Ok Andy.. I couldn't find what I was looking for but found the Air Atlantique Dove Ops Manual instead
1.3 WEIGHT LIMITS
Maximum Take-off weight: 9150lb
Maximum Landing weight: 8625lb
APS weight, without pilot: 6894lb
Datum Point: 31.2 inches aft of the front levelling peg on the port side of the fuselage as defined in the flight manual
Centre of Gravity Range:
Forward Limit - Undercarriage extended:3.7in forward of datum.. Undercarriage retracted: 3.3in forward of datum
Aft Limit - Undercarriage extended: 7.2in aft of datum.. Undercarriage retracted: 7.6in aft of datum.
It would be handy if I could put my hand on the FM but I can't.. it's probably in the loft
I'll try and type the APS Form..
ITEM...........................WEIGHT(lb)................LEVER ARM(in).......MOMENT
Dry operating weight:........6821........................ -5.41................. -36,894
Pilot:......................................................... -56.40
Fuel:.......................................................... +18.00
Engine Oil:.................... INCLUDED IN AIRCRAFT D.O.W.
Rear Baggage:............................................... +154.80
Passengers - Row 1:........................................ -18.00
Passengers - Row 2:........................................ +14.40
Passengers - Row 3:........................................ +48.00
Passengers - Row 4:........................................ +80.40
TAKE-OFF WEIGHT/C.of G.:
LESS Fuel Burn:.............................................. +18.00
LANDING WEIGHT:
(This is/was the actual APS form used for G-DHDV)
6.2 CENTRE OF GRAVITY
The aeroplane must be loaded in such a way that the Centre of Gravity lies between 3.7inches forward (-) and 7.2inches aft (+) of datum point. These are limits for take-off and landing with undercarriage extended. With undercarriage retracted, the Centre of Gravity lies between 3.3inches forward (-) and 7.7inches aft (+) of the datum point.
The centre of gravity datum is defined as a point 31.2 inches aft of the front levelling peg on the port side of the fuselage (defined in the aircraft Flight Manual). The following formula is to be used when calculating the aircraft centre of gravity:
(Empty weight x Empty arm) + (Weight of load x Respective arms)
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Empty weight = Total weight of load
= Empty moment + load moment
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Total Weight
Hope this is of some use
ATB
DaveB