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L77287
A
747-400 MAINTENANCE MANUAL
4
3.5
DIFFERENTIAL PRESSURE - PSI
3
2.5
2
1.5
0 60 120 180 300 360 420 480
TIME - SEC
747-400 COMBI (4 PSI LEAKDOWN)
Cabin Pressure Leakage Rate Chart
Figure 202 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
L77286
A
747-400
MAINTENANCE MANUAL
(2)
Stopwatch
(3)
External ground air source providing a continuous flow of 2500 cfm at a pressure of 10 psig.
C. References
(1)
AMM 21-00-00/201, Air Conditioning
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 34-11-00/501, Pitot-Static System
(4)
AMM 34-13-01/401, Standby Airspeed Indicator
(5)
AMM 34-13-02/401, Standby Altimeter
(6)
AMM 35-11-00/001, Crew Oxygen System
(7)
AMM 35-21-04/401, Unit - Continuous Flow Control
(8)
AMM 49-11-00/201, Auxiliary Power Unit
D. Prepare for the Cabin Pressure Leakage Test
NOTE: The pitot-static system must be complete when you do the test
____
procedure.
S 792-033
(1)
Make sure the pitot-static system does not have leaks
(AMM 34-11-00/501).
S 482-002
(2)
Use the EICAS System during the Cabin Pressure Leakage Test to monitor the cabin pressure.
NOTE: An independent ASI instrument can also be used to measure
____ the pressure differential. The ASI on the pilots' console can be used when no other ASI is available.
(a)
When an independent ASI is used: 1) Put the ASI in an applicable location. 2) Connect the ASI static pressure inlet to the airplane
static pressure line.
(b)
When the pilots' ASI is used:
1) Remove the standby airspeed indicator from the pilots instrument panel (AMM 34-13-01/401).
NOTE: Disconnect only the pitot pressure hose from
____ the standby ASI at the quick-disconnect.
S 862-003
(3)
Supply electrical power (AMM 24-22-00/201).
S 862-004
(4)
Move the EQUIP COOLING selector on the cabin temperature control module, on the panel P5, to the STBY position.
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747-400 MAINTENANCE MANUAL
S 792-005
(5) Make sure the pitot-static systems is installed and does not leak (AMM 34-11-00/501).
NOTE: Do not do the pressure leakage test on an airplane
____ which has not been tested for pitot-static systems leaks.
S 022-034
(6) If the pressure will exceed 20 PSI absolute, you must remove the oxygen equipment that follows:
(a)
The crew oxygen diluter demand masks.
(b)
The passenger oxygen continuous flow control units.
S 862-035
(7) To close the section 41, forward overboard valve, do the steps that follow:
(a)
Gain access to the section 41, left lower lobe, via the forward EE bay hatch.
(b)
Remove the electrical connector from the forward overboard valve.
(c)
Move the red valve selector handle to the closed position.
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