Wiring Diagram for the Piper PA-28RT Arrow IV Turbo

A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal vacuum reads 4.8 to 5.1 inches of mercury, a setting which provides sufficient vacuum to operate all the gyros at their rated rpm. Higher settings will damage the gyros and with a low setting the gyros will be unreliable. The regulator is located behind the instrument panel. If equipped with the optional auxiliary vacuum system, refer to Section 9, Supplement 3, for operation procedures. 7.21 PITOT-STATIC SYSTEM The system supplies both pitot and static pressure for the airspeed indicator, altimeter and vertical speed indicator (when installed). Pitot pressure is picked up by the pitot head on the bottom of the left wing. An optional heated pitot head, which alleviates problems with icing or heavy rain, is available. The switch for pitot heat is located on the switch panel. Static pressure is sensed by button type vents on each side of the aft fuselage. Push-button type pitot and static drains are located on the lower left sidewall of the cockpit. An alternate static source is available as optional equipment. The control valve is located below the left side of the instrument panel. When the valve is set in the alternate position, the altimeter, vertical speed indicator and airspeed indicator will be using cabin air for static pressure. The storm window and cabin vents must be closed and the cabin heater and defroster must be on during alternate static source operation. The altimeter error is less than 50 feet unless otherwise placarded. To prevent bugs and water from entering the pitot pressure hole when the airplane is parked, a cover should be placed over the pitot head. A partially or completely blocked pitot head will give erratic or zero readings on the instruments. NOTE During preflight, check to make sure the pitot cover is removed. REPORT: VB-1612 7-18 ISSUED: JULY 12, 1995 1. ALTIMETER 2. VERTICAL SPEED INDICATOR 3. AIRSPEED INDICATOR 4. STATIC SOURCE PICKUP 5. HEATED PITOT SWITCH (OPTIONAL) 8. ALTERNATE STATIC SOURCE VALVE 7. PITOT AND STATIC DRAINS B. PITOT HEAD PA-28R-201, ARROW 7.21 PITOT-STATIC SYSTEM (continued) DESCR/OPERATION ISSUED: JULY 12, 1995 PITOT-STATIC SYSTEM Figure 7-19 REPORT: VB-1612 7-19 SECTION 7 REPORT: VB-1612 7-20 -14 15 17 18 15 EEN 10 11 12 13 G SECTION 7 DESCR/OPERATION 7.23 INSTRUMENT PANEL 20 22 19 21 23 De Figure 7-21 INSTRUMENT PANEL 505 |sj 0% 25 ISSUED: JULY 12, 1995 1121 ° 1+ ° મા CLIMATE CONTROL CENTER 00000001 000000000 31 35 33 31 39 38 36 34 0 0 29 27 26 32 30 PA-28R-201, ARROW PA-28R-201 ARROW DESCR/OPERATION SECTION 7 1. VOR/LOC/GLIDESLOPE INDICATOR 2. CLOCK 3. TURN COORDINATOR 4. AIRSPEED INDICATOR - 5. WARNING GEAR UNSAFE LIGHT 6. DIRECTIONAL GYRO 7. ATTITUDE GYRO 8. VERTICAL SPEED INDICATOR 9. ANNUNCIATOR TEST SWITCH 10. ALTIMETER 11. TACHOMETER 12. MANIFOLD PRESSURE AND FUEL FLOW/PRESSURE GAUGE 13. ANNUNCIATOR LIGHTS 14. MAGNETIC COMPASS 15. AUTOPILOT 16. AUDIO CONTROL PANEL 17. COMMUNICATIONS TRANS- CEIVER 18. AREA NAVIGATION RECEIVER 19. NAVIGATION/COMMUNICATIONS TRANSCEIVER 20. ADF RECEIVER 21. RADAR TRANSPONDER 22. GYRO SUCTION GAUGE 23. CLIMATE CONTROL CENTER 24. HOUR METER 25. MIKE/PHONE JACKS 26. CIRCUIT BREAKERS 27. ELECTRICAL SWITCHES 28. ALTERNATE AIR CONTROL 29. MICROPHONE HOLDER 30. ENGINE CONTROLS QUADRANT 31. AIR CONDITIONER DOOH LIGHT 32. E.G.T. GAUGE 33. LANDING GEAR SELECTOR 34. LANDING GEAR POSITION 35. LEFT AND RIGHT FUEL GAUGES 36. OIL TEMPERATURE GAUGI 37. AMMETER 38. OIL PRESSURE GAUGE 39. RADIO/SWITCH/INSTRUMENT LIGHTS CONTROL 40. IGNITION (MAGNETO) SWITCH 41. RADIO COMPASS (ADF) 42. VOR/LOC INDICATOR INSTRUMENT PANEL REVISED: OCTOBER 7, 2004 ISSUED: JULY 12, 1995 Figure 7-21 REPORT: VB-1612 7-21 SECTION 7 DESCR/OPERATION PA-28R-201. ARROW 7.23 INSTRUMENT PANEL (continued) The instrument panel is designed to accommodate the customary advanced flight instruments and the normally required power plan: instruments. The altitude and directional gyros, located in the center of the left hand instrument panel, are vacuum operated. The vacuum gauge is located on the right hand instrument panel. The turn indicator, on the left side, is electrically operated. The optional Horizontal Situation Indicator (HSI), when installed in place of the directional gyro, is also electrically operated. The radios are located in the center section of the panel, and the circuit breakers are in the lower right corner of the panel. An annunciator panel is mounted in the upper instrument panel to warn the pilot of a possible malfunction in the alternator, oil pressure, or vacuum systems. If installed, the optional radio master (RADIO MASTR) switch is located on the bottom row of the main switch panel. When the battery master (BATT MASTR) switch is turned ON, power is supplied to the avionics master relay switch, opening the contactors, and preventing current flow to the radios. When the radio master (RADIO MASTR) switch is turned ON, power is removed