G-CCWM Weight & Performance - McAully Flying Group

Aircraft

Display units

Load inputs

Enter passenger and baggage weights. Fuel is entered in litres. Your entries are saved automatically in this browser.

Weight converter (stones ⇄ kg)

Enter either field to convert a passenger’s weight — the other updates automatically. Use the kg figure in the fields below.

Weight (stones)

Weight (kg)

Pilot / P1

Front passenger / P2

Rear passenger / PX1

Rear passenger / PX2

Baggage

Fuel

W&B Calculation

Moment = weight × arm. CG = total moment ÷ total weight.

Total weight

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Centre of gravity

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Take-off limit

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Landing limit

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Item	Volume	Weight	Arm	Moment

Limit checks

Fuel required for the flight

Enter minutes — time (hr) and litres follow automatically. Litres = time (hr) × burn rate.

Item	Minutes	Time (hr)	Litres
START/TAXI (5 g/hr · 22 l/hr)		—	—
CLIMB (8 g/hr · 36 l/hr)		—	—
EN ROUTE (8 g/hr · 36 l/hr)		—	—
CIRCUIT (6 g/hr · 27 l/hr)		—	—
ROUTE TOTAL	—	—	—
ALTERNATE AIRFIELD (8 g/hr · 36 l/hr)		—	—
45 MINS. HOLD (8 g/hr · 36 l/hr)		—	—
TOTAL FUEL REQUIRED	—	—	—
FUEL (max 50 USG / 41 IMP G / 190 L)	—	—	—
LESS FUEL REQUIRED	—	—	—
RESERVE	—	—	—

FUEL is taken automatically from the Fuel port wing tank, Fuel starboard wing tank and Fuel main tank entries above. RESERVE time is the reserve litres converted at the cruise burn rate (36 l/hr).

Take-off performance

At gross weight 1100 kg (2425 lb). Without wind, flaps in “take off position” (1st notch), engine full power.

Take-off speed: (54 kt) 100 km/h · Over 15 m (50 ft) barrier speed: (70 kt) 130 km/h

Pressure altitude (ft)	Temperature °C (°F)	Weight 1100 kg (2425 lb)				Weight 900 kg (1984 lb)
		Take-off distance		Run to clear 15m (50ft) barrier		Take-off distance		Run to clear 15m (50ft) barrier
		m	(ft)	m	(ft)	m	(ft)	m	(ft)

Head wind influence: for 10 kt multiply by 0.85 · for 20 kt multiply by 0.65 · for 30 kt multiply by 0.55
Down wind influence: add 10% to distance per section of 2 kt
Dried grass runway: add 15%

Current total weight (from Calculation)

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Adjusted take-off distance calculator

Take-off distance is pre-filled from the table’s Std-temperature row, interpolated between the 1100 kg and 900 kg columns at the current total weight above. It stays fully editable — type over it, or change the pressure altitude to re-suggest.

Pressure altitude (for suggestion)

Head wind

Runway surface

Take-off distance (m)

Suggested (Std temperature, interpolated by weight): —

Adjusted take-off distance

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Adjusted take-off distance (ft)

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Adjusted distance = take-off distance × head wind factor × runway surface factor. This reproduces the correction factors on the supplied performance sheet; it is a planning aid only — confirm against the current approved POH/AFM figures before flight.

Landing performance

At gross weight 1045 kg (2304 lb). Without wind, flaps in “landing” position, engine idling, dried and plane concrete runway.

Over 15 m (50 ft) barrier speed: (68 kt) 125 km/h · Touch down speed: (51 kt) 95 km/h

Pressure altitude Zp (ft)	Temperature °C (°F)	Weight 1045 kg (2304 lb)				Weight 845 kg (1863 lb)
		Landing distance		Landing ground roll over 15m (50ft) barrier		Landing distance		Landing ground roll over 15m (50ft) barrier
		m	(ft)	m	(ft)	m	(ft)	m	(ft)

Head wind influence: for 10 kt multiply by 0.85 · for 20 kt multiply by 0.65 · for 30 kt multiply by 0.55
Down wind influence: add 10% to distance per section of 2 kt
Dried grass runway: add 15%

Estimated landing weight

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Total weight − (fuel required × 0.72 kg/L)

Adjusted landing distance calculator

Landing distance is pre-filled from the table’s Std-temperature row, interpolated between the 1045 kg and 845 kg columns at the estimated landing weight above. It stays fully editable — type over it, or change the pressure altitude to re-suggest.

Pressure altitude (for suggestion)

Head wind

Runway surface

Landing distance (m)

Suggested (Std temperature, interpolated by weight): —

Adjusted landing distance

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Adjusted landing distance (ft)

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Adjusted distance = landing distance × head wind factor × runway surface factor. This reproduces the correction factors on the supplied performance sheet; it is a planning aid only — confirm against the current approved POH/AFM figures before flight.

Aircraft data used

Important: This calculator reproduces the values and arithmetic structure in the supplied sheet. It is a planning aid, not a substitute for the aircraft POH/AFM, current approved weight-and-balance data, or operational limitations. Confirm the aircraft-specific figures before flight.