Systems

Question 1

Electrical overview

Answer 1

Negative-ground, dual-fed, split bus. 14V
2 Alternators: belt driven 70amps. Control unit uses voltage regulator that maintains effective load sharing and regulates electrical sys to 14V. If alternator exceeds 17V circuit breaker pops.
Battery: 35amp, 12V lead-acid. Charged by alternators. Located at nose.

Question 2

Busses

Answer 2

6
Battery: Clock, Hobbs, tach meter, heater meter.
Avionics1: comm1, nav1, transponder, electric trim, audio panel
Avionics2: comm2, nav2, marker beacon
Nonessential bus: recog lights, standby lights, heater, vent fan, overhead blower
Main: everything else(fuel indicator, landing gear, pitot heat, pumps, starter)

Question 3

Vacuum

Answer 3

Air—>filter—>gyro—>manifold check valve+gauge—>regulator—>pump

Question 4

Landing gear

Answer 4

Hydraulically operated, fully retractable, tricycle landing gear.
Vlo(up): 109
Vlo(down): 140
Electrical, reversible hydraulic pump activated by gear selector apples hydraulic pressure on either side of gear piston to raise up or lower. When in position electric limit switches stop flow of current to hydr.pump.
Gear extension lock: springs lock gear into down position followed by hooks.

Question 5

LG—contingency

Answer 5

If gear is in neither Up/Down pos.->annunciation light.
Warning horn activated when flaps extended+low manifold pressure.
On ground: squat switch on left main gear will prevent hydraulic pump activation. When I’m air and oleo strut drops to full extension, switch closes to allow electrical flow for hydr. pump.
Hydr.Pump Failure: make sure gear in Down pos. pull E-gear extension knob.