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钻石20飞机飞行手册 DA 20 Airplane Flight Manual(41)

时间:2011-10-28 13:14来源:蓝天飞行翻译 作者:admin
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In case of equipment changes, the new weight and empty weight CG position must be determined by calculation or by weighting and must be entered in the Weight & Balance Report. These sample forms are included in this manual and can be used for airplane weighing, calculation of the empty weight CG position, and for the determination of the useful load.
NOTE

After every repair, painting or change of equipment, the new empty weight must be determined as required by applicable air regulations.  Weight, empty weight, CG position, and useful load must be entered in the Weight & Balance Report by an authorized personnel.

6.2. AIRPLANE WEIGHING
Pre-weighing conditions:
-
 equipment must be in accordance with the airplane equipment list

-
 brake fluid, lubricant (6 US qt / 5.7 liters) and

-
 unusable fuel, included (2 liters unusable, 3.18 lbs/1.44 Kg)


To determine the empty weight and the empty weight CG position, the airplane must be positioned in the above mentioned pre-weighing condition, with the nose gear and each main gear on a scale.  Ensure that the aircraft is level longitudinally and laterally as illustrated in Figures 6.1 and 6.2.
With the airplane correctly positioned, a plumb line is dropped from the leading edge of each wing at the root rib to the floor; join these two points to determine the reference datum (RD). From this line use a suspended plumb line aligned with each landing axle gear to measure the distances X (nose gear), X2LH (left main gear) and X2RH (right main gear).
The following formulas apply:
Finding Empty - Center of Gravity (XCG)
Empty Weight:  G = G1+ G2LH + G2RH lbs [kg]
Empty Weight CG Formula:
(G1 x X1)+(G2LH x X2LH)+(G2RH x X2RH)
XCG =
G1 + G2LH + G2RH

Finding Empty - Weight Moment
Empty-weight Moment M = Empty Weight (G) x Empty-weight CG (XCG)

CAUTION


ITEMS FORWARD OF THE REFERENCE DATUM ARE CONSIDERED TO HAVE A NEGATIVE LEVER ARM. ITEMS AFT OF THE REFERENCE DATUM ARE CONSIDERED TO HAVE A POSITIVE LEVER ARM. 
Record the data in the Weighing Report included at the back of this manual.  Figure 6.3, Sample Weighing Report is for reference only. 
Doc # DA202-C1  April 06, 2010  Page 6 - 3 
Revision 25  DOT Approved 


Figure 6.1. Longitudinal Leveling Diagram
Legend: X1 Arm - Datum to center line nose wheel X2 Arm - Datum to C/L main wheels (LH and RH) G1 Net weight - Nose wheel G2 Net weight - Main wheels (LH and RH) G Empty weight XCG Arm - Empty - weight (Calculated)


Model: DA20-C1 Serial Number Registration Data with reference to the Type Certificate Data Sheet and the Flight Manual
Reference Datum:  Leading edge of wing at root rib. 
Horizontal reference line:  Wedge 1000:55.84, 2000mm (78.7 in) aft of the step in the fuselage 
 
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