350 24 75.8 166 20.3 73.0 166 19.8 70.5 167 19.3

2350 22 68.0 159 18.6 65.5 159 18.1 63.3 160 17.6

2350 20 59.7 151 17.0 57.5 151 16.5 55.5 151 16.0

2350 18 52.2 142 15.3 50.3 141 14.8 48.6 141 14.5

2300 24 74.1 165 19.8 71.4 165 19.3 68.9 165 18.6

2300 22 66.4 158 18.1 64.0 158 17.6 61.8 158 17.1

2300 20 58.5 149 16.5 56.3 149 16.0 54.4 149 15.6

2300 18 50.5 139 14.8 48.6 139 14.3 46.9 139 14.0

Figure 5-10

Sheet 3 of 5
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-26 DATE: 23 April 2015

 9000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the 

fuel flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A. -20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH

9000 feet

2450 21 70.2 171 19.5 67.6 172 19.0 65.2 171 18.5

2450 20 66.0 162 18.6 63.5 162 18.0 61.3 162 17.6

2450 19 61.5 157 17.6 59.2 157 17.1 57.1 157 16.6

2450 18 57.2 153 16.6 55.0 152 16.1 53.1 152 15.8

2400 21 68.4 164 19.0 65.8 165 18.3 63.5 164 17.8

2400 20 63.9 159 18.0 61.5 160 17.5 59.3 159 17.0

2400 19 59.8 155 17.1 57.5 155 16.6 55.5 155 16.1

2400 18 55.6 151 16.1 53.5 150 15.6 51.6 150 15.3

2350 21 66.5 162 18.3 64.0 162 17.8 61.8 162 17.3

2350 20 62.2 158 17.5 59.9 158 17.0 57.8 157 16.5

2350 19 58.1 153 16.5 55.9 153 16.1 53.9 152 15.6

2350 18 54.5 148 15.8 52.4 148 15.3 50.6 148 15.0

2300 21 64.9 161 17.8 62.5 160 17.3 60.3 160 16.8

2300 20 60.6 156 17.0 58.3 156 16.5 56.3 155 16.0

2300 19 56.6 152 16.0 54.5 151 15.6 52.6 151 15.1

2300 18 52.6 146 15.1 50.6 145 14.8 48.8 145 14.3

Figure 5-10

Sheet 4 of 5
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-27

 12000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the fuel 

flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A. -20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH

12000 feet

2450 19 64.0 165 18.1 61.5 165 17.6 59.3 163 17.1

2450 18 59.6 160 17.1 57.3 160 16.6 55.2 160 16.3

2450 17 55.1 153 16.3 53.0 153 15.8 51.1 155 15.3

2400 19 62.4 163 17.6 60.0 163 17.1 57.9 163 16.6

2400 18 58.0 158 16.6 55.8 158 16.1 53.8 158 15.8

2400 17 53.8 157 15.8 51.7 152 15.3 49.8 152 15.0

2400 16 49.4 146 14.8 47.5 146 14.3 45.8 146 14.0

2350 19 60.3 160 17.0 58.0 160 16.5 55.9 161 16.1

2350 18 56.4 156 16.1 54.2 156 15.6 52.3 156 15.3

2350 17 52.4 150 15.3 50.4 150 14.8 48.6 150 14.5

2350 16 48.3 144 14.3 64.4 144 14.0 44.7 144 13.6

2300 19 58.8 158 16.5 56.5 158 16.0 54.5 159 15.6

2300 18 54.6 152 15.6 52.5 152 15.1 50.6 153 14.8

2300 17 50.5 148 14.8 48.6 147 14.3 46.9 147 14.0

2300 16 46.5 141 13.8 44.8 141 13.5 43.2 141 13.1

Figure 5-10

Sheet 5 of 5
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-28 DATE: 23 April 2015

5.16 OPERATING ENVELOPE

(Figure 5-11)

Associated Conditions:

Aircraft Weight 4548 lbs

Outside Air Temperature ISA

Wind ZERO

Flaps UP

Landing Gear UP

0

4000

8000

12000

16000

20000

24000

50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200

TRUE AIR SPEED [kts]

ALTITUDE [ft]

2700 rpm

FULL THROTTLE

75% @ 2450 rpm

65% @ 2450 rpm

55% @ 2350 rpm

STALL SPEED

Figure 5-11

CRUISE SPEED vs. ALTITUDE
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-29

5.17 RANGE PROFILE

(Figure 5-12)

Associated Conditions:

STD RANGE CONFIGURATION

Aircraft Weight 4548 lbs

Total Fuel 520 lt

Climb to desired altitude

Mixture BEST ECONOMY

Ambient ISA, zero wind

Rate of descent 750 fpm

LONG RANGE CONFIGURATION

Aircraft Weight 4548 lbs

Total Fuel 670 lt

Climb to desired altitude

Mixture BEST ECONOMY

Ambient ISA, zero wind

Rate of descent 750 fpm

NOTE

Range computation includes 20 lbs of fuel for 

start, taxi and take-off, plus the fuel required

climb, cruise and descent, plus 45min reserve 

fuel at 45% power.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-30 DATE: 23 April 2015

Figure 5-12

RANGE PROFILE
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-31

5.18 TIME, FUEL AND DISTANCE TO DESCENT

(Figure 5-13)

Associated Conditions:

Power As required

Mixture BEST ECONOMY

Flaps UP

Landing Gear UP

Airspeed 158 KIAS

NOTE

Distances shown are for zero wind. These

information may be used for all descent weights.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-32 DATE: 23 April 2015

Figure 5-13

TIME, FUEL AND DISTANCE TO DESCENT
A.F.M. P/N NOR10.707-30C

Section 5

P.68R PERFORMANCE

Rev. 27

DATE: 23 April 2015 5-33

5.19 LANDING DISTANCE TO CLEAR 50 FT 

OBSTACLE

(Figure 5-14)

Associated Conditions:

Throttle IDLE at 50 ft above ground level

Flaps 35°

Maximum effective braking

Level, Hard Surface, Dry Runway

Speed at 50 ft obstacle 1.3 Vs0

CAUTION

Increase Ground Run by 12% when operating 

from a grass surface.
A.F.M. P/N NOR10.707-30C

Section 5

PERFORMANCE P.68R

Rev. 27

5-34 DATE: 23 April 2015

Figure 5-14

LANDING DISTANCE