E55 Baron (Early) Systems
This document describes the systems on Baron N3622A.
Overview
- N3622A
- Serial TE-777
- Model: E55
- Year: 1969
- Max takeoff weight: 5300 lb
- Max landing weight: 5300 lb
- The following sections cover all the systems as described in CFI ACS Part II Task E. Aircraft Flight Controls and Operation of Systems
Primary Flight Controls
- Electric trim on pitch axis only
- There seems not to be a separate breaker for pitch trim servo
Secondary Flight Controls
- Flaps
- Electrically actuated
- Positions
- 15° (Approach)
- 30° (Full)
- The switch must be pulled out of a detent to change the flap position
- Slotted type
- See POH page 7-7
- Note: on earlier serials, the flaps had a weird method of operation that allowed selection of flap angles between 15° and 30°, but N3622A does not; the flaps will move to the position selected on the flap handle.
Powerplant and Propellers
- Engine Overview (CHAND)
- C - Continental IO-520-C
- Fuel injected
- Six-cylinder
- Rated at 285 horsepower at 2700 rpm
- H - Horizontally opposed
- A - Air cooled
- N - Naturally aspirated
- D - Direct-drive
- C - Continental IO-520-C
- Engine lubrication and cooling
- 12 quart oil capacity (page 7-25)
- No published minimum oil, Company policy is 9
- Has thermostat to control flow through oil coolers
- Oil type is SAE 50 (above 40 °C) or SAE 30 (below 40 °C)
- Cowl flaps manually actuated
- Induction System
- N3622A induction system draws air through the ram inlets and draws it through a filter
- Some Barons have an induction selector that allows for selection of filtered or unfiltered ram air
- Propeller system
- 2-bladed
- McCauley
- P/N: 2AF34C55
- 78 inch diameter
- Variable pitch
- Constant speed
- Full-feathering
- Forces moving prop to feather (high pitch)
- Springs
- Counterweights
- Air charge
- Engine oil under governor-boosted pressure moves the blades to low pitch
- Has unfeathering accumulators
- Gas-assisted pressure to drive oil back into the propeller dome to get the propeller on a stopped engine (that isn't producing oil pressure) out of feather
- Unfeathering accumulator like a balloon, when oil pump is going its blowing up the balloon
- Feather is pinching the balloon closed
- In prop big spring with nitrogen charge inside to push oil out
- Counterweights on prop to drive prop to feather
- POH page 1-12, 7-26
- 2-bladed
Landing Gear
- Electrically actuated
- Squat switch on left main
- See https://www.csobeech.com/gear-rod.html for lots of gear mechanism pictures
- Gear
- All three down and locked all three switches in series = one green light
- All three up switches in series = one red light
- Light bulbs you can rotate to dim for night
- Gear extended closes the squat switch
- Gear has warning horn
- Hear it on short final, no hesitation -- go around immediately
- Nose gear has springs between rudder pedals and turning mechanism
Fuel, Oil, and Hydraulic
Fuel System
- Fuel capacity 142 gallons total, 136 gallons usable
- Mains 40 gallons total, 37 gallons usable
- Aux 31 gallons total (all usable)
- 4 sumps per side
- Main, aux, 1 for base of fuel line, 1 for strainer
- Fuel returns back to the tank that is selected
- Float type fuel sensors
Oil System
- See above with powerplant
Brakes (Hydraulic)
- Do not leave the parking brake set when the plane is unattended
Electrical
- 24 volt electrical system
- Two 12 volt batteries connected in series
- Two 50-amp 28-volt gear driven alternators
- There is a two-position voltage regulator switch
- Doesn't matter which voltage regulator is used
- In case of voltage drop, can try the other regulator
- See POH page 7-31
- Load meters
- Measure load on alternators
- Compare with ammeters which show how much the battery is being charged or discharged
Avionics
- GNS 530W - com 1
- GNS 430 (no waas) - com 2
- GFC600 Autopilot
- 2-axis - pitch and roll
- GMC 605 mode controller
- GI 285 annunciator panel
- With Control Wheel Steering (CWS)
- After the autopilot test, two presses to kill the autopilot and on the third press hold it down until you see ESP OFF (Electronic Stability Protection)
- Note: "If the AP DISC / TRIM INT button is held down for 5 seconds or more, ESP will be disabled. ESP will be re-enabled when either of the AP or FD keys are selected on or power is cycled on the GMC 605."
- Has internal AHRS
- PM2000 Intercom
- Garmin GTX 330ES Transponder
Pitot Static, Vacuum/Pressure, and Associated Instruments
- One pitot tube under left wing
- Two static ports on left and right aft fuselage
- No vacuum or pressure system or instruments
- Alternate static red lever left lever by pilot side left shin
Environmental
- Heater burns from left main
- 0.5 - 1 gph (find reference for that)
- 25 Amp hour, 12 V lead acid connected in series = 24 V system
- Controlled by two transisterized voltage regulators only one running at a time
- Regulates the voltage of both alternators
- Left to right
- In-out-in-out = opens everything
- Heater switch: on, off, blower
- At altitude never need to use blower
- Blower only comes on when gear handle is down
- There is an overheat switch
Deicing and anti-icing
- Glycol on prop and windscreen
- Not FIKI certified so really shouldn't be using it
- POH page 7-46 for fluid-flow endurance
- Windshield: 36 minutes
- Props: 120 min
- Both: 28 minutes
Oxygen System
- No oxygen system in N3622A