A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 1 of 42

SUPPLEMENT F

MTOW DECREASE TO 1960 kg (4321 lb)

SECTION 1 – GENERAL

This Supplement must be attached to approved Aircraft Flight Manual when 

the aircraft operates with a maximum take-off weight of 1960 kg (4321lbs).

The information contained herein supplements the basic Flight Manual. For 

limitations, procedures and performances not contained in this supplement 

consult the basic Flight Manual. Whenever conflict arises between 

information enclosed herein and the approved basic Flight Manual, the 

information in this supplement must take precedence.

In any case, the latest applicable revision of the following reference 

publications must be regarded as completion of this Supplement and must be 

always carried on board.
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 2 of 42 DATE: 23 April 2015

NOTES, CAUTIONS AND WARNINGS

In this Supplement the Note, Caution and Warning indications are supplied in 

accordance with these definitions:

NOTE An operating procedure, technique or 

maintenance practice which is considered 

essential to emphasize.

CAUTION An operating procedure, technique or 

maintenance practice which may result in a 

minor damage if not carefully followed.

WARNING An operating procedure, technique or 

maintenance practice which may result in 

personal injury or loss of life if not 

carefully followed.
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 3 of 42

SECTION 2 – OPERATING LIMITATIONS

When the aircraft operates with MTOW of 1960 kg (4321 lb):

2.1 AIRSPEED LIMITATIONS

SPEED KCAS KIAS

Design Maneuvering Speed (VA)

Do not make full or abrupt control movements 

above this speed 125 129

Maximum Flaps Extended Speed (VFE)

Do not exceed this speed at the given flap setting

0° - 15° flap 152 157

15° - 30° flap 138 143

30° - 35° flap 99 101

Air Minimum Control Speed (VMCA)

This is the lowest speed at which the airplane is 

controllable with a bank of not more than 5° when 

one engine suddenly becomes inoperative and the 

other engine is operating at take-off power 60 62

Never Exceed Speed (VNE)

Do not exceed this speed under any circumstances 193 200

Maximum Structural Cruising Speed (VNO)

Do not exceed this speed except in calm air and 

then with caution 153 158

Maximum Gear Extension Speed: VLO (Extension)

Do not extend landing gear above this speed 131 135

Maximum Gear Retraction Speed: VLO (Retraction)

Do not retract landing gear above this speed 100 105

Maximum Gear Extended Speed: VLE

Do not exceed this speed with landing gear 

extended 131 135
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 4 of 42 DATE: 23 April 2015

2.2 AIRSPEED INDICATOR MARKINGS

MARKINGS KIAS

White range

(Full Flaps operating range, lower limit is 

maximum weight stalling speed in landing 

configuration. Upper limit is maximum speed 

permissible with flaps extended). 60 to 101

Lower Red Line

(Air Minimum Control Speed). 62

Blue Line

(One engine inoperative best rate of climb 

speed). 88

Green range

(Normal Operating Range. Lower limit is 

maximum weight stalling speed with flaps and 

landing gear retracted. Upper limit is 

maximum structural cruising speed). 65 to 158

Yellow range

(Caution Range. Operation must be conducted 

with caution and only in smooth air) 158 to 200

Upper Red Line

(Maximum Speed for all operations) 200

CROSSWIND

The maximum demonstrated crosswind velocity for take off and landing is 

25 kts.
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 5 of 42

2.3 WEIGHT LIMITS

It is the responsibility of the aircraft owner and/or pilot to ensure that the 

aircraft is properly loaded. Maximum allowable weights are listed below.

Refer to Section 6 "Weight and Balance" for loading instructions.

kg lb

(a) Maximum Takeoff Weight 1960 4321

(b) Maximum Landing Weight 1960 4321

(c) Maximum Weight in Baggage 

Compartment 181 400

2.4 CENTER OF GRAVITY LIMITS

(Refer to Figure F2-1)

(a) Rearward Limits:

 0.526 m (20.7 inches) aft of datum at all weights.

(b) Forward Limits:

 0.325 m (12.8 in) aft of datum at maximum take-off weight of 

1960 kg (4321 lb).

