Section 7
Description of the Airplane and Systems
Columbia 400 (LC41-550FG)
RC050002
Initial Issue of Manual: November 10, 2004
7-138
Latest Revision Level/Date: A/12-01-2004
manifold, a display controller, and associated lines, fittings, valves, and sensors. The oxygen
bottles are located in the right hand wing locker between WS 25.0 and WS 46.0 wing rib, and
between the forward and aft spars. The total oxygen capacity of the system is 42 cu. ft (1189 L).
The maximum oxygen cylinder pressure is 2000 psi. The low pressure operating pressure is 20 to
33 psi. The bottles are interconnected by bottle fittings and the high-pressure stainless steel lines
to the high-pressure manifold of the regulator valve assembly mounted to the inboard side of the
root rib. Also attached to this high-pressure manifold are the stainless steel lines connected to the
filler port located in the baggage compartment and to the remote overpressure burst assembly
located in the belly of the wing. The regulator/valve assembly includes a regulator to reduce the
bottle pressure to the low-pressure manifold for distribution. This assembly also includes a valve,
on the low-pressure side, that is activated by a latching solenoid to turn on and off the flow of
oxygen to the cabin distribution (low pressure) manifold. The low-pressure lines are then routed
into the cabin area, behind the interior, to a manual valve, and then to the low-pressure
distribution manifold where the dispensing systems are attached to deliver the supplemental
oxygen to the pilot and passengers. Attached to both the high pressure manifold and the low-
pressure distribution manifold are electronic pressure transducers to measure the oxygen pressure
at the respective locations. These values are sent to the display/logic controller located in the
instrument panel. Also connected to the controller is the solenoid wiring, annunciator light
wiring, and the aircraft power to supply power to the system. The annunciator light provides
warning information to the pilot.
Oxygen is required to be used by the pilot above 12,500 ft for flight time exceeding 30 minutes
and above 14,000 ft for the duration of the flight above 14,000 ft. If climbing to an altitude
where oxygen will be required, it is recommended that at approximately 10,000 ft, the pilot
should begin using the oxygen. Passengers are required to be supplied with oxygen above 15,000
ft.
Oxygen Flow Controls –
Four manually operated oxygen flow controls can be connected to the
oxygen distribution manifold. The flow controls are calibrated and adjustable for altitude by the
user. The following flow controls can be one of the following:
•
A4 Flowmeters and Oxygen Conserving Cannulas – Up to 18,000 ft
•
A4 Flowmeters and Masks (Standard and Microphone) – Up to 25,000 ft.
The flow controls provide the means to distribute the appropriate amount of oxygen for the
pressure altitude of flight and indicate the presence of flowing oxygen to the pilot or
passenger(s). The flowmeter or flow indicator and the oxygen quantity gauge should be checked
periodically (approximately every 10 minutes). The flow control should be reset with each
change in pressure altitude or as required by the user for physiological requirements.
Oxygen Display
–
The cockpit display (see Figure 7 - 54) located next to the lower instrument
panel next to the ECS panel allows the pilot to monitor the system performance and includes the
display and three-position master switch. The system three-position master switch on the display
can be positioned in the ON, OFF and DISP modes. The ON position engages the solenoid and
will display the High Pressure and Low Pressure values. The OFF position will disengage the
solenoid and there will be no display. The DISP mode is a quick check function that displays
only the High Pressure and Low Pressure values for preflight and filling operations. The DISP
mode is to be used to determine whether or not the bottles need to be refilled or for filling
purposes as this provides the fill level, or high-pressure reading. The fault light alerts the pilot to
a problem with the electrical connection to the regulator/valve assembly. For the fault light to be
extinguished the oxygen circuit breaker needs to be pulled and reset, or aircraft power reset if