Wiring Diagram for the Piper PA-32R Lance

system. The primary (through the filter) induction source should always be used for takeoffs. The Bendix RSA-10ED1 type fuel injection system consists of a servo regulator which meters fuel flow in proportion to airflow to the engine, giving the proper fuel-air mixture at all engine speeds, and a fuel flow divider which receives the metered fuel and accurately divides the fuel flow among the individual cylinder fuel nozzles. A combination fuel flow indicator and manifold pressure gauge is installed in the left side of the instrument panel. The fuel flow indicator is connected to the fuel flow divider and monitors fuel pressure. The instrument converts fuel pressure to an accurate indication of fuel flow in gallons per hour and percentage of cruise power. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 7-3 SECTION 7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 7.9 ENGINE CONTROLS Engine controls consist of a throttle control, a propeller control and a mixture control lever. These controls are located on the control quadrant on the lower center of the instrument panel (Figure 7-1) where they are accessible to both the pilot and the copilot. The controls utilize teflon-lined control cables to reduce friction and binding. The throttle lever is used to adjust the manifold pressure. It incorporates a gear up warning horn switch which is activated during the last portion of travel of the throttle levers to the low power position. If the landing gear is not locked down, the horn will sound until the gear is down and locked or until the power setting is increased. This is a safety feature to prevent an inadvertent gear up landing. The propeller control lever is used to adjust the propeller speed from high RPM to low RPM. The mixture control lever is used to adjust the air to fuel ratio. The engine is shut down by the placing of the mixture control lever in the full lean position. In addition, the mixture control has a lock to prevent activation of the mixture control instead of the pitch control. For information on the leaning procedure, see the Avco-Lycoming Operator's Manual. The friction adjustment lever on the right side of the control quadrant may be adjusted to increase or decrease the friction holding the throttle, propeller, and mixture controls or to lock the controls in a selected position. The alternate air control is located to the right of the control quadrant. When the alternate air lever is in the up, or closed, position the engine is operating on filtered air; when the lever is in the down, or open, position the engine is operating on unfiltered, heated air. The control is operated by pressing the knob to the left to clear the retaining gate and then moved in the desired direction (refer to Figure 7-1). REPORT: VB-750 74 ISSUED: AUGUST 1, 1975 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE AIRCRAFT EQUIPPED WITH BACKUP GEAR EXTENDER 25 TTT 1990 PARK SPAKE PUSH 157 1167 SEAR GEAR P OS KIAS MAX OFF LEFT 4704L NM00 29 ALAS M AIGHT TCAL 0666666 SECTION 7 DESCRIPTION AND OPERATION CLUST ALT AIR CONTROL KNOB MUST BE PRESSED TO THE LEFT TO CLEAR THE RETAINING GATE PRIOR TO SELECTING THE DESIRED POSITION. CONTROL QUADRANT AND CONSOLE Figure 7-1 ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 REPORT: VB-750 7-5 SECTION 7 DESCRIPTION AND OPERATION וון 15 20 10 RPM 25 -5 HUND OR 24562 AFTED SMIN RED CE FOWLER TO 2575 PM S 33 IN G. 30 35111 NOSE GEAR PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE LEFT GEAR RIGHT GEAR GEAR AUTO EXT OFF UP 106 KIAS MAX DOWN 129 KIASMAX AIRCRAFT EQUIPPED WITH BACKUP GEAR EXTENDER LANDING GEAR SELECTOR Figure 7-3 7.11 LANDING GEAR The Cherokee Lance is equipped with a retractable tricycle landing gear, which is hydraulically actuated by an electrically powered reversible pump. The pump is controlled by a selector switch on the instrument panel to the left of the control quadrant (Figure 7-3). The landing gear is retracted or extended in about seven seconds. WARNING Avoid ejecting objects out of the pilot storm window which could possible enter or obstruct the holes in the mast. Some aircraft also incorporate a pressure sensing device in the system which lowers the gear regardless of gear selector position, depending upon airspeed and engine power (propeller stlipstream). Gear extension is designed to occur, even if the selector is in the up position, at airspeeds below approximately 118 mph with power off. The extension speeds will vary from approximately 93 mph to approximately 118 mph depending on power settings and altitude. The device also prevents the gear from retracting at airspeeds below approximately 93 mph will full power, though the selector switch may be in the up position. This speed increases with reduced power and/or increased altitude. Manual override of the device is provided by an emergency gear lever located between the front seats to the right of the flap handle (refer to Figure 7-9). The sensing device operation is controlled by differential air pressure across a flexible diaphragm which is mechanically linked to a hydraulic valve and an electrical switch which actuates the pump motor. A high pressure and static air source for actuating the diaphragm is provided in a mast mounted