口诀:配平取中值；无油重量重心取中值（B737-15.3是例外);地板承载取小值,末位数是3取中值;起飞重量重心:B737_19以下取中值,19以上取小值;A320-第一位数字相比较，相同数字被排除，剩下一个要死记，数字相连取小值。

5.重量与平衡1. What are some characteristics of an airplane loaded with the CG at the aft limit?A.Lowest stall speed, highest cruise speed, and least stabilityB.Highest stall speed, highest cruise speed, and least stability.C.Lowest stall speed, lowest cruise speed, and highest stability.A X2. What characteristic should exist if an airplane is loaded to the rear of its CG range?A.Sluggish in aileron control.B.Sluggish in rudder controlC.Unstable about the lateral axisC X3. As the CG is moved forward, the stabilityA.ImprovesB.DecreaseC.dose not changeA X4. In flight ,as the time goes on , the CG willA.changeB.not changeC.may change or may not changeA X5. In small airplanes, normal recovery form spins may become difficult if theA.-CG is too far rearward and rotation is around the longitudinal axis.B.-CG is too far rearward and rotation is around the CG.C.-spin is entered before the stall is fully developed.C X1. Determine which statement given below is correct.A. Operating Weight is the sum of the DOW and the Take-off FuelB. Take-off Weight is equal to the addition of the DOW and the PayloadC. DOW is obtained by addition of the Basic Weight and Pantry load for A320A2. Determine which statement given below is correct.A. Operating Weight equals to the Take-off Weight minus the Take-off FuelB. Take-off Weight is equal to the addition of the Operating Weight and the PayloadC. Zero Fuel Weight is obtained by subtracting the Take-off Fuel from Operating WeightB3. For most modern swept-wing transports with a large proportion of fuel store in the wings, reducing fuel contents in wing tanks will result in:A. an aft movement of CG as fuel is consumedB. a forward movement of CG as fuel is burningC. no effect on CG movementB4. For most modern swept-wing transports, with the fuel burning , the CG will .A. not changeB. change randomC. change regularlyC5. The CG is often expressed as a percent of MAC, %0 of MAC means:.A. the CG is at trailing edge of MACB. the CG is at middle of MACC. the CG is at leading edge of MACC6. The CG is often expressed as a percent of MAC, %100 of MAC means:.A. the CG is at trailing edge of MACB. the CG is at middle of MACC. the CG is at leading edge of MACA7. Determine the ZFW CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment: NoneCargo =11,000 lb as: cargo 1 = 4,500 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 50Fuel =28,000 lbThe CG is: B.A. 33.8% at ZFWB. 31.9% at ZFWC. 30.0% at ZFW8. Determine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment: NoneCargo =11,000 lb as: cargo 1 = 4,500 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 50Fuel =28,000 lbThe CG is: C.A. 27.2% at take-offB. 28.4% at take-offC. 30.2% at take-off9. Determine the ZFW CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment: NoneCargo =10,000 lb as: cargo 1 = 3,500 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 150 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 40Fuel =30,000 lbThe CG is: C.A. 29.0 % at ZFWB. 32.7 % at ZFWC. 30.7 % at ZFW10. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing theFigure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment: NoneCargo =10,000 lb as: cargo 1 = 3,500 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 150 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 40Fuel =30,000 lbThe CG is: C.A. 31.6% at take-offB. 30.3% at take-offC. 28.8% at take-off11. D etermine the ZFW CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment = 100 lb in zone FCargo =9,500 lb as: cargo 1 = 3,000 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 50Fuel =25,000 lbThe CG is: A.A. 34.2 % at ZFWB. 32.3 % at ZFWC. 36.0 % at ZFW12. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment = 100 lb in zone FCargo =9,500 lb as: cargo 1 = 3,000 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 ; cabin OB = 70 ; cabin OC = 50Fuel =25,000 lbThe CG is: A.A. 31.8% at take-offB. 29.7% at take-offC. 27.9% at take-off13. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =3,990 kg as: FWD HOLD 1 = 1,995 kg ; AFT HOLD 4 = 1,995 kgPassengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 50 ; AFT PASS COMPT = 50Take-off Fuel = 11,700 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank = 2589 kgThe CG is: A.A. 21.5 % at ZFWB. 23.1 % at ZFWC. 20.0 % at ZFW14. D etermine take-off CG in percent of MAC under the following condition for a B737-300 aircraft by completing theFigure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =3,990 kg as: FWD HOLD 1 = 1,995 kg ; AFT HOLD 4 = 1,995 kgPassengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 50 ; AFT PASS COMPT = 50Take-off Fuel = 11,700 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank = 2589 kgThe CG is: A.A. 19.3% at take-offB. 20.9% at take-offC. 22.0% at take-off15. