签派执照考试书V3 飞机性能载重平衡部分 A319/B737为例 4.32水平安定面配平

Takeoff Horizontal Stabilizer Trim Setting A horizontal stabilizer trim setting is used during all takeoffs. These settings are designed to produce: The proper all-engines operating climb-out attitude at V2 + 15 to 25 kts The proper one-engine inoperative climb-out attitude at V2 Reasonable column forces for the pilots Trim setting is provided as a function of the airplane weight, C.G., flap setting, and engine thrust level.

Takeoff Horizontal Stabilizer Trim Setting Lift Lift (downward) Thrust Weight Downward force from the horizontal tail is used to rotate the airplane about the main gear for takeoff rotation, and to hold the airplane in the correct pitch attitude for the climb-out from the airport after liftoff. (Drag contribution to moment about CG is negligible)

Horizontal Stabilizer Movement

Horizontal Stabilizer Jackscrew

Trim Setting on Flight Deck 767-300 Example

Takeoff Horizontal Stabilizer Trim Setting 777-200ER Example AND = Airplane Nose Down ANU = Airplane Nose Up Increasing downward tail force Decreasing downward tail force

Takeoff Horizontal Stabilizer Trim Setting 777-200ER With High Thrust Engines (>90K)

Determining the Stabilizer Trim Setting Takeoff weight = 220,000 kg Center of gravity = 39%MAC 777-200ER Example Stab Trim Units = 3.0

Determining the Stabilizer Trim Setting 777-200ER Example AIRPLANE GROSS WEIGHT - KILOGRAMS 110000 120000 130000 140000 150000 160000 170000 180000 190000 200000 210000 220000 230000 240000 250000 7 9 18 20 22 24 26 28 30 32 34 36 38 40 42 44 %MA C 8 5 4 3 6 Stabilizer Trim Units Flaps 15 & 20 Full Thrust to 15% Derate 220000 kg 39

力矩 The influence of an item depends on 2 factors : 力 Weight 力臂 Harm（ARM） : item CG position 力矩Moment = Weight  Harm

The Mean Aerodynamic Chord and the CG index Airplane c.g. is often expressed in terms of %m.a.c. BA of airplane c.g. Datum for B.A. lemac Where: BA is the balance arm of the airplane’s c.g. c.g. is in terms of %m.a.c.

重心的表示方法

Definition of the Reference Chord Z 25%RC 18.850m 4.1935m 17.8015m 2.540m H-arm 0 X

Definition of the Reference Chord Z 25%RC MAC LEMAC H-arm 0 X

4.32 水平安定面 问题(P170)： 737-300,P141,R-1条件, 重量=90,000 KG, CG=635.7 INCH, LEMAC=625, MAC=134 解:CG - LEMAC = 635.7 – 625 = 10.7 %MAC=10.7 / 134 =8.0 % (P138) 查表=7 ¾ ANU

Data in the （M）CDU 43,500 + 250 43,750 + 3,700 1 2 0 + 10,080 57,530 + 14000 71,530 3 2 8 5 7 5 3 6 3

MANIFEST1-成图

平衡图 （ 表 ）各项注释

WB例题平衡图填写过程

根据飞机起飞襟翼和起飞重心%MAC的位置查出相应尾翼配平数值 WB例题平衡图填写过程 根据飞机起飞襟翼和起飞重心%MAC的位置查出相应尾翼配平数值 FLAP5

WB划线法平衡图图样

WB平衡图划线法填写过程 根据无油和起飞的总指数、总重量划出飞机重心位置%MAC TOW ZFW 17.9 16.5 5

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