NOTE: The method for the calculation of the CG location in
____ %MAC is given in the Weight and Balance Manual. The calculation of the %MAC is difficult. Your airline weights engineer has the Weight and Balance Manual.
 1)  The calculation of the center of gravity (CG) location depends on the location of the loads on the airplane. a) You must start with the empty weight and the CG of the
 airplane. b) Get the weight and the CG of each load (i.e. fuel,
 crew, load in the aft cargo compartment). c) Calculate the total airplane weight and the total CG. d) Change the total airplane CG into units of %MAC with
 the method in the Weight and Balance Manual.
 (c)  Use the tables that follow to find the N1 limit of the second engine from the table with the applicable engine thrust, the airplane model, and the center of gravity. 1) If you do not know the CG of the airplane, use the table
 with the CG requirement "CG Not Known, But Within Taxi Range".
 2)  Find the second engine N1 limit where the row and column intersects for the ambient temperature and the airplane gross weight. a) Use the lower ambient temperature value if the actual
 ambient temperature is between the temperature values in the table. b) Use the lower gross weight value if the actual gross weight is between the values in the table. 3) Make a record of the N1 limit for the second engine.
 S 842-005-C00
 (4)  Do the steps to operate one or two engines at high power in the procedure for normal power plant operation (AMM 71-00-00/201).
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
~............................................................................. | MINIMUM GROSS WEIGHT FOR TWO ENGINES SET TO THE SAME POWER | ............................................................................... | AIRPLANE MODEL | POWER SETTING | MINIMUM GROSS WEIGHT | ............................................................................... | 737-300 | TAKEOFF POWER | 106,200 LB 48,170 KG | | .............................................................. | | PART POWER | 68,000 LB 30,840 KG | 2................…...............…............................................1
 ~............................................................................. | MINIMUM GROSS WEIGHT FOR ONE ENGINE OPERATION - ALL POWER SETTINGS *[1] | ............................................................................... | AIRPLANE MODEL | THRUST | CENTER OF | MINIMUM GROSS WEIGHT | | | RATING | GRAVITY | | ............................................................................... | 737-300 | 20,000 LB | 5-15 %MAC | 77,100 LB 35,000 KG | | | .................................................. | | | NOT KNOWN | 87,000 LB 39,456 KG | 2................…...........…...........…....................................1
 *[1] INCLUDES TAKEOFF POWER
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
~.............................................................................. | MINIMUM GROSS WEIGHT AND 2ND ENGINE N1 LIMIT FOR 1ST ENGINE SET TO TAKEOFF | ................................................................................ | AIRPLANE MODEL | THRUST RATING | CENTER OF GRAVITY | ................................................................................ | 737-300 | 20,000 LB | CG NOT KNOWN, BUT WITHIN TAXI RANGE | .................…...............….............................…................ | MINIMUM | AMBIENT TEMPERATURE | | GROSS WEIGHT ................................................................ ................. -40 | -31 | -22 | -13 | -4 | 5 | 14 | 23 | 32 | 41 |°F| | KG | LB | -40 | -35 | -30 | -25 | -20 | -15 | -10 | -5 | 0 | 5 |°C| ................................................................................ | 39456 | 87000 | 46.1| 46.6| 47.1| 47.6| 48.1| 48.5| 49.0| 49.5| 49.9| 50.4| | ................................................................................ | 39909 | 88000 | 49.9| 50.4| 50.9| 51.4| 51.9| 52.5| 53.0| 53.5| 54.0| 54.5| | ................................................................................ | 40363 | 89000 | 53.6| 54.1| 54.7| 55.3| 55.8| 56.4| 56.9| 57.5| 58.0| 58.5| | ................................................................................ | 40816 | 90000 | 57.3| 57.9| 58.5| 59.1| 59.7| 60.3| 60.9| 61.4| 62.0| 62.6| | ................................................................................ | 41270 | 91000 | 61.0| 61.7| 62.3| 62.9| 63.6| 64.2| 64.8| 65.4| 66.0| 66.6| | ................................................................................ | 41723 | 92000 | 64.7| 65.4| 66.1| 66.8| 67.5| 68.1| 68.8| 69.4| 79.1| 70.7| | ................................................................................ | 42177 | 93000 | 68.5| 69.2| 69.9| 70.6| 71.3| 72.0| 72.7| 73.4| 74.1| 74.8| | ................................................................................ | 42630 | 94000 | 72.2| 72.9| 73.7| 74.5| 75.2| 76.0| 76.7| 77.4| 78.1| 78.8| | ................................................................................ | 43084 | 95000 | 75.9| 76.7| 77.5| 78.3| 79.1| 79.9| 80.6| 81.4| 82.2| 82.9| | ................................................................................ | 43537 | 96000 | 79.6| 80.5| 81.3| 82.1| 83.0| 83.8| 84.6| 85.4| 86.2| 87.0| | ................................................................................ | 43991 | 97000 | 81.4| 82.1| 83.0| 83.8| 84.7| 85.4| 86.3| 87.1| 88.0| 88.9| | ......................….....….....….....….....….....….....….....….....….....…... | KG | LB | 2ND ENGINE N1 LIMIT (1ST ENGINE SET AT TAKEOFF) | 2.......….......…..............................................................1
　
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