from the avionics master relay, allowing the contactors to spring closed, permitting current flow to the radios. A ground clearance energy saver system is available to provide direct power to the number one communications (COMM 1) transceiver without turning on the battery master (BATT MASTR) switch and, if equipped, the radio master (RADIO MASTR) switch. An internally lit ground clearance (GND CLC) rocker switch, located on the instrument panel, provides annunciation for engagement of the system. When the switch is ON, direct airplane battery power is applied to the number one communications (COMM 1) transceiver audio amplifier (speaker) and radio accessories. During periods when the engine is shutdown, and communications is not required, the ground clearance (GND CLC) switch must be turned OFF to prevent depletion of the battery. REPORT: VB-1612 7-22 ISSUED: JULY 12, 1995 SECTION 7 PA-28R-201, ARROW DESCR/OPERATION FWD CABIN DOOR LATCH Figure 7-23 7.25 CABIN FEATURES All seat backs have three positions: normal, intermediate and recline. The adjustment lever is located at the base of the seat back on the outboard side of the seat. The front seats adjust fore and aft for ease of entry and occupant comfort. An armrest is located on the side panels adjacent to the front seat. The rear seats are easily removed to provide room for bulky items. Rear seat installations incorporate leg retainers with latching mechanisms, which must be released before the rear seats can be removed. Releasing the retainers is accomplished by depressing the plunger behind each rear leg. Optional headrests are available. Seat occupants are protected by individual lap belts and single strap shoulder harnesses. Each shoulder harness is controlled by an inertial reel located above the side window. The shoulder strap is routed over the shoulder adjacent to the window and attached to the lap belt in the general area of the occupant's inboard hip. A check of the inertial reel mechanism can be made by pulling sharply on the strap and checking that the reel will lock in place under sudden stress; this locking feature prevents the strap from extending ISSUED: JULY 12, 1995 REPORT: VB-1612 7-23 SECTION 7 DESCR/OPERATION PA-28R-201, ARROW 7.25 CABIN FEATURES (continued) and holds the occupant in place. Under normal movement the strap will extend and retract as required. Shoulder harnesses should be routinely wom during takeoff, landing and whenever an in-flight emergency situation occurs. Additional features include pilot storm window, two sun visors, ash trays for each occupant, map pockets located on the side panels below the instrument panel, miscellaneous pockets on the rear of the front seat backs, armrests for the front occupants, cabin or baggage door locks and ignition lock. The Arrow cabin door is double locked. To close the cabin door, hold the door closed with the armrest while moving the side door latch to the LATCHED position; then engage the top latch. Both latches must be secured before flight. 7.27 BAGGAGE AREA A large baggage area, located behind the rear seats, is accessible either from the cabin or through a large outside baggage door on the right side of the aircraft. Maximum capacity is 200 lbs. Tiedown straps are provided and should be used at all times. NOTE It is the pilot's responsibility to be sure that when baggage is loaded the aircraft C.G. falls within the allowable C.G. Range. (See Weight and Balance Section.) REPORT: VB-1612 7-24 ISSUED: JULY 12, 1995 SECTION 7 PA-28R-201, ARROW DESCR/OPERATION 7.29 HEATING, VENTILATING, AND DEFROSTING SYSTEM The heating system is designed to provide maximum comfort for the occupants during winter and cool weather flights. The system includes a heat shroud, heat ducts, defroster outlets, heat and defroster controls. CAUTION When cabin heat is operated, heat duct surface becomes hot. This could result in burns if arms or legs are placed too close to heat duct outlets or surface. An opening in the front of the lower cowl admits ram air to the heater shroud and then the air is ducted to the heater shut-offs on the right and left side of the firewall. When the shut-off's are opened the heated air then enters the heat ducts located along each side of the center console. Outlets in the heat duct are located at each seat location. Airflow to the rear seats can be regulated by controls in the heat ducts located between the front seats. The temperature of the cabin is regulated by the heater control located on the right side of the instrument panel. Defrosting is accomplished by heat outlets located on the right and left side of the cowl cover. Heated air is ducted directly to defroster shut-off valves at the firewall, then to the defroster outlets. The airflow is regulated by a defroster control located below the heat control. To aid air distribution, the cabin air is exhausted overboard by an outlet located on the bottom of the fuselage. Cabin exhaust outlets are located below