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1972 Piper PA28R 200 Arrow – Equ

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1972 Piper PA28R 200 Arrow – Equ Powered By Docstoc
					                        Piper PA28R-200 Arrow – Systems Summary

[1] Landing Gear

    •    Hydraulically operated, fully retractable, tricycle landing gear
    •    Reversible (actuated in one direction – raises gear; actuated in other direction – lowers gear) electrically
         powered pump
    •    Lights: 3 green lights on indicates down and locked; all lights out indicate retracted; yellow “in transit”
         light on the panel; red “gear unsafe” light on the panel
              o Caution: lights dim substantially when navigation lights are on; this renders them invisible in
                   most daylight conditions
    •    Retraction speed: ≤ 125mph; extension speed: ≤ 150mph
    •    Nosewheel steering linkage disengages after retraction to reduce rudder pedal load
    •    Nose steerable through 30 degree arc; equipped with shimmy dampener
    •    Oleo strut extensions: 2.75” ± 0.25” nose, 2.00” ± 0.25” main under empty weight and full fuel/oil)
    •    Numbers
              o Extension/retraction time: 7 seconds
              o Tire size: 5.00 x 5 nose, 6.00 x 6 mains (all tires four-ply with tubes)
              o Tire pressure: 30 psi nose, 27 psi mains
    •    Emergency extension
              o Extension speed: 100mph or below
              o Hold the emergency gear lever switch in the down position
              o Extension is accomplished by manually releasing hydraulic pressure; gear free-falls; nose gear is
                   assisted in free-fall/lock by a spring
              o If gear does not indicate down and locked, yaw the airplane side to side
    •    Auto extender system
              o Extension speed: 85mph to 105mph, depending on power/altitude
              o Operates on a sensing device controlled by differential air pressure
              o High pressure source and static source are mounted on left side of the fuselage above the wing;
                   this mast is heated when Pitot Heat is turned on
              o Override
                         Raise the emergency gear lever to the up position and latch in
                         Should be overridden for: maximum glide, short field takeoffs, and practice stalls with
                             gear up
                         Override condition indicated by flashing yellow light below gear handle
    •    Warning system: activated by micro-switches in the throttle quadrant
              o Steady sound; red “gear unsafe” light
              o Activated under the following conditions:
                         Gear up and power below approx. 14” MP
                         When the auto extender system extends the gear and the gear handle is in the raised
                             position
                         Gear handle in the raised position when on the ground
    •    Squat switch on the right main gear prevents gear retraction while on the ground

[2] Brakes

    •    Brake pedals on the pilot’s side only
    •    Individual cylinders for toe brakes and the hand brake; shared brake reservoir
    •    Separate controls for brakes for left and right main gears
    •    Single disc, single puck brakes on the main gears



1972 PA28R-200 Arrow Systems                    tangojulietaviation.com                                      Page 1 of 3
    •      Brake fluid reservoir located in the upper left corner of the front side of the firewall; fill with MIL-H-5606
           hydraulic brake fluid (red)

[3] Engine, Oil, and Induction

    •      Engine type: horizontally opposed, air-cooled, direct drive, fuel injected; type Lycoming IO-360-C1C
    •      Engine TBO: 2,000 hours
    •      Maximum 200 brake horsepower at 2,700 rpm; max recommended cruise is 75%
    •      Oil cooler installed; air inlet for oil cooler is on the right side of the cowling; air exhaust is next to the main
           engine exhaust
    •      Oil capacity: 8 quarts
    •      Bendix RSA-5AD1 fuel injector
                o Operates on differential pressure
                o Fuel pressure regulated by a servo valve
                o Fuel flow divider receives metered fuel and distributes it to each cylinder
                o Fuel flow instrument connected to the flow divider
    •      Alternate induction air door opens automatically when the primary air source is obstructed; this can be
           tested from the cabin during run-up

[4] Propeller

    •      Hartzell two blade constant-speed, controllable-pitch propeller
    •      Propeller governor relies on oil pressure: when RPM is decreased, the oil from the engine enters the
           propeller dome, thus moving the piston and a sliding arm to cause the propeller to take a bigger bite of air
           (consequently, a drop in oil pressure is observed)
    •      Loss of engine oil will cause propeller overspeed

[5] Fuel

    •      Two 25 gal. tanks; usable capacity in each tank is 24 gal. (total of 48 gal. usable fuel)
    •      Engine driven fuel pump; auxiliary electric pump used for priming and when the engine driven pump fails
    •      Three fuel drains: one for each tank and one for the fuel strainer (on left side of firewall)
    •      Fuel tanks are individually vented
    •      Gauges: individual fuel level gauges for each tank; a single fuel pressure gauge connected to the induction
           system

[6] Electrical

    •      Alternator: quantity – one; 12-volt, 60-amp
               o Incorporates a voltage regulator and an overvoltage relay; alternator will go offline at 16.5 volts
                    output and up
               o Full power output even at low engine RPM
    •      Battery: quantity – one; 12-volt, 25-amp hour
               o Located behind the baggage compartment
               o Acid overflow vents below the compartment
    •      Ammeter shows total electrical load placed on the system
    •      Circuit breakers protect major electrical accessories
    •      Piper External Power plug located on the right side of the fuselage behind the wing
    •      Loss of alternator indicated by zero reading on the ammeter; there is no alternator warning light on N5250T

[7] Vacuum



1972 PA28R-200 Arrow Systems                        tangojulietaviation.com                                         Page 2 of 3
    •    Operates attitude indicator and directional gyro
    •    Single dry-type vacuum pump; shear drive protects the pump from damage
    •    Vacuum gauge mounted on the instrument panel; normal reading is 5.0 ± 0.1 in. Hg, but may read lower at
         very high altitudes (above 12,000 feet)
    •    Vacuum regulator located behind instrument panel protects the gyro instruments
    •    Up to 2000 rpm may be required to obtain full vacuum pump suction

[8] Environmental

    •    Three cabin air inlets – one on each wing and one in the horizontal stabilizer
    •    Major heating components: heat shroud, heat ducts, defroster outlets, heating and defrosting controls
    •    Opening in front of lower cowl admits ram air into heater shroud; air is ducted into heater shutoffs on the
         right and left side of the firewall
    •    Overhead and floor mounted fresh air vents
    •    Cabin air exhaust through an outlet at the bottom of the fuselage aids in air distribution

[9] Pitot-Static

    •    Pitot-static mast located on the left wing; incorporates a pitot tube hole (front of the mast), a pitot drain
         hole (bottom of the mast), and a static port (rear of the mast)
    •    Separate high-pressure and static sources for the automatic gear extender located on the left side of the
         fuselage above the wing
    •    Pitot heat provides heating for the pitot-static mast and the high pressure/static source for the automatic
         gear extender

[10] Major Avionics Components & Flight Controls

    •    Vacuum-driven directional gyro and attitude indicator
    •    Electric turn and bank indicator (not a turn coordinator) – does not display the rate of roll
    •    Airspeed indicator, altimeter, and vertical speed indicator driven by pitot-static system
             o Alternate static source switch located below the pilot’s control wheel
    •    Electric pitch trim; disengaged by a rocker switch below the pilot’s control wheel
    •    Piper Autocontrol III autopilot
             o To turn off, push the ON/OFF switch on the autopilot or turn the master off
             o Autopilot must be off for takeoff and landing
             o Autopilot use prohibited above 200mph CAS

[11] Emergency Locator Transmitter

    •    Located in the tailcone
    •    Access is via a panel on the right side of the fuselage




1972 PA28R-200 Arrow Systems                     tangojulietaviation.com                                         Page 3 of 3

				
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