Specifications

Information Manual 7-33
Cirrus Design Section 7
SR20 Airplane Description
The SN3308 detects and warns of abnormal conditions such as
flagged navigation receivers and failed directional gyro or flux detector.
It also monitors its own internal temperature and provides warnings for
over-temperature or loss of cooling conditions.
Redundant circuits paralleled through diodes at the indicator supply
DC electrical power for gyro operation. 28 VDC for the redundant
power circuits is supplied through the 5-amp HSI/PFD 1 circuit breaker
on the Essential Bus and 5-amp HSI/PFD 2 circuit breaker on Main
Bus 2.
Magnetic Compass
A conventional, internally lighted, liquid filled, magnetic compass is
installed on the cabin headliner immediately above the windshield. A
compass correction card is installed with the compass.
March 2010