Pilatus PC-12 NGX, Руководство пилота

Страница: 528 / 625

6-4-2 Weighing
1 With the airplane level, record the weight shown on each load cell in the appropriate
section on
Fig. 6-4-1 , Airplane Weighing Form.
2 Calculate airplane C.G. Arm and record on Fig. 6-4-2 , Airplane Basic Empty Weight. The
C. G. Arm calculation formula is:
C. G. Arm in (m) = ((L + R) x B + T x A) / (L + R + T)
3 Adjust weight and moment for unusable fuel and optional equipment installed after
airplane weighing to determine airplane Total Basic Empty Weight and Moment.
4 Calculate Basic Empty Weight C.G.
5 Update Fig. 6-6-1 , Weight and Balance Record, as required.
Section 6 - Weight and Balance (EASA Approved)
Weighing
Pilot's Operating Handbook Report No: 02406
Issue date: Mar 06, 2020
Page 6-4-2
12-C-A15-30-0604-00A-169A-A
FOR
GENERAL
AND
FAMILIARIZATION
PURPOSES
ONLY