A.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 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 sup plements the basic Flight Manual. For

limitations, procedures and performance s not contained in this supplement

consult the basic Flight Manual. Whenever conflict arises between

information enclosed herein and the approved basic Flight Manual, the

informat ion 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

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 2 of 42 DATE: 23 April 2015 

### NOTES, CAUTIONS AND WARNINGS

In this Su pplement 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

m aintenance 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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 3 of 42 

### SECTION 2

– OPERATING L IMITATIONS

When the aircraft operates with MTOW of 1960 k g (4321 lb) 

### :

2.1 AIRSPEED LIMITATIONS

SPEED KCAS KIAS

Design Maneuvering Speed (VA)

Do not make full or abrupt con trol movements

above this speed 125 129

Max imum 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

A ir 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 en gine suddenly becomes inoperative and the

other engine is operating at take

- off power 60 62

Never Exceed Speed (VNE)

Do not exceed thi s speed under any circumstances 193 200

Maximum Structural Cruising Speed (VNO)

Do not exceed this speed except in calm air and

the n with caution 153 158

Maximum Gear Extension Speed: V LO (Extension)

Do not exten d landing gear above this speed 131 135

Maximum Gear Retraction Speed: V LO (Retraction)

Do not retrac t landing gear above this speed 100 105

Maximum Gear Extend ed Speed: V LE

Do not exceed this s peed with landing gear

extended 131 135A.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 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 maxim um 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 fl aps 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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 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 belo w.

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 Fig ure F 2

- 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 160 0 kg (3 527 lb) or less.

Linear variation bet ween 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

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 6 of 42 DATE: 23 April 2015 Figure F 2

- 1

AIRCRAFT WEIGHTS VS. CENT E R OF GRAVITY



### 2.5 FLIGHT MANOEUVRE L OAD 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 gA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 7 of 42 

### 2.6 LIMITATION PLACARDS

In Full Vie w of Pilot:A.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMEN T F P

. 68R

Rev. 27

P age 8 of 42 DATE: 23 April 2015 

### S ECTION 3

– EMERGENCY PROCEDURES

There is no change to air craft emergency procedures when the aircraft

operates with a maximum take

- off weight of 1960 kg (4321 lb).A.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 9 of 42 

### SECTION 4

– NORMAL PROCEDURES

4.1 AIRSPEED FOR SAFE OPERA TION

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: V LO (Extension) 135 KIAS

(h1) Maximum Gear Retraction Speed: V LO (Retraction) 105 KIAS

(i) Maximum Gear Extended Speed: V LE 135 KIAS

(j) Maximum Demonstrated Crosswind Velocity 25 KTSA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 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 1 3 5 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 Fl aps) 7 8 KIAS min.

(L) Air Minimum Control Speed 62 KIASA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 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

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 12 of 42 DATE: 23 April 2015 

### SECTION 5

– PERFORMANCE

5.1 FLIGHT PLANNING EXAM PLE

This paragraph provides information t o 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 quantit y 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 2 1 °C (ISA + 10° C )

Pressure altitude 2 000 ft

Win d direction and speed 180 ° at 8 Kts

Runway direction 330°

CRUISE

Outside Air Temperature ISA

Pressure altitude 6 000 ft

En

- Route Distance 400 nM

ARRIVAL AIRPORT

Outside Air Temperature 2 1 °C (ISA + 10° C )

Pressure altitude 2 000 ft

Wind directi on and speed 330 ° at 12 Kts

Runway direction 3 0 0°

Procedure:

Take

- Off Distance

The measured take

- off distance s are reported as a function of ambient

temperature, including variations for weight change and wind influence.