and outboard of the rear seats. The above features are removed when air conditioning is installed. Optional individual overhead fresh air outlets supply fresh air from a louvered air inlet located on the side of the left aft fuselage beneath the dorsal fin. The air is directed to a plenum chamber at the base of the fin, then ducted to the individual outlets. For individual comfort, the amount and direction of air can be regulated to control the amount of air and direction of desired airflow. An optional blower is available which forces outside air through the overhead vents for ground use. The blower is operated by a FAN switch with three positions - OFF, LOW, or HIGH. ISSUED: JULY 12, 1995 REPORT: VB-1612 7-25 1. FRESH AIR INLET 2. FRESH AIR INLET 3. FRESH AIR BLOWER 4. BULKHEAD ASSEMBLY 6. FRESH AIR DUCT 6. CABIN EXHAUST OUTLET 7. CABIN VENT B. CONTROL PANEL 9. DEFROSTER CONTROL LINE 10. HEATER CONTROL UNE 11. CABIN HEAT DIVERSION CONTROL 12. FRESH AIR CONTROL REPORT: VB-1612 7-26 SECTION 7 DESCR/OPERATION PA-28R-201, ARROW 7.29 HEATING, VENTILATING, AND DEFROSTING SYSTEM (continued) Figure 7-25 HEATING, VENTILATING AND DEFROSTING SYSTEM ISSUED: JULY 12, 1995 FRESH AIR ✓ HEATER AIR PA-28R-201, ARROW SECTION 7 DESCR/OPERATION 7.31 STALL WARNING An approaching stall is indicated by a stall warning horn which is activated between five and ten knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall. Stall speeds are shown on graphs in the Performance Section. The stall warning horn emits a continuous sound in contrast to the gear warning horn, which emits a 90 Hz beeping sound. The stall warning horn is activated by a lift detector installed on the leading edge of the left wing. During preflight, the stall warning system should be checked by turning the battery master (BATT MASTR) switch ON, lifting the detector and checking to determine if the horn is actuated. 7.33 FINISH All exterior surfaces are primed with etching primer and finished with acrylic lacquer. To keep the finish attractive looking, economy size spray cans of touchup paint are available from Piper Dealers. 7.35 AIR CONDITIONING* The air conditioning system is a recirculating air system. The major components include an evaporator, a condenser, a compressor, a blower, switches and temperature controls. The evaporator is located on the left side of the fuselage behind the rear baggage compartment. This cools the air used for the air conditioning system. The condenser is mounted on a retractable scoop located on the bottom of the fuselage and to the rear of the baggage compartment area. The scoop extends when the air conditioner is ON and retracts to a flush position when the system is OFF. The compressor is mounted on the forward right underside of the engine. It has an electric clutch which automatically engages or disengages the compressor to the belt drive system of the compressor. Air from the baggage area is drawn through the evaporator by the blower and distributed through an overhead duct to individual outlets located adjacent to each occupant. *Optional equipment ISSUED: JULY 12, 1995 REPORT: VB-1612 7-27 SECTION 7 DESCR/OPERATION PA-28R-201, ARROW 7.35 AIR CONDITIONING* (continued) The switches and temperature control are located on the lower right side of the instrument panel in the climate control center panel. The temperature control regulates the temperature of the cabin. Turning the control. clockwise increases cooling; counterclockwise decreases cooling. The fan speed switch and the air conditioning ON-OFF switch are inboard of the temperature control. The fan can be operated independently of the air conditioning; however, the fan must be on for air conditioner operation. Turning either switch off will disengage the compressor clutch and retract the condenser door. Cooling air should be felt within one minute after the air conditioner is turned on. NOTE If the system is not operating in 5 minutes, turn the system OFF until the fault is corrected. The fan switch allows operation of the fan with the air conditioner turned OFF to aid in cabin air circulation. LOW or HIGH can be selected to direct a flow of air through the air conditioner outlets in the overhead duct. These outlets can be adjusted or turned off individually. A condenser door light, located to the right of the tachometer, illuminates when the door is open and is extinguished when the door is closed. A circuit breaker on the circuit breaker panel protects the air conditioning electrical system. Whenever the throttle is in the full forward position, it actuates a micro switch which disengages the compressor and retracts the scoop. This allows maximum power and maximum rate of climb. The fan continues to operate and the air will remain cool for about one minute. When the throttle is retarded approximately inch, the clutch will engage, the scoop will extend, and the system will again supply cool, dry air. *Optional equipment REPORT: VB-1612 7-28 ISSUED: JULY 12, 1995