曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

time may require re-weighing to keep the basic empty weight and
center of gravity current. The frequency of weighing is determined by
the operator. All changes to the basic empty weight and center of
gravity are the responsibility of the operator. Refer to Section 8 for
specific servicing procedures.
1. Preparation:
a. Inflate tires to recommended operating pressures.
b. Service brake reservoir.
c. Drain fuel system.
d. Drain ice protection system.
e. Service engine oil.
f. Move crew seats to the most forward position.
g. Raise flaps to the fully retracted position.
h. Place all control surfaces in neutral position.
i. Verify equipment installation and location by comparison to
equipment list.
2. Leveling:
a. Level longitudinally with a spirit level placed on the pilot door
sill and laterally with of a spirit level placed across the door
sills. Alternately, level airplane by sighting the forward and aft
tool holes along waterline 95.9.
b. Place scales under each wheel (minimum scale capacity, 500
pounds nose, 1000 pounds each main).
c. Deflate the nose tire and/or shim underneath scales as
required to properly center the bubble in the level.
Original: 03-27-07
42 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
3. Weighing:
a. With the airplane level, doors closed, and brakes released,
record the weight shown on each scale. Deduct the tare, if
any, from each reading.
4. Measuring:
a. Obtain measurement ‘x’ by measuring horizontally along the
airplane center line (BL 0) from a line stretched between the
main wheel centers to a plumb bob dropped from the forward
side of the firewall (FS 100). Add 100 to this measurement to
obtain left and right weighing point arm (dimension ‘A’).
Typically, dimension ‘A’ will be in the neighborhood of 157.5.
b. Obtain measurement ‘y’ by measuring horizontally and
parallel to the airplane centerline (BL 0), from center of
nosewheel axle, left side, to a plumb bob dropped from the
line stretched between the main wheel centers. Repeat on
right side and average the measurements. Subtract this
measurement from dimension ‘A’ to obtain the nosewheel
weighing point arm (dimension ‘B’).
5. Determine and record the moment for each of the main and nose
gear weighing points using the following formula:
Moment = Net Weight x Arm
6. Calculate and record the as-weighed weight and moment by
totaling the appropriate columns.
7. Determine and record the as-weighed C.G. in inches aft of datum
using the following formula:
C.G. = Total Moment ÷ Total Weight
8. Add or subtract any items not included in the as-weighed condition
to determine the empty condition. Application of the above C.G.
formula will determine the C.G for this condition.
9. Add the correction for engine oil (15 lb at FS 78.4), if the airplane
was weighed with oil drained. Add the correction for unusable fuel
(15.0 lb at FS 154.9) to determine the Basic Empty Weight and
Moment. Calculate and record the Basic Empty Weight C.G. by
applying the above C.G. formula.
Original: 03-27-07
13772-130 43 of 58
Cirrus Design Section 9
SR22 Supplements
10. Record the new weight and C.G. values on the Weight and
Balance Record.
The above procedure determines the airplane Basic Empty Weight,
moment, and center of gravity in inches aft of datum. C.G. can also be
expressed in terms of its location as a percentage of the airplane
Mean Aerodynamic Cord (MAC) using the following formula:
C.G. % MAC = 100 x (C.G. Inches – LEMAC) ÷ MAC
Where:
LEMAC = 133.1
MAC = 47.7
Original: 03-27-07
44 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
Center of Gravity Limits
The charts below depict the airplane center-of-gravity envelope in
terms of inches aft of the reference datum and as a percentage of the
Mean Aerodynamic Cord (MAC). The relationship between the two is
detailed in the weighing instructions.
2000
2200
2400
2600
2800
3000
3200
3400
3600
136 138 140 142 144 146 148 150
C.G. - Inches Aft of Datum
Weight - Pounds
12.5% M AC
FS 139.1
2700 lb
9.8% MAC
FS 137.8
2100 lb
19.2% M AC
FS 142.3
3400 lb
31.5% M AC
FS 148.1
3400 lb
31.5% MAC
FS 148.1
2100 lb
Original: 03-27-07
13772-130 45 of 58
Cirrus Design Section 9
SR22 Supplements
Weight & Balance Loading Form
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(149)