1. Calculate the angle between wi nd direction and runway direction

180°

- 330°=

- 50 °

2. Calculate the wi nd component parallel to runway (from Figure 5

- 3)A.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 13 of 42 5 Kts

- tail wind

3. Enter Figure F5

- 5 at 21° OAT

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

5. Proceed vertically downwa rds 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

- tail wind 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 F 5

- 6 at 21° OAT

2. Proceed vertically upwards until intersecting the 2000 ft rate

- of

- climb

graph

3. Proceed h orizontally 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 1 170

ft/min

Rate of climb

– OEI climb

1. Enter Figu re F 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. Proc eed vertically downwards to obtain the OEI rate of climb of 2 5 0

ft/min

Rate of climb

– Balked landing climb

1. Enter Figure F 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 refer ence 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/minA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 14 of 42 DATE: 23 April 2015 Time, Fuel and Distance to Climb

– MCP climb

Time, fuel and distance t o 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 F 5

- 9 at the giv en 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 t his 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 la nding 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

- 1 3 at the given altitude (cruise or airport)

2. Proceed vertically up to the t ime

- to

- descent line relating to selected R/S

and read the required time to descentA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 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 relati ng 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

- 1 2.1 = 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 = 3 69 .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 F 5

- 1 0 ), at a cruise altitude of

6 000 ft (ISA) and a power rating of 6 5

. 5 % (2350 RPM and 2 2 " Hg), the

cruise airspeed is 1 60 KTAS at MTOW

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

. Cruise time and fuel may be calculated by the following formula s :

Cruise Time = Cruise Distance / Cruise Speed

= 3 69 .6 / 16 0 = 2.3 1 hours or 13 8

. 6 min

Cruise Fuel = Fuel Flow x Cruise Time

= 18.1 x 2.3 1 = 41. 8 US Gal ( 251

. 2 lbs)A.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 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 descen t:

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

= 4.0 + 138. 6 + 8.5 = 15 1

. 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 descen t:

Total Required Fuel = Fuel for St art, Taxi and Take

- Off + Fuel to Climb +

Cruise Fuel + Fuel to Descent

= 20.0 + 12.0 + 25 1 .2 + 8.0 = 2 91

. 2 lbs (4 8

. 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

– 2 91

. 2 = 296

. 1 lbs (49. 3 US Gal)

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

time at 45% power (2200 RPM)

.

Landing Distance

The measured landing distance s (over 50 ft obstacle) are r eported 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

- 2 91

. 2 = 39 08

. 8 lbs

2. Calculate the angle between wind direction and runway direction

330°

- 300°= 30 °

3. Calculate the wi nd component parallel to runway (from Figure 5

- 3)

10 Kts

- headwind

4. Enter Figure 5

- 1 4 at 21° OAT

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

6. Proceed vertica lly downwards to the reference line

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

the horizontal 39 09 lbs lineA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 17 of 42 8. Proceed vertically downwards to the reference line

9. Follow the slope of the adiacent take

- off lines until intersectin g 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

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 18 of 42 DATE: 23 April 2015 

### 5.2 TAKE

- OFF DISTANCE

(Figure F 5

- 5)

Associated Conditions :

Power 2700 RPM, full throttle, before brake release

Flaps 1 5°

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 increas e

the take

- off distance.

CAUTION

 The Ground Run is approx. 60% of T ake

- O ff

Distance.

 Increase Ground Run by 2 5% when operating

from a grass surface

. These values are typical ones . On wet ground or

wet soft grass covered runways, the Ground Run

may beco me s ignificantly longer than stated

above

.A.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 19 of 42 Figure F 5

- 5

TAKE

- OFF DISTANCEA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 20 of 42 DATE: 23 April 2015 

### 5.3 TW IN ENGINE CLIMB

- MCP CLIMB

(Figure F 5

- 6 )

Associated Conditions :

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft ; at higher

altitu de LEAN for smooth operations

. Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate

- of

- Climb Speed 88 KIASA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 21 of 42 Figure F 5

- 6

TWIN ENGINE CLIMB

- M CP CLIMBA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 22 of 42 DATE: 23 April 2015 

### 5.4 ONE ENGINE INOPERATIVE CLIMB

(Figu re F 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 KIASA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 23 of 42 Figure F 5

- 7

ONE ENGINE INOPERATIVE CLIMBA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 24 of 42 DATE: 23 April 2015 

### 5. 5 BALKED LANDING CLIMB

(Figure F 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 KIASA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 25 of 42 Figure F 5

- 8

BALKED LANDING CLIMBA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 26 of 42 DATE: 23 April 2015 

### 5. 6 TIME

, FUEL AND DISTANCE TO CLIMB

- M CP

CLIMB

(Figure F 5

- 9 )

Associated Conditions :

