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R  **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
 D. Operation if there is a Failure
 (1) Failure in the active CPCS If the Built-In Test Equipment (BITE) detects a failure, the status changes automatically to standby and the other system takes over the control. Minor failures which are stored in the class 3 memory, do not lead to a system failure. The CPC sends a signal to the EIS and on the ECAM upper display unit the related warning appears. The CPC also keeps the failure data in its memory which can be indicated on the MCDU.
 (2) Failure in the standby CPCS If the BITE detects a failure, the system stays in standby-fail. Minor failures which are stored in the class 3 memory, do not lead to a system failure. The CPC sends a signal to EIS and on the ECAM upper display unit the related warning appears. The CPC also keeps the failure data in its memory which can be indicated on the MCDU.
 (3) Failure in both CPCS If in both CPCS systems failures appear, the crew must control the cabin pressure manually. The CPCs send a signal to EIS and on the ECAM upper display unit the related warning appears. The CPCs also keep the failure data in its memory which can be indicated on the MCDU. 
R  **ON A/C 106-149, 303-399, 401-499, 
R  D. Operation if there is a Failure 
R R R R R R R R  (1) Failure in the active CPCS If the Built-In Test Equipment (BITE) detects a failure, the status changes automatically to standby and the other system takes over the control. Minor failures which are stored in the class 3 memory, do not lead to a system failure. The CPC sends a signal to the EIS and on the ECAM upper display unit the related warning appears. The CPC also keeps the failure data in its memory which can be indicated on the MCDU.

 

R R R R R R R  (2) Failure in the standby CPCS If the BITE detects a failure, the system stays in standby-fail. Minor failures which are stored in the class 3 memory, do not lead to a system failure. The CPC sends a signal to EIS and on the ECAM upper display unit the related warning appears. The CPC also keeps the failure data in its memory which can be indicated on the MCDU. 
R R R R R R R R R R R R R R  (3) Failure in both CPCS If in both CPCS systems failures appear, the crew must control the cabin pressure manually. The CPCs send a signal to EIS and on the ECAM upper display unit the related warning appears. The CPCs also keep the failure data in its memory which can be indicated on the MCDU. If the crew cannot control the cabin pressure manually, the RPCU will open the outflow valve automatically under these conditions: - The outflow valve is not fully open - Both landing gears are on ground or one landing gear is on ground and the park brake is applied - All engine master lever switches are in the OFF position or all air data units show speed below 100 knots - The two CPCs are in standby fail or on manual mode. 
R  **ON A/C ALL
 E. Control and Indicating (Ref. Fig. 019)
 (1) LDG ELEV Selector - AUTO and Pushed The CPCs use the landing elevation and the QNH data from FMGS, - Pulled and Turned The data from FMGS is not used, the crew must select the landing-field elevation manually. The control range is from -2000 to 14000ft. 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
 (2) MODE SEL Pushbutton Switch - AUTO The automatic mode of the active CPC operates the outflow valve and supplies data for indication on the EIS. - MAN When the MODE SEL pushbutton switch is released (the MAN legend comes on), the manual operation is active.

 

 CABIN PRESS - Panel 25VU Figure 019
 1EFF : 1 1R 1CES  ALL  1 11 1 21-31-00 Page 52 Aug 01/05

 

 -FAULT The FAULT legend comes on if both automatic systems are defective. When the pushbutton switch is released (the MAN legend comes on and the FAULT legend goes off) the manual control is then operative with the toggle switch to control outflow valve position.
 -For CPC P/N 20791 only: Push and release the MAN pushbutton switch to switch the active auto system in stand-by and the stand-by auto system takes over control.
 (3)
 V/S CTL Toggle Switch The switch, spring loaded to neutral,controls the outflow valve with the manual motor, when the MODE SEL pushbutton switch is in the MAN position.

 -UP : The outflow valve move towards the open position,
 -DN : The outflow valve move towards the closed position.

 (4)
 DITCHING pushbutton switch (guarded black)

 -Normal released Position
 Normal system operation.

 -ON When the pushbutton switch 13HL is pushed (the ON legend comes on) and the aircraft goes into the ditching configuration. This closes: .the outflow valve 10HL, .the packs flow control valves 11HB (8HB), .the avionics skin air inlet valve 15HQ, if open, .the avionics skin air outlet valve 22HQ, if open, .the emergency ram-air inlet, if open, .the fwd cargo isolation valves 4HN (5HN), if installed.
　
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