CESSNA®
MODEL 525B
MAINTENANCE MANUAL
F.
On Airplanes -0057 and -0665 and On, the EFD-750 Electronic Flight Display (EFD) uses static and
pitot air pressure inputs to provide a display of attitude, altitude, and airspeed.
3.
Operation
A.
The static systems are three separate systems that are divided between the pilot, the copilot and the
standby systems. The pilot static system has two static ports (left lower and right upper), plumbing
and an ADC. The copilot static system has two static ports (left upper and right lower), plumbing
and an ADC. There are three static ports found on each side of the fuselage that are pneumatically
connected to an opposite set on the other side of the airplane in order to reduce location difference.
B.
The left and right pitot system supply ram air pressure for the left and right ADCs. The left and
right static systems supply static air pressure to the left and right ADC. The left ADC functions as
a processor for the inputs from the left pitot and static source and supplies altitude, airspeed, and
vertical speed information to the pilot PFD. The right ADC functions as a processor for the inputs
from the pitot and static source and supplies altitude, airspeed, and vertical speed information to the
co-pilot PFD.
C.
The standby system components include the aft right pitot probe, the static ports, plumbing and the
ESI-1000 Electronic Standby Indicator or EFD-750 Electronic Flight Display airspeed and altitude
display. The standby pitot and static system supplies ram air pressure and static air pressure to the
ESI-1000 or EFD-750.
D.
Each of the pitot probes and static ports are electrically heated to prevent ice from forming. The
heaters are operated by turning on the PITOT STATIC HEAT 1 and 2 switches, found on the right
switch panel.
(1)
The pilot and standby pitot-static heat circuits are operated by putting the PITOT STATIC HEAT
1 to the ON position. The copilot pitot-static and AOA heat circuits are operated by putting the
PITOT STATIC HEAT 2 to the ON position.
E.
The Garmin GDC 7400 ADC system measures aircraft static and impact pressure data from pressure
transducers and raw air temperature from an outside temperature probe.
The ADCs compute
pressure altitude, vertical speed, airspeed values, air temperature information, and density altitude.
Aircraft specific configuration parameters are stored internally. The system gives pitot-static data to
the Garmin G3000 Integrated Avionics System through the interfaces that follow:
•
ARINC 429 output to the attitude heading and reference system (AHRS)
•
ARINC 429 output to third party ARINC 429 Devices
•
Two ARINC 429 outputs to the PFDs and the integrated avionics units (IAU).
•
Four ARINC 429 inputs from external sensors
•
RS-232 Interface with IAUs
•
Two Aircraft Power Inputs
•
Temperature Probe Interface for GTP 59 or other supported probe.
F.
The ADC 1 receives electrical power from the avionics bus through the ADC 1 circuit breaker on the
right circuit breaker panel in the cockpit. The ADC 2 receives electrical power from the emergency
bus through the ADC 2 circuit breaker on the right circuit breaker panel in the cockpit.
34-11-00
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© TEXTRON AVIATION INC.
Feb 23/2022
ICA-525B-34-00004
Form 2261 Rev 1