Power 2700 RPM, full throttle

Mixtur e 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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 27 of 42 Figure F 5

- 9

TIME

, FUEL AND DISTANCE TO CLIMB

- M CP CLIM BA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 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 m ultiply 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 GPHSEA 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 5 3

. 3 138 15.8 51.4 138 15.5 49.7 139 15.1

2 40

0 25 76.2 158 20.6 73.5 160 20.0 71.7 161 19.5

240 0 23 6 7

. 9 152 18.8 65.5 153 18.3 63.3 154 17.8

240 0 21 6 0

. 4 145 17.1 58.3 146 16.8 56.4 146 16.3

240 0 19 5 2

. 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

2 3 00 25 72.6 155 19.5 70.0 156 19.0 67.7 157 18.5

2 3 00 23 64.8 149 17.8 62.5 150 17.3 60.4 150 16.8

2 3 00 21 57.0 141 16.1 55.0 142 15.6 53.2 143 15.3

2 3 00 19 49.8 135 14.6 48.0 135 14.1 46.4 136 13.8

Figure F 5

- 1 0

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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 29 of 42 

###  3 000 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. +2 0 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH3000 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

2 40

0 2 4 75.2 162 20.5 72.5 163 19.8 70.1 164 19.3

2 40

0 2 2 67.2 155 18.6 64.8 156 18.1 62.6 156 17.6

2 40

0 2 0 58.6 147 16.8 56.5 147 16.3 54.6 148 16.0

2 40

0 1 8 50.8 138 15.1 49.0 139 14.8 47.4 139 14.5

2350 2 4 73.1 160 19.8 70.5 161 19.3 68.1 162 18.6

2350 2 2 65.4 153 18.1 63.0 154 17.6 60.9 155 17.1

2350 2 0 57.3 146 16.3 55.2 146 16.0 53.4 146 15.5

2350 1 8 49.5 137 14.6 47.8 137 14.3 46.1 137 14.0

2 3 00 2 4 71.6 159 19.3 69.0 160 18.8 66.7 160 18.3

2 3 00 2 2 63.8 152 17.6 61.5 152 17.1 59.4 153 16.6

2 3 00 2 0 56.0 144 16.0 54.0 144 15.5 52.2 145 15.1

2 3 00 1 8 48.1 135 14.1 46.4 135 13.8 44.8 135 13.5

Figure F 5

- 1 0

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

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 30 of 42 DATE: 23 April 2015 

###  6 000 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 GPH6000 feet 2450 2 4 79.9 171 21 .6 77.0 171 21.0 74.4 172 20.5

2450 2 2 72.2 164 20.0 69.5 165 19.3 67.1 165 18.8

2450 2 0 63.3 156 18.0 61.0 156 17.5 58.9 156 17.0

2450 1 8 54.5 146 16.1 52.5 146 15.6 50.7 146 15.3

2 40

0 2 4 78.4 169 21.1 75.5 170 20.5 72.9 170 20.0

2 4 0 0 2 2 70.1 162 19.3 67.5 163 18.8 65.2 163 18.3

2 40

0 2 0 61.3 159 17.5 59.0 159 17.0 57.0 159 16.5

2 40

0 1 8 53.4 145 15.6 51.4 145 15.3 49.6 145 14.8

2350 2 4 75.8 167 20.3 73.0 167 19.8 70.5 168 19.3

2350 2 2 68.0 160 18.6 65.5 160 18.1 6 3.3 161 17.6

2350 2 0 59.7 152 17.0 57.5 152 16.5 55.5 152 16.0

2350 1 8 52.2 144 15.3 50.3 143 14.8 48.6 143 14.5

2 3 00 2 4 74.1 166 19.8 71.4 166 19.3 68.9 166 18.6

2 3 00 2 2 66.4 159 18.1 64.0 159 17.6 61.8 159 17.1

2 3 00 2 0 58.5 151 16. 5 56.3 151 16.0 54.4 151 15.6

2 3 00 1 8 50.5 141 14.8 48.6 141 14.3 46.9 141 14.0

Figure F 5

- 1 0

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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 31 of 42 

###  9 000 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 GP H by 6.01

Figure F 5

- 1 0

S heet 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 GPH9000 feet 2450 2 1 70.2 172 19.5 67.6 173 19.0 65.2 172 18.5

