Please help me to solve this problem, it needs to calculate aircraft's centre of gravity, as follows:

1.Weight and the ARM:

(1) Front wheel weight: 600kg,to Datum distance:372mm,

(2) Main wheel(Wl+Wr) weight:1400kg,to Datum distance:2200mm,Wing frontier to the Datum distance:1963mm,

(3) Total weight: 2000kg,

2.I need to calculate the following results:

(1) The aircraft was in a horizontal status of longitudinal CG position, vertical CG position.

(2) The front end of the aircraft rise an angle (such as 3 degrees or 5 degrees),its vertical CG position.

(3) The front end of the aircraft drop an angle (for example -3 degrees or -5 degrees),its vertical CG position.

Thanks for you!