South East Asian Airlines

LET 410 UVP-E

L410

South East Asian Airlines

Aircraft Limitations

Weight Limitation

Maximum Ramp Weight (MRW) : 6,420 kg

Maximum Zero Fuel Weight (MZFW) : 5,840 kg

Maximum Take-off Weight (MTOW) : 6,400 kg

Maximum Landing Weight (MLW) : 6,200 kg

Forward C.G. Limit

Empty Weight : 17%

Maximum Take-off Weight : 26%

Aft C.G. Limit

All Weight :30%

L410

South East Asian Airlines

L410

Passenger Limitation

The maximum permissible no. of occupants including the crew is 21

Floor Loading Limitations

Maximum load on baggage compartment:

Front Baggage Compartment : 220 lb (100 kg)

Rear Baggage Compartment : 330 lb (150 kg)

Upper : 132 lb (60 kg)

Lower : 198 lb (90 kg)

Maximum specific load on the floorof baggage compartments (front & rear) : 82 lb/sq.ft (400 kg/m2)

Maximum specific load on the floorof passenger cabin : 82 lb/sq.ft (400 kg/m2)

South East Asian Airlines

Fuel Capacity

L410

Wing Tanks lb (kg) Wing Tip Tanks lb (kg)

LH RH LH RH

Total fuel tank capacity1,102(500)

1,102(500)

346(156.9)

346(156.9)

Unusable fuel10

(4.5)10

(4.5)4

(1.9)4

(1.9)

Total usable fuel1,092

(495.5)1,092

(495.5)342

(155)342

(155)

Differences in fuel quantity between the LH and RH group oftanks not exceeding 132 lb (60 kg) have no influence on theflight performance of the airplane.

South East Asian Airlines

Passenger Configuration

L410

South East Asian Airlines

Weight & Moment Limit

L410

South East Asian Airlines

C.G. Limits & MAC Positions

L410

The center of gravity limits must always inside the envelope given by thecurve shown in figure below. The position of Mean Aerodynamic Chord(MAC) is also shown in the figure below. The dimensions are given in mm(inches). The airplane will not tip over when being loaded if its center ofgravity is maintained within the envelope during loading.

South East Asian Airlines

Load Planning Procedure

L410

Load Planning Moment System

To compute the weight and balance of our aircraft, use the LET 410 UVP-E Load Sheet Form. Use the respective values as follows:

1. Write the identification of flight, aircraft and crew in the assigned field.

2. Record the weight and moment for crew from SEAIR

Load diagram Form. This weight must not exceed the maximum specific floor loading.

To determine the moment, multiply the actual weight to its corresponding arm.

3. Record the weights and moments for passenger and baggage from Passenger Manifest. This weight must not exceed the maximum baggage weight respectively.

SEAIR Inc. uses the actual weight.

4. Determine and record the Basic Empty Weight, arm and moment of a given aircraft from SEAIR Load Diagram Form.

South East Asian Airlines

L410

5. Add the crew weight and the total traffic load to Basic Empty Weight to obtain the Zero Fuel Weight.

6. Determine and record the weight and corresponding moments for the usable fuel mains. The fuel loading include fuel for starting engines, taxi, trip, holding and required reserves.

7. Record the corresponding weight and moment for the usable fuel in the wingtip tanks (wtt) as appropriate.

8. Add the total weight of the fuel to Zero Fuel Weight to obtain the Ramp Weight. This weight must not exceed the Maximum Ramp Weight (MRW).

9. Record the weight and moment of start and taxi fuel.

10. Determine the take-off weight by subtracting the start and taxi fuel weight to Ramp Weight. This weight must not exceed the Maximum Take-off Weigh (MTOW).

11. Determine the take-off weight moment by adding the moment for crew, total traffic load, basic empty weight, usable fuel and start and taxi fuel.

12. Divide the actual take-off weight from its corresponding moment to obtain the value of take-off weight arm.

13. Determine and record the expected fuel burn.

Fuel Consumption : 300 kg/hr or 5 kg/min

South East Asian Airlines

L410

14. Subtract the expected fuel burn from take-off weight to obtain the landing weight. This weight must not exceed the Maximum Landing Weight (MLW).

15. In case of Last Minute Change (LMC), determine and record the weights and moments of the LMC. Recalculate the weight for take-off and landing (LMC Corrected) and write down the result in the appropriate field.

LMC is the load changes after completion of the loading sheet (i.e. delayed passengers, urgent cargo, etc.)

16. Write down the payload details in the appropriate fields and the remarks/notoc as necessary.

17. To compute for Forward C.G. Value, indicated in C.G. Limits at take-off weight, use the formula below:

TOW (kg) – 4500 Fwd C.G. (%) = (

2100 X 9 ) + 17

18. To compute for Take-off C.G., use the formula below:

T/O Arm – Distance from R.D. to L.E. T/O C.G. (%) =

MAC X 100