2450 2 0 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

2 40

0 2 1 68.4 165 19.0 65.8 166 18.3 63.5 165 17.8

2 40

0 2 0 63.9 166 18.0 61.5 167 17.5 59.3 166 17.0

2 40

0 19 59.8 156 17.1 57.5 156 16.6 55.5 15 6 16.1

2 40

0 18 55.6 152 16.1 53.5 151 15.6 51.6 151 15.3

2350 2 1 66.5 163 18.3 64.0 163 17.8 61.8 163 17.3

2350 2 0 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

2 3 00 2 1 64.9 162 17.8 62.5 161 17.3 60.3 161 16.8

2 3 00 2 0 60.6 157 17.0 58.3 157 16.5 56.3 156 16.0

2 3 00 19 56.6 153 16.0 54.5 152 15.6 52.6 152 15.1

2 3 00 18 52.6 148 15.1 50.6 147 14.8 48.8 147 14.3A.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 32 of 42 DATE: 23 April 2015 

###  1 2000 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 GPH12000 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

2 40

0 19 62.4 164 17.6 60.0 164 17.1 57.9 164 16.6

2 40

0 18 58.0 159 16.6 55.8 159 16.1 53.8 159 15.8

2 40

0 17 53.8 158 15.8 51.7 154 15.3 49.8 154 15.0

2 40

0 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

2 3 00 19 58.8 159 16.5 56.5 159 16.0 54.5 160 15.6

2 3 00 18 54.6 154 15.6 52.5 154 15.1 50.6 155 14.8

2 3 00 17 50.5 150 14.8 48.6 149 14.3 46.9 149 14.0

2 3 00 16 46.5 143 13.8 44.8 143 13.5 43.2 143 13.1

Figure F 5

- 1 0

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

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 33 of 42 

### 5. 8 OPERATING ENVELOPE

(Figure F 5

- 1 1 )

Associated Conditions :

Aircraft Weight 4 321 lbs

Outside Air Temperature ISA

Wind ZERO

Flaps UP

Landing Gear UP

Figure F 5

- 1 1

CRUISE SPEED vs . ALTITUDEA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 34 of 42 DATE: 23 April 2015 

### 5. 9 RANGE PROFILE

(Figure F 5

- 1 2 )

Associated Conditions :

STD RANGE CONFIGURATION

Aircraft Weight 4 321 lbs

Total F uel 520 lt

Climb to desired altitude

Mixture BEST ECONOMY

Ambient ISA, zero wind

Rate of descent 750 fpm

LONG RANGE CONFIGURATION

Aircraft Weight 4 321 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 a t 45% power.A.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 35 of 42 Figure F 5

- 1 2

RA NGE PROFILEA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 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 F 6

- 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 o f 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 F 6

- 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 F 6

- 2

BASIC EMPTY WEIGHTA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 37 of 42 Aircraft Serial Number____________________

Registration Marks_______________________

AIRCRAFT ACTUAL BASIC EMPTY WEIGHT

ITEM Wei ght × C.G. Arm = Moment

(Aft of Datum)

Basic Empty Weight* (from Figure F 6

- 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

( 43 21 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 F 6

- 4) WHEN

ALTERATIONS HAVE BEEN MADE.

Figure F 6

- 3

WEIGHT AND BALANCE DATA FORMA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 38 of 42 DATE: 23 April 2015 Figure F 6

- 4

WEIGHT AND BALANCE RECORDA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 39 of 42 Figure F 6

- 5

Sheet 1 o f 2

WORK SHEETA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 40 of 42 DATE: 23 April 2015 Figure F 6

- 5

Sheet 2 of 2

WORK SHEETA.F.M. P/N NOR10.707

- 30 C

- Section 8

P

. 68R SUPPLEMENT F

Rev. 27

DATE: 23 April 2015 P age 41 of 42 Figure F 6

- 6

WEIGHT/MOMENT ENVELOP EA.F.M. P/N NOR10.707

- 30 C

- Section 8

SUPPLEMENT F P

. 68R

Rev. 27

P age 42 of 42 DATE: 23 April 2015 - INTENTIONALLY LEFT BLANK

-