Main Panel Layout




Detailed Description

Automatic Pitch Control (APC) Gauge



The APC gauge reads from 0 to 5 and displays a combination of Angle-Of-Attack (AOA) and Pitch Rate information to the pilot.  The CF-104 is prone to pitch-up at high AOA and pitch rate so an automatic pitch control system was developed to provide some warnings to the pilot when ever the aircraft is approaching dangerous flight conditions.  A stick-shaker will shake the stick to alert the pilot that he is approaching a high AOA.  As the AOA reaches a dangerous level, a stick-kicker will activate and apply forward pressure on the stick.  The kicker will activate as the APC gauge displays a reading of 5.  If the pilot continues to pull back on the stick beyond this value, pitch-up is imminent.

The APC reading relates to AOA in this manner.  When the APC is reading a value of zero, the AOA can be between 0 and 3 degrees.  A value of 5 corresponds to approximately 13 degrees AOA.  The pitch-up angle of attack is around 16 degrees.  Needless to say, the APC gauge should be monitored during slow flight and agressive maneuvering.  During landing, it is essential as well to keep the AOA with safe limits.  A value of 3 on the APC during landing is typical.  The stick shaker in the simulator is modeled as a chattering sound that is played.  You will hear this often.  During dogfights, it is common practice to turn hard until the stick shaker activates.


Compressor Inlet Temperature Gauge and Warning Light



The Compressor Inlet Temperature Gauge monitors engine inlet temperature.  Top speeds of the CF-104 are extremely high and the aircraft will accelerate beyond M 2.3 unless the engine is throttled back.  At high speeds, the inlet temperature can get very high.  Beyond.100 deg C, the warning light marked SLOW will begin to flash as a warning that the inlet temperature is getting too hot.  Prolonged flight at high inlet temperatures can cause serious damage to the engine.  In flight tests and speed record attempts, M 2.3 was regularly achieved for short time periods with no damaging effects on the engine.  At higher altitudes and colder temperatures, the aircraft may be flown at higher Mach numbers and lower inlet temperatures.


G Meter



The G Meter reads current G load, minimum G load, and maximum G load.  The button on the bottom left of the gauge may be used to reset the maximum and minimum values back to 1.


UHF Radio Channel Selector



Nineteen preset UHF channels and one Guard channel may be defined for UHF voice radio.  UHF radio is inoperative in this simulation.


Combined Mach /  Indicated Airpseed Indicator



The airspeed indicator combines both Mach number reading and indicated airspeed reading in knots.  Indicated airspeed does not read below 60 knots.  There is also a rotating drum in the top part of the gauge that displays the "tens" value of the airspeed reading to provide a more precise indication.  Along the top of the gauge is a rotating dial that displays indicated Mach number up to M 2.2.  The push button is inactive in the simulator.


Altimeter



The altimeter has one needle which reads the altitude in hundreds of feet.  The digits in the middle read hundreds, thousands, and ten-thousands.  The knob on the bottom left is used to adjust barometric pressure.


Attitude Indicator



The Attitude Indicator displays several pieces of data.  Power to the attitude indicator is received from the Inertial Navigation System (INS).   The INS is on the right side panel.  The INS mode switch must be turned on in order for the Attitude Indicator to receive power.   The INS detects magnetic heading and sends this data to the attitude indicator which displays heading along the horizon line of the ball.  See the Aircraft Systems - Navigation System section  in the manual for more information on the INS.  Besides heading information, the ball also displays pitch angle and roll attitude.

 The bottom of the AI incorporates a needle and ball to display yaw information.  

On the left side of the gauge is a vertical tape display.  The difference between actual ground speed as determined by the INS and desired ground speed as entered on the desired ground speed indicator, to the right of the radar, is displayed on this vertical tape.  An arrow will appear on the tape when the two values are within +/- 9 knots.

The knob on the bottom right of the AI will tilt the ball so can be adjust as different aircraft attitudes as desired by the pilot to show level flight.


Position and Homing Indicator (PHI)



See the Aircraft Systems - Navigation Systems section in the manual for information on this gauge.