 0.259 m (10.2 in) aft of datum at 1600 kg (3527 lb) or less.

Linear variation between given points.

NOTE

The datum line is tangent to the wing leading 

edge.

NOTE

Changes in centre of gravity position due to 

landing gears extension/retraction are 

negligible.
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 6 of 42 DATE: 23 April 2015

Figure F2-1

AIRCRAFT WEIGHTS VS. CENTER OF GRAVITY

2.5 FLIGHT MANOEUVRE LOAD FACTOR LIMITS

(a) Positive Load Factor (Flaps Up ) +3.80 g

(b) Negative Load Factor (Flaps Up) - 1.52 g

(c) Positive Load Factor (Flaps Down – 35°) +2.00 g

(d) Negative Load Factor (Flaps Down – 35°) - 0.80 g
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 7 of 42

2.6 LIMITATION PLACARDS

In Full View of Pilot:
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 8 of 42 DATE: 23 April 2015

SECTION 3 – EMERGENCY PROCEDURES

There is no change to aircraft emergency procedures when the aircraft 

operates with a maximum take-off weight of 1960 kg (4321 lb).
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 9 of 42

SECTION 4 – NORMAL PROCEDURES

4.1 AIRSPEED FOR SAFE OPERATION

The following airspeeds are those which are significant for safe operation of 

the aircraft. The figures are for standard aircraft flown at maximum gross 

weight under normal conditions at sea level. For additional airspeed 

information see Section 2.

(a) Maximum Structural Cruising Speed 158 KIAS

(b) Design Manoeuvring Speed 129 KIAS

(c) Maximum Flap Extended Speed

0° to 15° 157 KIAS

15° to 30° 143 KIAS

30° to 35° 101 KIAS

(d) Best Rate of Climb Speed 88 KIAS

(e) Best Angle of Climb Speed 76 KIAS

(f) Final Approach Speed (min.) 78 KIAS

(g) Air Minimum Control Speed 62 KIAS

(h) Maximum Gear Extension Speed: VLO (Extension) 135 KIAS

(h1) Maximum Gear Retraction Speed: VLO (Retraction) 105 KIAS

(i) Maximum Gear Extended Speed: VLE 135 KIAS

(j) Maximum Demonstrated Crosswind Velocity 25 KTS
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 10 of 42 DATE: 23 April 2015

4.2 BEFORE LANDING

(a) Fuel Selector RH ENG.-RH TANK

LH ENG.-LH TANK

(b) Auxiliary Fuel Pumps ON

(c) Mixtures FULL RICH

(d) Propellers FULL FORWARD

(e) Flaps (below 157 KIAS) DOWN 15°

(f) Flaps (below 143 KIAS) DOWN 30°

(g) Landing Lights AS REQUIRED

(h) Landing Gear (below 135 KIAS) DOWN

(i) Landing Gear Position Indicator Lights

- Green Light CHECK ON

- Red Light CHECK OFF

(J) Flaps (below 101 KIAS) DOWN 35°

(K) Approach Speed (Full Flaps) 78 KIAS min.

(L) Air Minimum Control Speed 62 KIAS
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 11 of 42

4.3 NOISE LEVEL

The noise level, determined according to ICAO Annex 16, Volume I, Chapter 

10, for the P.68 R at maximum continuous power and at Maximum Take-Off 

Weight of 1960 kg (4321 lb), is 76.4 dB(A).

In conformity with the above regulations, the maximum noise permitted level 

for the P.68 R at the highest power setting and at Maximum Take-Off Weight 

in the normal operating range, is 88 dB(A).
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 12 of 42 DATE: 23 April 2015

SECTION 5 – PERFORMANCE

5.1 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)
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 13 of 42

5 Kts - tailwind

3. Enter Figure F5-5 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 F5-6 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 F5-7 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 F5-8 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 8

SUPPLEMENT F P.68R

Rev. 27

Page 14 of 42 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 F5-9 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 1.8 min

Cruise Time to Climb 5.8 min

Time to Climb 5.8 - 1.8 = 4.0 min

Airport Fuel to Climb 4.0 lbs

Cruise Fuel to Climb 16.0 lbs

Fuel to Climb 16.0 - 4.0 = 12.0 lbs (2.0 US Gal)

Airport Distance to Climb 2.0 nM

Cruise Distance to Climb 8.0 nM

Distance to Climb 8.0 - 2.0 = 6.0 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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 15 of 42

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 - 6.0 - 24.4 = 369.6 nM

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

and available fuel load.

