Other limitations are linked to payload carriage:  . the permissible limits for shear loads and bending moments due to payload
(1.10.03) and
.  the maximum weights that can be transported or loaded on cabin floor or on cargo compartment floor (1.10.04 floor loading limits).
WEIGHT AND
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WEIGHT AND
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B. WEIGHT AND BALANCE MANUAL

.  the paragraphs 1.10.05 to 1.10.07 deal with cargo compartment loading and give rules and recommendations for weight limitation, location, tying down of each load type (number of containers, maximum weight, load factors, …) and additional limitations in case of latch failure(s).

B. WEIGHT AND BALANCE MANUAL

1.3. 1.20: FUEL
This chapter of the WBM describes the influence on the aircraft CG position of the use of the fuel systems (refueling and fuel burn).
The first part (1.20.01) describes briefly the aircraft fuel system : the arrangement of the tanks and the collector positions, fuel circulation within the different tanks during refueling and defueling.
The last part of the introduction is the following :
.
A310, A320 family, A330/340 family

.
A300, A300-600

C. Fuel volume, density and weight

All fuel quantities in this manual are in liters, and all fuel weights
are based on a fuel density of 0.782 kg per liter unless otherwise
specified.

It is important to note the value of the density used in the WBM, because variations in actual fuel density due to specific gravity and temperature may result in large weight variations relative to those given in the manual.
The second part (1.20.02) of the chapter details the aircraft refueling of tanks sequence : 

Using this sequence it is possible to determine for each fuel quantity on board the aircraft, how much fuel each tank contains.
WEIGHT AND
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WEIGHT AND
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B. WEIGHT AND BALANCE MANUAL

As noted below the graph in this example : 
. Points ., é and . are fixed in weight (kg or lb) irrespective of fuel density.
. Points ., . and ü are variable depending of fuel density. This explains why for one selected fuel quantity there might be more or less fuel in a given tank depending on the fuel density value.
This is particularly appreciable for A330/340, A310 and A300-600R aircraft that is to say aircraft with fuel tank in the horizontal stabilizer.
In addition to the above graph, a second graph presents the variations of the CG position of the fuel loaded on aircraft and a table gives all the coordinates of this graph.
Note : the table and the corresponding graph are designed for the WBM standard fuel density
(0.785 kg/l or 0.782 kg/l), whenever this table needs to be done for another density all break
points (cf example points ., . and ü) that depend on fuel density have to be recalculated with the corresponding fuel quantities.
　
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