1. Introduction.

....1.1. The results of weighing and centre of gravity determination, checking to Appendix "A" Serial No. 1432, A.L's Nil, loading in accordance with Appendix 1 (Provisional laoding and C.G. diagram) to Chap. 1, Sect. 4, Vol. 1, of A.B.1565T and centre of gravity range, are included in this part of report.

....1.2. This was the second production aircraft of this type.

2. Weight summary. (see also Appendix 1).

....2.1.

....2.2. In addition to the above load the following alternative items may be carried:-

...........(a) 30 gallon tinned steel drop tank.
...........(b) 30 gallon vulcanized fibre drop tank.
...........(c) 30 gallon wood drop tank.
...........(d) 90 gallon tinned steel drop tank.
...........(e) 250 lb. G.P. or S.A.P. bomb.
...........(f) 500 lb. G.P., M.C. or S.A.P. bomb.

3. Maximum capacity of tanks.

Fuel	Fuselage tank	85 gallons
.	Wing tanks (2)	27 gallons
.	Total	112 gallons
Oil	Fuselage tank.	9 gallons

4. Centre of gravity.

....4.1. The centre of gravity with the aircraft loaded as stated in para. 2.1 measured relative to the datum point and parrallel to the datum line is 4.8" aft.

....4.12. With the addition of the various alternative loads quoted in para. 2.2 the centre of gravity ranges from 4.8" aft to 5.5" aft.

....4.21. Considering both normal and alternative loads the centre of gravity range due to dissipation of load is from 3.9" aft to 5.5" aft. The forward limit occurs on all loads when ammunition had been expended, bombs or drop tanks released and fuel consumed down to a supply sufficient for a half hour's running of the engine at maximum power permissible at grand level. The aft limit occurs when carrying the 90 gallon drop tank with the normal load.

....4.22. The aft limit obtained when considering the normal load only is 5.1" aft when all fuel from the wing tanks has been consumed.

....4.3. For purposes of test the aft limit quoted in para. 4.2 is extended by 1% S.M. chord which is equivalent to 0.8".

....4.4. All C.G. positions are quoted undercarriage down. The normal effect due to retraction is 3600 lb/in. and moves the C.G. aft by 0.4" at the normal load.

....4.5. The loading and C.G. diagram referred to in para. 1 quotes the following information in respect of weight and C.G.

"Maximum permissible all-up (i.e. take-off) weight for all forms of flying...........8500 lb.

Permissible C.G. range for all forms of flying...........from 3.5 inches to 6.5 inches aft of datum point."

....4.6. For conversion of C.G. position in inches to percentage of S.M. chord see Appendix 1.

5. General.

....5.1. A comparison between A. & A.E.E. results and the provisional loading and C.G. diagram referred to in para. 1 follows:-

....5.2. In Appendix 1 the various loads are set out in detail.

Appendix 1.

Equation to SM chord:-	CG in inches aft of datum + 18.65	X	100	=	% SMC
.	78.54	.	1