. Ex : A330-200
B. WEIGHT AND BALANCE MANUAL
1.8. 1.80: ACTIONS ON GROUND
This section contains information on jacking points, weighing on jacks or on wheels, and CG calculations. It first describes the Weighing point locations (1.80.02) and then gives all formulae necessary to the calculation of the weight and CG of an aircraft weighed on wheels (1.80.04) and weighed on jacks (1.80.05). Section 1.80.06 gives the Equipment/component removal list: information on weight and H-arm of equipment normally removable from the aircraft for maintenance purposes. These equipment are parts of the wing (slats, flaps…), part of the engine pylon and nacelle, doors,…
1.9. 1.90: Examples
Note 1 : the examples presented in this section are valid only for the balance scale presented in
1.00.05.
Note 2 : the Typical loading diagram (1.90.04) is drawn on the aircraft certified limits diagram. It
should be drawn on the operational limits diagram to take into account the aircraft CG
movements due to CG determination errors and moving part transfer during flight.
WEIGHT AND
BALANCE
WEIGHT AND
BALANCE
B. WEIGHT AND BALANCE MANUAL
2. SECTION 2 : WEIGHT REPORT
This chapter contains the documents supplied with the aircraft at delivery: . 2.10 : Delivery weighing report which contains data to establish aircraft Operational Empty Weight (OEW) and Manufacturer Empty Weight (MEW) and corresponding CG positions. . 2.20 : Weighing check list which describes each item position and unit weight. In case the item is not present during aircraft weighing it should be mentioned in this section.
C. BALANCE CHART DESIGN
BALANCE CHART DESIGN INTRODUCTION
The purpose of this section is to detail the whole process that leads to the production of a balance chart and of the corresponding AHM560. It first describes the calculation tools that are used (moment and index), then the calculation of the influence on aircraft CG of any item loading and finally the method to determine the aircraft operational limits.
A330-243
LOAD and TRIM SHEET
VERSION : 18 BC-264 YC
DRY OPERATING WEIGHT CONDITIONS
WEIGHT (kg) H-arm (m)
I = (H-arm -33.1555) x W 5000 + 100
DRY OPERATING WEIGHT INDEX
AIRCRAFT REGISTER :
DATE : PREPARED BY :
FLT Nbr : CAPT. SIGNATURE :
FROM : TO :
DRY OPERATING WEIGHT
WEIGHT DEVIATION (PANTRY) ±
CORRECTED DRY OPERATING WEIGHT =
CARGO +
PASSENGERS x 8 4 = +
ZERO FUEL WEIGHT =
TOTAL FUEL ONBOARD +
TAKEOFF WEIGHT =
17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Aircraft CG (%MAC)
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