From the Cruise Performance Table (figure F5-10), at a cruise altitude of 

6000 ft (ISA) and a power rating of 65.5% (2350 RPM and 22" Hg), the 

cruise airspeed is 160 KTAS at MTOW.

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

= 369.6 / 160 = 2.31 hours or 138.6 min

Cruise Fuel = Fuel Flow x Cruise Time

= 18.1 x 2.31 = 41.8 US Gal (251.2 lbs)
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 16 of 42 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

= 4.0 + 138.6 + 8.5 = 151.1 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 + 12.0 + 251.2 + 8.0 = 291.2 lbs (48.4 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 – 291.2 = 296.1 lbs (49.3 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 - 291.2 = 3908.8 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 3909 lbs line
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 17 of 42

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 8

SUPPLEMENT F P.68R

Rev. 27

Page 18 of 42 DATE: 23 April 2015

5.2 TAKE-OFF DISTANCE

(Figure F5-5)

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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 19 of 42

Figure F5-5

TAKE-OFF DISTANCE 
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 20 of 42 DATE: 23 April 2015

5.3 TWIN ENGINE CLIMB - MCP CLIMB

(Figure F5-6)

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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 21 of 42

Figure F5-6

TWIN ENGINE CLIMB - MCP CLIMB
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 22 of 42 DATE: 23 April 2015

5.4 ONE ENGINE INOPERATIVE CLIMB

(Figure F5-7)

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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 23 of 42

Figure F5-7

ONE ENGINE INOPERATIVE CLIMB
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 24 of 42 DATE: 23 April 2015

5.5 BALKED LANDING CLIMB

(Figure F5-8)

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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 25 of 42

Figure F5-8

BALKED LANDING CLIMB
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 26 of 42 DATE: 23 April 2015

5.6 TIME, FUEL AND DISTANCE TO CLIMB - MCP

CLIMB

(Figure F5-9)

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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 27 of 42

Figure F5-9

TIME, FUEL AND DISTANCE TO CLIMB - MCP CLIMB
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 28 of 42 DATE: 23 April 2015

5.7 CRUISE PERFORMANCE - BEST ECONOMY 

MIXTURE 

 SEA LEVEL

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4321 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 18.5

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 F5-10

Sheet 1 of 5
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 29 of 42

 3000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4321 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 81.3 167 22.0 78.4 168 21.3 75.8 169 20.6

2450 23 73.0 160 20.1 70.4 161 19.5 68.0 162 19.0

2450 21 64.5 153 18.3 62.2 153 17.8 60.1 154 17.3

2450 19 56.2 145 16.5 54.2 145 16.0 52.4 145 15.6

2400 24 75.2 162 20.5 72.5 163 19.8 70.1 164 19.3

2400 22 67.2 155 18.6 64.8 156 18.1 62.6 156 17.6

2400 20 58.6 147 16.8 56.5 147 16.3 54.6 148 16.0

2400 18 50.8 138 15.1 49.0 139 14.8 47.4 139 14.5

2350 24 73.1 160 19.8 70.5 161 19.3 68.1 162 18.6

2350 22 65.4 153 18.1 63.0 154 17.6 60.9 155 17.1

2350 20 57.3 146 16.3 55.2 146 16.0 53.4 146 15.5

2350 18 49.5 137 14.6 47.8 137 14.3 46.1 137 14.0

2300 24 71.6 159 19.3 69.0 160 18.8 66.7 160 18.3

2300 22 63.8 152 17.6 61.5 152 17.1 59.4 153 16.6

2300 20 56.0 144 16.0 54.0 144 15.5 52.2 145 15.1

2300 18 48.1 135 14.1 46.4 135 13.8 44.8 135 13.5

Figure F5-10

Sheet 2 of 5
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 30 of 42 DATE: 23 April 2015