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 30Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgThe CG is: B.A. 17.0 % at ZFWB. 15.3 % at ZFWC. 18.5 % at ZFW16. D etermine the take-off CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 30Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgThe CG is: B.A. 15.6% at take-offB. 14.2% at take-offC. 13.0% at take-off17. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 2. Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 50 ; AFT PASS COMPT = 40Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgFlap setting =15°The STAB TRIM setting is: B.A. 5B. 4C. 3 3/418. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 2. Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 30Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgFlap setting =5°The STAB TRIM setting is: C.A. 5 1/2B. 5C. 5 1/419. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 2. Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 138 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 50 ; AFT PASS COMPT = 48Take-off Fuel = 12,000 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =2889 kgFlap setting =15°The STAB TRIM setting is: B.A. 4 3/4B. 3 3/4C. 3 1/420. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 34.6×46.4 inches? Condition:Floor load limit: 88 pounds/sq ftPallet weight: 41 poundsTiedown devices: 26 poundsA.A. 914.1 poundsB. 940.1 poundsC. 981.1 pounds21. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 36.5×48.5 inches? Condition:Floor load limit: 107 pounds/sq ftPallet weight: 37 poundsTiedown devices: 33 poundsC.A. 1, 295.3 poundsB. 1, 212.3 poundsC. 1, 245.3 pounds22. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 138.5×97.6 inches? Condition:Floor load limit: 235 pounds/sq ftPallet weight: 219 poundsTiedown devices: 71 poundsB.A. 21,840.9 poundsB. 21,769.9 poundsC. 22,059.9pounds23. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment = 100 lb in zone FCargo =9,500 lb as: cargo 1 = 3,000 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 150 PAX as: cabin OA = 30 ; cabin OB = 70 ; cabin OC = 50Fuel =25,000 lbThe CG is: B.A. 35.2% at ZFWB. 36.6% at ZFWC. 37.9% at ZFW24. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing theFigure 1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %Deviation or adjustment = 100 lb in zone FCargo =9,500 lb as: cargo 1 = 3,000 lb ; cargo 3 = 3,000 lb ; cargo 4 =1,000 lb ; cargo 5 = 2,500 lbPassengers (165 lb / PAX) = 150 PAX as: cabin OA = 30 ; cabin OB = 70 ; cabin OC = 50Fuel =25,000 lbThe CG is: C.A. 35.5% at take-offB. 34.9% at take-offC. 33.5% at take-off25. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 40Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgThe CG is: C.A. 20.0 % at ZFWB. 16.9 % at ZFWC. 18.6 % at ZFW26. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 2.Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 40Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111kg ;Central Fuselage Tank =3389 kgThe CG is: B.A. 15. 1% at take-offB. 16.5% at take-offC. 17.9% at take-off27. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 2. Condition:Dry Operating Weight = 32,930 kgDry Operating Index = 44.9Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg ; AFT HOLD 4 = 2,000 kgPassengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ;MID PASS COMPT = 60 ; AFT PASS COMPT = 30Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ;Central Fuselage Tank =3389 kgFlap setting =15°The STAB TRIM setting is: A.A. 4 1/2B. 4C. 5 1/428. D etermine which statement given below is correct.B.A. Operating Weight is the sum of the empty weight and the Take-off Fuel for B737B. Take-off Weight is equal to the sum of the DOW , the Payload and the Take-off FuelC. DOW is obtained by addition of the Basic Weight and Pantry load for A32029. D etermine which statement given below is correct.C.A. Operating Weight equals to the Take-off Weight minus the Take-off FuelB. Take-off Weight is equal to the addition of the DOW and the PayloadC. Landing Weight is obtained by subtracting the Trip Fuel from Take-off Weight30. F or most modern transports, if the CG at take-off is in the proper CG scope , the CG at ZFW B.A. will stay in the permitted CG scope certainlyB. may exceed the permitted CG scopeC. directly determined by the CG at take-off31. W hat is the maximum allowable weight that may be carriedon a pallet which has the dimensions of 96.1×133.3 inches? Condition:Floor load limit: 249 pounds/sq ftPallet weight: 347 poundsTiedown devices: 134 poundsA.A. 21,669.8 poundsB. 21,803.8 poundsC. 22,120.8 pounds32. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 148×125.2 inches? Condition:Floor load limit: 209 pounds/sq ftPallet weight: 197 poundsTiedown devices: 66 pounds26630.7A. 25,984.9 poundsB. 25,787.9 poundsC. 25,721.9 pounds33. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 87.7×116.8 inches? Condition:Floor load limit: 175 pounds/sq ftPallet weight: 137 poundsTiedown devices: 49 poundsA.A. 12,262.4 poundsB. 12,448.4 poundsC. 12,311.4 pounds1. Determine which statement given below is correct.A. Operating Weight is the sum of the DOW and the Take-off FuelB. Take-off Weight is equal to the addition of the DOW and the PayloadC. DOW is obtained by addition of the Basic Weight and Pantry load for A3202. Determine which statement given below is correct.A. Operating Weight equals to the Take-off Weight minus the Take-off FuelB. Take-off Weight is equal to the addition of the Operating Weight and the PayloadC. Zero Fuel Weight is obtained by subtracting the Take-off Fuel from Operating Weight3. For most modern swept-wing transports with a large proportion of fuel store in the wings, reducing fuel contents in wing tanks will result in:A. an aft movement of CG as fuel is consumedB. a forward movement of CG as fuel is burningC. no effect on CG movement4. For most modern swept-wing transports, with the fuel burning , the CG willA. not changeB. change randomC. change regularly5. The CG is often expressed as a percent of MAC, %0 of MAC means:A. the CG is at trailing edge of MACB. the CG is at middle of MACC. the CG is at leading edge of MAC6. The CG is often expressed as a percent of MAC, %100 of MAC means:A. the CG is at trailing edge of MACB. the CG is at middle of MACC. the CG is at leading edge of MAC7. Determine the ZFW CG in percent of MAC under theFigure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment: None; Cargo =11,000 lb as: cargo 1 = 4,500 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 50; Fuel =28,000 lb. The CG is:A. 33.8% at ZFWB. 31.9% at ZFWC. 30.0% at ZFW8. Determine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment: None; Cargo =11,000 lb as: cargo 1 = 4,500 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 50; Fuel =28,000 lb. The CG is:A. 27.2% at take-offB. 28.4% at take-offC. 30.2% at take-off9. Determine the ZFW CG in percent of MAC under theFigure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment: None; Cargo =10,000 lb as: cargo 1 = 3,500 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 150 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 40; Fuel =30,000 lb. The CG is:A. 29.0 % at ZFWB. 32.7 % at ZFWC. 30.7 % at ZFW10. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment: None; Cargo =10,000 lb as: cargo 1 = 3,500 lb ; cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 150 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 40; Fuel =30,000 lb. The CG is:A. 31.6% at take-offB. 30.3% at take-offC. 28.8% at take-off11. D etermine the ZFW CG in percent of MAC under theFigure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment = 100 lb in zone F; Cargo =9,500 lb as: cargo 1 = 3,000 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 50; Fuel =25,000 lb. The CG is:A. 34.2 % at ZFWB. 32.3 % at ZFWC. 36.0 % at ZFW12. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment = 100 lb in zone F; Cargo =9,500 lb as: cargo 1 = 3,000 lb , cargo 3 = 3,000 lb ,cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 160 PAX as: cabin OA = 40 , cabin OB = 70 , cabin OC = 50; Fuel =25,000 lb. The CG is:A. 31.8% at take-offB. 29.7% at take-offC. 27.9% at take-off13. D etermine the ZFW CG in percent of MAC under theFigure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =3,990 kg as: FWD HOLD 1 = 1,995 kg , AFT HOLD 4 = 1,995 kg; Passengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 50 , AFT PASS COMPT = 50; Take-off Fuel = 11,700 kg as: Wing Fuel Tanks = 9,111 kg , Central Fuselage Tank = 2589 kg. The CG is:A. 21.5 % at ZFWB. 23.1 % at ZFWC. 20.0 % at ZFW14. D etermine take-off CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =3,990 kg as: FWD HOLD 1 = 1,995 kg , AFT HOLD 4 = 1,995 kg; Passengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 50 , AFT PASS COMPT = 50; Take-off Fuel = 11,700 kg as: Wing Fuel Tanks = 9,111 kg , Central Fuselage Tank = 2589 kg. The CG is:A. 19.3% at take-offB. 20.9% at take-off15. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 ,MID PASS COMPT = 60 , AFT PASS COMPT = 30; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg.The CG is:A. 17.0 % at ZFWB. 15.3 % at ZFWC. 18.5 % at ZFW16. D etermine the take-off CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 60 , AFT PASS COMPT = 30; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg. The CG is:B. 14.2% at take-offC. 13.0% at take-off17. