(b)
When the system is stable, stop the pressure and vacuum sources.
(c)
Make a note of the airspeed and altitude to the nearest 1 knot and 20 foot increments.
(d)
Make sure the leakage rate is not larger then 5 knots or 400 feet per minute.
S 825-066
(5) Decrease the static pressure to the ambient pressure.
NOTE:____Change the pressures at a slow rate. Make sure the pitot pressure is equal to or larger than the static pressure.
S 435-067
(6)
Connect the differential pressure indicator for the cabin altitude.
(7)
Do the test for the cabin differential-pressure indicator.
S 705-068
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S 865-087
(8) Connect the cabin altitude differential indicator to the No. 1 auxiliary static system.
CAUTION: KEEP THE RATE OF ALTITUDE CHANGE TO LESS THAN 300 FEET PER
_______ MINUTE. IF THE RATE OF CHANGE IS LARGER THEN 300 FEET PER MINUTE, YOU WILL DAMAGE EQUIPMENT.
(a)
Get the local barometric pressure (inches Hg).
(b)
Subtract 4.07 in. Hg. from the local barometric pressure.
1) Apply the result to the No. 1 auxiliary static system as absolute pressure.
(c)
Make sure the differential pressure indicator is 2.0 |0.2 psi.
NOTE: Hit the indicator lightly on the case, not the glass
____ dial cover, before you read the value.
(d)
Subtract 10.18 inches of Hg from the local barometric pressure.
1) Apply the result to the No. 1 auxiliary static system in absolute pressure.
(e)
Make sure the differential pressure indicator is 5.0 |0.2 psi.
NOTE: Hit the indicator lightly on the case, not the glass
____ dial cover, before you read the value.
G. Put the Airplane Back to Its Usual Condition
S 865-069
(1)
Remove the pressure on the pitot static lines.
S 845-070
(2)
Disconnect the test equipment.
S 085-071
(3)
Remove the seals from the airplane's static lines.
NOTE: Make sure there are no unwanted materials in or around the
____
static ports.
S 865-072
(4)
Open the NO. 1 AIR DATA COMPUTER-1 and TEMP PROBE circuit breakers on the load control panel, P18.
S 865-073
(5)
Open the NO. 2 AIR DATA COMPUTER-2 circuit breakers on the load control panel, P6.
(6)
Disconnect the decade resistance box from connector D277.
S 865-074
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(7) S 865-075Connect D277 to the TAT probe.
(8) S 865-076Close the circuit breakers for the air data systems on the load control panels, P6 and P18.
(9) S 865-077Open these circuit breakers on the load control panel, P18: CAPTAIN'S UPPER L F/O LWR L ELEVATOR PITOT L ALPHA VANE HTR L
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