 6000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4321 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 79.9 171 21.6 77.0 171 21.0 74.4 172 20.5

2450 22 72.2 164 20.0 69.5 165 19.3 67.1 165 18.8

2450 20 63.3 156 18.0 61.0 156 17.5 58.9 156 17.0

2450 18 54.5 146 16.1 52.5 146 15.6 50.7 146 15.3

2400 24 78.4 169 21.1 75.5 170 20.5 72.9 170 20.0

2400 22 70.1 162 19.3 67.5 163 18.8 65.2 163 18.3

2400 20 61.3 159 17.5 59.0 159 17.0 57.0 159 16.5

2400 18 53.4 145 15.6 51.4 145 15.3 49.6 145 14.8

2350 24 75.8 167 20.3 73.0 167 19.8 70.5 168 19.3

2350 22 68.0 160 18.6 65.5 160 18.1 63.3 161 17.6

2350 20 59.7 152 17.0 57.5 152 16.5 55.5 152 16.0

2350 18 52.2 144 15.3 50.3 143 14.8 48.6 143 14.5

2300 24 74.1 166 19.8 71.4 166 19.3 68.9 166 18.6

2300 22 66.4 159 18.1 64.0 159 17.6 61.8 159 17.1

2300 20 58.5 151 16.5 56.3 151 16.0 54.4 151 15.6

2300 18 50.5 141 14.8 48.6 141 14.3 46.9 141 14.0

Figure F5-10

Sheet 3 of 5
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 31 of 42

 9000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4321 lbs

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

flow in GPH by 6.01

Figure F5-10

Sheet 4 of 5

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 70.2 172 19.5 67.6 173 19.0 65.2 172 18.5

2450 20 66.0 163 18.6 63.5 163 18.0 61.3 163 17.6

2450 19 61.5 158 17.6 59.2 158 17.1 57.1 158 16.6

2450 18 57.2 154 16.6 55.0 153 16.1 53.1 153 15.8

2400 21 68.4 165 19.0 65.8 166 18.3 63.5 165 17.8

2400 20 63.9 166 18.0 61.5 167 17.5 59.3 166 17.0

2400 19 59.8 156 17.1 57.5 156 16.6 55.5 156 16.1

2400 18 55.6 152 16.1 53.5 151 15.6 51.6 151 15.3

2350 21 66.5 163 18.3 64.0 163 17.8 61.8 163 17.3

2350 20 62.2 159 17.5 59.9 159 17.0 57.8 158 16.5

2350 19 58.1 154 16.5 55.9 154 16.1 53.9 153 15.6

2350 18 54.5 150 15.8 52.4 150 15.3 50.6 150 15.0

2300 21 64.9 162 17.8 62.5 161 17.3 60.3 161 16.8

2300 20 60.6 157 17.0 58.3 157 16.5 56.3 156 16.0

2300 19 56.6 153 16.0 54.5 152 15.6 52.6 152 15.1

2300 18 52.6 148 15.1 50.6 147 14.8 48.8 147 14.3
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 32 of 42 DATE: 23 April 2015

 12000 ft 

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4321 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 64.0 166 18.1 61.5 166 17.6 59.3 164 17.1

2450 18 59.6 161 17.1 57.3 161 16.6 55.2 161 16.3

2450 17 55.1 155 16.3 53.0 155 15.8 51.1 156 15.3

2400 19 62.4 164 17.6 60.0 164 17.1 57.9 164 16.6

2400 18 58.0 159 16.6 55.8 159 16.1 53.8 159 15.8

2400 17 53.8 158 15.8 51.7 154 15.3 49.8 154 15.0

2400 16 49.4 148 14.8 47.5 148 14.3 45.8 148 14.0

2350 19 60.3 161 17.0 58.0 161 16.5 55.9 162 16.1

2350 18 56.4 157 16.1 54.2 157 15.6 52.3 157 15.3

2350 17 52.4 152 15.3 50.4 152 14.8 48.6 152 14.5

2350 16 48.3 146 14.3 64.4 146 14.0 44.7 146 13.6

2300 19 58.8 159 16.5 56.5 159 16.0 54.5 160 15.6

2300 18 54.6 154 15.6 52.5 154 15.1 50.6 155 14.8

2300 17 50.5 150 14.8 48.6 149 14.3 46.9 149 14.0

2300 16 46.5 143 13.8 44.8 143 13.5 43.2 143 13.1

Figure F5-10

Sheet 5 of 5
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 33 of 42

5.8 OPERATING ENVELOPE

(Figure F5-11)