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 50 , AFT PASS COMPT = 40; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg; Flap setting =15°. The STAB TRIM setting is:A. 5B. 4C. 3 3/418. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 60 , AFT PASS COMPT = 30; Take-off Fuel =12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg; Flap setting =5°. The STAB TRIM setting is:A. 5 1/2B. 5C. 5 1/419. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 138 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 50 , AFT PASS COMPT = 48; Take-off Fuel = 12,000 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =2889 kg; Flap setting =15°. The STAB TRIM setting is:A. 4 3/4B. 3 3/4C. 3 1/420. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 34.6×46.4 inches? Condition:Floor load limit: 88 pounds/sq ft; Pallet weight: 41 pounds; Tiedown devices: 26 pounds.A. 914.1 poundsB. 940.1 poundsC. 981.1 pounds21. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 36.5×48.5 inches? Condition:Floor load limit:107 pounds/sq ft; Pallet weight:37 pounds; Tiedown devices: 33 pounds.A. 1, 295.3 poundsB. 1, 212.3 poundsC. 1, 245.3 pounds22. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 138.5×97.6 inches?Condition:Floor load limit:235 pounds/sq ft; Pallet weight: 219 pounds; Tiedown devices: 71 pounds.A. 21,840.9 poundsB. 21,769.9 poundsC. 22,059.9pounds23. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment = 100 lb in zone F; Cargo =9,500 lb as: cargo 1 = 3,000 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 150PAX as: cabin OA = 30 , cabin OB = 70 , cabin OC = 50; Fuel =25,000 lb. The CG is:A. 35.2% at ZFWB. 36.6% at ZFWC. 37.9% at ZFW24. D etermine the take-off CG in percent of MAC under the following condition for an A320 aircraft by completing the Figure 5-1.Condition:Dry Operating Weight = 94,000 lb and CG = 26 %; Deviation or adjustment = 100 lb in zone F; Cargo =9,500 lb as: cargo 1 = 3,000 lb , cargo 3 = 3,000 lb , cargo 4 =1,000 lb , cargo 5 = 2,500 lb; Passengers (165 lb / PAX) = 150 PAX as: cabin OA = 30 , cabin OB = 70 , cabin OC = 50; Fuel =25,000 lb. The CG is:A. 35.5% at take-offB. 34.9% at take-offC. 33.5% at take-off25. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 , MIDPASS COMPT = 60 , AFT PASS COMPT = 40; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg. The CG is:A. 20.0 % at ZFWB. 16.9 % at ZFWC. 18.6 % at ZFW26. D etermine the ZFW CG in percent of MAC under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 = 2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 140 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 60 , AFT PASS COMPT = 40; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg. The CG is:A. 15. 1% at take-offB. 16.5% at take-offC. 17.9% at take-off27. D etermine the STAB TRIM setting under the following condition for a B737-300 aircraft by completing the Figure 5-2.Condition:Dry Operating Weight = 32,930 kg , Dry Operating Index = 44.9; Cargo =4,000 kg as: FWD HOLD 1 =2,000 kg , AFT HOLD 4 = 2,000 kg; Passengers (165 lb or 75 kg / PAX) = 130 PAX as: FWD PASS COMPT = 40 , MID PASS COMPT = 60 , AFT PASS COMPT = 30; Take-off Fuel = 12,500 kg as: Wing Fuel Tanks = 9,111 kg ,Central Fuselage Tank =3389 kg; Flap setting =15°. The STAB TRIM setting is:A. 4 1/2B. 4C. 5 1/428. D etermine which statement given below is correct.A. Operating Weight is the sum of the empty weight and the Take-off Fuel for B737B. Take-off Weight is equal to the sum of the DOW , the Payload and the Take-off FuelC. DOW is obtained by addition of the Basic Weight and Pantry load for A32029. D etermine which statement given below is correct.A. Operating Weight equals to the Take-off Weight minus the Take-off FuelB. Take-off Weight is equal to the addition of the DOW and the PayloadC. Landing Weight is obtained by subtracting the Trip Fuel from Take-off Weight30. F or most modern transports, if the CG at take-off is in the proper CG scope , the CG at ZFWA. will stay in the permitted CG scope certainlyB. may exceed the permitted CG scopeC. directly determined by the CG at take-off31. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 96.1×133.3 inches?Condition:Floor load limit:249 pounds/sq ft; Pallet weight: 347 pounds; Tiedown devices: 134 pounds.A. 21,669.8 poundsB. 21,803.8 poundsC. 22,120.8 pounds32. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 148×125.2 inches?Condition:Floor load limit:209 pounds/sq ft; Pallet weight: 197 pounds; Tiedown devices: 66 pounds.A. 25,984.9 poundsB. 25,787.9 poundsC. 25,721.9 pounds33. W hat is the maximum allowable weight that may be carried on a pallet which has the dimensions of 87.7×116.8 inches?Condition:Floor load limit:175 pounds/sq ft; Pallet。