(k)  
Make a record of the cabin rate of change, left engine bleed pressure and engine N1% data.

 (l)  
Close this circuit breaker on the P6-2 panel: 1) IDLE CONT

 (m)  
Close these circuit breakers on the P6-3 circuit breaker panel: 1) NOSE GEAR AIR/GND 2) LANDING GEAR AIR/GND RELAY & LTS.

 (n)  
Operate the MANUAL VALVE switch on the pressurization control panel to set pressure differential to 4.0 psid.

 D. Airplane Leak Down Check
 S 782-014
 (1)  Do this check of the leakage of the cabin pressure:
 (a)  
Make a record of the cabin temperature.

 (b)  
When 4.0 psid on the DIFF PRESS gauge has been achieved and stabilized, fully close (manually) the aft outflow valve. 1) Make sure that the indication on the gauge above the

 CLOSED/OPEN switch on the P5-17 pressurization control panel shows that the valve is fully closed.

 (c)  
Set the L PACK switch to OFF.

 (d)  
Set the BLEED 1 switch to OFF.

 (e)  
Shut down the left engine.

 CAUTION: THE APU MUST BE KEPT IN OPERATION IN THE EVENT A BLEED
_______ SOURCE IS NEEDED IF A VERY HIGH RAPID CABIN DEPRESSURIZATION OCCURS OR IF ELECTRICAL POWER IS NEEDED AND A GROUND SOURCE IS NOT USED. FAILURE TO KEEP THE APU IN OPERATION COULD POSSIBLY RESULT IN EQUIPMENT DAMAGE.
 (f)  
Continue to operate the APU.

 (g)  
Make a record of the pressure differential indications during the cabin pressure leak down: 1) Start the check at 4.0 psid (time zero). 2) Make a record of the pressure differential indications at

 10 second intervals for 120 seconds of time.
 S 862-015
 (2)  
Depressurize the airplane and restore it to its unpressurized condition (AMM 05-51-91/201).

 (3)  
Remove pneumatic pressure (AMM 36-05-00/201).

 S 862-016
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A 737-300/400/500MAINTENANCE MANUAL
 S 082-017
 (4)  
Remove the nose and main landing gear safety locks
 (AMM 32-00-01/201).

 S 412-028

 (5)  
Reconnect the electrical connectors D494 and D500 to the left and right turbofan valves, respectively.

 E. Performance Summary
 S 782-018
 (1)  
Best performance of the air conditioning packs and airplane structure is as follows: ~................................................................. | SYSTEM | BEST PERFORMANCE | ................................................................... |Single Pack - Low Flow Mode |Able to maintain or increase cabin| | |differential at 4.0 PSID and cabin| | |rate of change of 0 or negative | | |value (cabin pressurizing). | ................................................................... |Single Pack - High Flow Mode |Able to maintain or increase cabin| | |differential at 4.0 PSID and cabin| | |rate of change of -500 feet/minute| | |or greater (cabin pressurizing). | ................................................................... |Cabin Leakage Rate |Greater than 100 seconds required | | |for cabin bleed down to occur. | 2..............................…..................................1

 S 782-019

 (2)  
If the test data agrees with the best performance data for the packs (inflow) and the airplane structure (outflow), you can be very sure that cabin pressure can be maintained at cruise (FL250) on a single pack.

 S 782-020

 (3)  
Compare the data that you recorded on Figure 202 with the listed best performance data to find the condition of the packs and the airplane.

 S 812-021

 (4)  
If the test data does not agree with the best performance data for the packs and the airplane structure, refer to AMM 21-00-05/101 for trouble analysis and steps to correct the problems.

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