Associated Conditions:

Aircraft Weight 4321 lbs

Outside Air Temperature ISA

Wind ZERO

Flaps UP

Landing Gear UP

Figure F5-11

CRUISE SPEED vs. ALTITUDE
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 34 of 42 DATE: 23 April 2015

5.9 RANGE PROFILE

(Figure F5-12)

Associated Conditions:

STD RANGE CONFIGURATION

Aircraft Weight 4321 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 4321 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 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 35 of 42

Figure F5-12

RANGE PROFILE
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 36 of 42 DATE: 23 April 2015

SECTION 6 – WEIGHT AND BALANCE

6.4 WEIGHT AND BALANCE DETERMINATION 

FOR FLIGHT

NOTE

It is the responsibility of the pilot and/or aircraft 

owner to ensure that the aircraft is properly 

loaded.

WARNING

When no passengers or baggage are loaded

behind crew seats, fill the fuel tanks 

sufficiently to meet approved C.G. limits.

(a) Use the Loading Form (Figure F6-5) and add the weight of all items to 

be loaded to the Basic Empty Weight. Observe Maximum Take Off

Weight Limitation.

(b) Determine the moment of all items to be carried in the aircraft.

(c) Add the moment of all items to be loaded to the Basic Empty Weight 

moment.

(d) By using the figures of item (a) and item (c) (above), locate a point on 

the Centre of Gravity Moment Envelope (Figure F6-6). If the point

falls within the Envelope, the loading meets weight and balance 

requirements.

ITEM WEIGHT × ARM = MOMENT

kg m kgm

a. Weight (as weighed) - - -

b. Unusable Fuel for 

 STD Range Configuration only 13 0.770 10.01

c. Unusable Fuel for 

 Long Range configuration only 19 0.770 14.63

Basic Empty Weight (a+b) or (a+c) - - -

Figure F6-2

BASIC EMPTY WEIGHT
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 37 of 42

Aircraft Serial Number____________________

Registration Marks_______________________

AIRCRAFT ACTUAL BASIC EMPTY WEIGHT

ITEM Weight × C.G. Arm = Moment

(Aft of Datum)

Basic Empty Weight* (from Figure F6-2)

Optional Equipment

(if not on board when factory weighed)

Actual Basic Empty Weight

* Aircraft Basic Empty Weight includes full (7.5 liters) engine oil, full brake 

fluid, 18 liters of unusable fuel for STD Range Configuration plus a further 8 

liters of unusable fuel for the Long Range Configuration.

AIRCRAFT USEFUL LOAD

NORMAL CATEGORY OPERATION

(Max Take Off Weight) - (Actual Basic Empty Weight) = Useful load

(4321 lbs) - (........................ lbs) = ............................. lbs

(1960 kg) - (......................... kg) = .............................. kg

THIS ACTUAL BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD 

ARE FOR THE AIRCRAFT AS DELIVERED FROM THE FACTORY.

REFER TO WEIGHT AND BALANCE RECORD (Figure F6-4) WHEN 

ALTERATIONS HAVE BEEN MADE.

Figure F6-3

WEIGHT AND BALANCE DATA FORM
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 38 of 42 DATE: 23 April 2015

Figure F6-4

WEIGHT AND BALANCE RECORD
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 39 of 42

Figure F6-5

Sheet 1 of 2

WORK SHEET
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 40 of 42 DATE: 23 April 2015

Figure F6-5

Sheet 2 of 2

WORK SHEET
A.F.M. P/N NOR10.707-30C - Section 8

P.68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 Page 41 of 42

Figure F6-6

WEIGHT/MOMENT ENVELOPE
A.F.M. P/N NOR10.707-30C - Section 8

SUPPLEMENT F P.68R

Rev. 27

Page 42 of 42 DATE: 23 April 2015

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