STUDENT GUIDE FOR T-1A AIRCRAFT SYSTEMS
16. Recall the systems associated with the stall warning system.
17. Recall the location and function of the AOA vanes.
18. Recall the location of the AOA indicator.
19. Discuss the significance of the AOA indicator.
20. Describe the function of the AOA indexer.
1003. PITOT STATIC SYSTEM
The pitot static system provides the source for operating the aircraft's differential pressure
instruments. It consists of two independent pitot and static systems; the left pitot static system is
connected to the P's air data system; the right pitot static system is connected to the CPs air data
system, the standby airspeed indicator, and standby altimeter.
The pitot system provides ram air pressure to both Air Data Computers (ADC) and the standby
altimeter and standby airspeed indicators. The pitot system consists of a pitot tube installed on a
mast located on each forward lower side of the fuselage, a drainage valve, aluminum alloy
tubing, a pitot tube heating element, a pitot mast heating element, and fittings. The left (P) pitot
tube is connected to the P's ADC. The right (CP) pitot tube is connected to the CP's ADC and
the standby airspeed indicator.
1004. STATIC SYSTEM
The static system provides ambient air pressure to both ADCs, the standby altimeter, and
airspeed indicator. The static system consists of a pair of static ports located on each side of the
1005. STANDBY INSTRUMENTS
The standby instruments include the airspeed indicator, altimeter, attitude indicator, and
magnetic compass. These instruments provide backup indications in the event of failure of the
integrated flight instrument system.
Standby Airspeed Indicator
The standby airspeed indicator, located on the center instrument panel, is operated by pitot and
static pressures direct from the CP's pitot static system.
The standby altimeter, located on the instrument panel, is an internally lighted pneumatic
instrument, operating on static system pressure from the CP's static system.