For anyone: How in depth was your oral exam? I have put together an excruciatingly detailed guide for the Seneca for my ride (mil thing didn't work out). I'm just wondering how much is too much.
It follows the PTS, for you smart-aleck's out there.
Here's an example of a piece of the outline:
1. Airplane Systems and Components
a. Landing Gear
i. Normal Extension and Retraction
- VLE 150mph, VLO 125mph
- Electrically powered reversible hydraulic boost pump in the nose
- Pump holds 1800 psi (+/- 100 psi) in the system to keep gear up
- System pressure can lag to 1700 psi before the pump cycles.
- System is reversible via shuttle valve for extension / retraction
- Full extension / retraction takes about 6-8 seconds
- With gear down and locked electrical limit switches stop current flow to pump.
ii. Emergency Extension and Retraction
- Emergency Gear Extension Speed: 100mph
- Accomplished via pressure-dump valve near center of the instrument panel
- Gear falls by gravity to down and locked position
- Aerodynamic loading and overextension-springs help lock gear
iii. Landing Gear Lights
- Contact switches (limit switches) engage at full extension
- Illuminate green landing gear switches in cockpit
- Convex mirror aides in visual indication of gear down (Three Green, One in the mirror)
- Lights are removable and interchangeable.
1. IF GEAR LIGHTs DO NOT ILLUMINATE
a. The gear is not down and locked fully
b. The bulb is burned out
c. There is a malfunction in the indication system
NOTE: Gear lights are tied to the NAV LIGHT SWITCH for pilot comfort at night.
Check to ensure NAV LIGHT Switch is OFF before initializing emergency gear extension actions.
iv. Landing Gear Tires
- Nose Gear tire: 6 ply, 6.00-6, @ 31 PSI
- Nose gear is steerable up to 42° via rudder pedals
- Bungee assembly reduces ground steering effort and dampens shocks/bumps.
- When gear is retracted, the steering mechanism is disengaged and straightened via centering spring.
- Main Tires: 8 ply, 6.00-6 @ 50 psi
v. Landing Gear Warning Horn
- Activated via micro switch in the throttle quadrant under any of the following conditions:
- Gear is up and manifold pressure is below 14” on one or both engines.
- Gear Selector is in the UP position when the aircraft is on the ground.
NOTE: To prevent inadvertent gear retraction on the ground, the Seneca I has a pressure switch (squat switch) on the left main landing gear that will not allow the pump motor to operate unless at least 8” of exposed chrome is present on the oleo strut.
vi. Brakes
- Single-disc double puck assembly on each main gear struts.
- Main brakes are actuated by toe-brakes on the rudder pedals.
- Braking is accomplished hydraulically via a reservoir.
- Reservoir is independent of the landing gear extension / retraction system.
- Located behind the panel and rear-top of the nose compartment.
- Parking brake is actuated by the pulling the handle and pushing on the lock button.
- Parking brake uses handle-operated brake cylinder on the reservoir.
- Reservoir level should be maintained to the line.
vii. Shock Absorption
- Accomplished via air/oil struts (Oleo Struts)
- Consists of an inner metal tube or piston attached to wheel and outer metal tube attached to airframe.
- Sealed with O-rings or elastomeric seals to prevent contamination.
- Cavity is filled with nitrogen or dry compressed air and hydraulic oil.
- Divided into two chambers that communicate through a small orifice
- When the aircraft is on the ground, the nitrogen/gas supports the weight
- During landing /taxiing the pistons slide up and down which compresses the gas
- Gas acts as a spring and forces oil through orifice which acts as a damper
- A tapered rod / check valve can change the orifice size so that dampening during hard compressions (hard landings) is less than on a rebound (ballooning).