(d)  
Make sure that all the bleed air and electrical loads are off.

 (e)  
Make sure the engine indications are in the correct ranges.

 WARNING: MAKE SURE THE AIRPLANE HAS THE CORRECT GROSS WEIGHT,
_______ SUFFICIENT BRAKES, AND THAT THE (JET BLAST) IS NOT DANGEROUS (AMM 71-00-00/201). THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO THE AIRPLANE AND ENGINE.
 (f)  
Move the forward thrust lever to the static takeoff N1.

 (g)  
Make sure the engine accelerates smoothly.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
TEST NO. 5 - POWER ASSURANCE CHECK__________________________________
 (h) (i) (j)  Let the engine become stable and make sure the engine instrumentation indications are in the operation ranges.Move the forward thrust lever to the idle position.Make sure the engine decelerates smoothly and is stable at idle.
 (k)  If no more tests are necessary, do the engine shutdown (normal) operation (AMM 71-00-00/201).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
TEST NO. 5 - POWER ASSURANCE CHECK
__________________________________
 ~............................................................................... | POWER ASSURANCE CHECK EXAMPLE (CFM56-3-B1 ENGINE 20K LBS THRUST) | | | | Let Test Conditions - Ambient Temperature (OAT) = 90°F (32°C) | | Use MPA Fan Speed (for this example 85% N1) | ................................................................................. | Procedure: | ................................................................................. | 1. From the MPA Test Table (85% N1 Fan Speed): | | at OAT=90° F, N1 Target = 87.3% | | for 20K pounds thrust, EGT max = 848°C | | for -3-B1 Engines, N2 max = 98.6% | ................................................................................. | 2. Set N1 target, make a record of N1, N2, and EGT after the engine | | operation is stable for four minutes: | | N1 = 87.0% N2 = 95.5% EGT = 780°C | ................................................................................. | 3. Adjust the parameters to the N1 target as follows: | | use the N1 difference (N1 target - N1 record) = 87.3 - 87.0 = 0.3%, | | | | For each 0.1 %N1 positive difference (N1 target more than N1 | | record), add 1.0°C to the EGT record to get EGT adj | | add 0.045% to the N2 record to get N2 adj | | | | N2 adj = N2 record + (0.3/0.1)(0.045) = 95.5 + 0.1 = 95.6% | | EGT adj = EGT record + (0.3/0.1)(1) = 780 + 3 = 783°C. | ................................................................................. | 4. Compare the adjusted parameters to the limits found in Step 1: | | N2 max = 98.6% | | N2 margin = N2 max - N2 adj = 98.6 - 95.6 = 3.0% | | EGT max = 848°C | | EGT margin = EGT max - EGT adj = 848 - 783 = 65°C. | ................................................................................. | 5. EGT adjustment for the HPTCC Timer: | | The timer is not available, no adjustment is necessary. | ................................................................................. | 6. EGT adjustment for the altitude: | | There is an altitude effect for this thrust rating. The MPA tables | | are for sea level. If the route structure of the airplane includes | | an airport at 4000 feet, decrease the EGT margin by 44°C. | ................................................................................. | 7. N2 adjustment for the thrust rating: | | No adjustment is necessary at this thrust rating. | ................................................................................. | 8. Result of the MPA Test: | | N2 margin = 3.0% | | EGT margin = 65°C at sea level or | | EGT margin = 65 - 44 = 21°C at altitude (4000 feet). | 2...............................................................................1
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