on the left side of the fuselage above the wing. Any obstruction of the holes in this mast will cause the gear to extend. An optional heated mast is available to alleviate obstruction in icing conditions. The optional heated mast is turned on whenever the PITOT HEAT is turned on. REPORT: VB-750 7-6 ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 7 DESCRIPTION AND OPERATION The emergency gear lever, when placed in the raised position, can be used to override the system, and gear position is then controlled by the selector switch regardless of airspeed/power combinations. The emergency gear lever is provided with a latching device which may be used to lock the override lever in the up position. The latch is located on the right side panel of the console below the level of the manual override lever. To lock the override lever in the up position, raise the override lever to the full up position and push the latch down. A yellow warning light located below the gear selector switch (Figure 7-3) flashes to warn the pilot that the automatic gear lowering system is disabled. The latch is spring-loaded to the off position to aid disengagement. To disengage the latch raise the override lever and release. The lever will return to its normal position and the yellow flashing light will extinguish. The lever must also be latched in the raised (up) position when gear-up stalls are practiced. The emergency gear lever, when used for emergency extension of the gear, manually releases hydraulic | pressure to permit the gear to free fall with spring assistance on the nose gear. The lever must be held in the downward position for emergency extension. Gear down and locked positions are indicated by three green lights located above the selector, and a red Warning Gear Unsafe light is located at the top of the panel. An all lights out condition indicates the gear is up. The landing gear should not be retracted above a speed of 125 mph and should not be extended above a speed of 150 mph. The main landing gear uses Cleveland 6.00 x 6 wheels. The main gear incorporate brake drums and Cleveland double disc hydraulic brake assemblies. The nose wheel carries a 5.00 x 5 six ply tire and the main gear use 6.00 x 6 eight ply tires. All three tires are tube type. Two micro-switches in the throttle quadrant activate a warning horn and red Warning Gear Unsafe light under the following conditions: 1. Gear up and power reduced below approximately 14 inches of manifold pressure. 2. On aircraft equipped with the backup gear extender, if the system has extended the landing gear and the gear selector is UP, except at full throttle. 3. Gear selector switch UP while on the ground. On aircraft which are NOT equipped with the backup gear extender, an additional switch is installed which activates the warning horn and light whenever the flaps are extended beyond the approach position (10°) and the landing gear are not down and locked. The gear warning horn emits a 90 Hz beeping sound in contrast to the stall warning horn which emits a | continuous sound. The nose gear is steerable through a 22.5 degree arc each side of center through the use of the rudder pedals. As the nose wheel retracts, the steering linkage disengages to reduce rudder pedal loads in flight. The nose wheel is equipped with a hydraulic shimmy dampener to reduce nose wheel shimmy. The oleo struts are of the air-oil type, with normal extension being 2.60 inches for the nose gear and 4.0 inches for the main gear under normal static load (empty weight of airplane plus full fuel and oil). The standard brake system includes toe brakes on the left and right set of rudder pedals and a hand brake located below and near the center of the instrument panel. The toe brakes and the hand brake have individual brake cylinders, but all cylinders use a common reservoir. The parking brake is incorporated in the lever brake and is operated by pulling back on the lever and depressing the knob attached to the top of the handle. To release the parking brake, pull back on the brake lever; then allow the handle to swing forward. ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 REPORT: VB-750 7-7 SECTION 7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE NORM OVERRIDE GEAR OVERRIDE 1 SWITCH (NOTE 5) LANDING GEAR ACTUATOR 25 AMP DOWN HYD PUMP MOTOR EB FLASHER AUTOMATIC GEAR DOWN ACTUATOR 100 3-1/4 W SQUAT SW (NOTE 3) (NOTE 5) P S NOTES: GND FLT PUMP UP EB EB GEAR ACTUATOR (NOTE 1) DM UP DN UP TERMINAL REPORT: VB-750 7-8 GEAR UNSAFE UP LIMIT SWITCH THROTTLE SWITCH 'A' NC 4 5 N-UP QUP O PRESS SWITCH NC C SLOW NO CR N-UP QUP O NO NC NO NC NO QUA 5 AMP LANDING GEAR CONTROL & WARNING CIRCUIT PROTECTOR L GEAR SHOWN IN DOWN LOCKED POSITION WITH STRUTS COMPRESSED AND THROTTLE CLOSED. 2. LIGHT LEGEND: R-RED LIGHT Y-YELLOW LIGHT TO UP CYCLE G-GREEN LIGHT W-WHITE LIGHT 3. AUTOMATIC GEAR DOWN ACTUATOR SWITCH SHOWN IN LOW AIRSPEED POSITION. 4. SWITCH LEGEND: C-COMMON NC-NORMALLY CLOSED NO-NORMALLY OPEN 5. AIRCRAFT EQUIPPED WITH BACKUP GEAR EXTENDER. (NOTE 5) CR DOWN LOCK SWITCH NO NC NO NC NO NC EB RIGHT CLLEFT (GOLNOSE G 3 TERMINAL GEAR WARNING HORN FLASHER LANDING GEAR ELECTRICAL SCHEMATIC Figure 7-5 6 TERMINAL TO RADIO LIGHT DIMMER SWITCH ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE RESERVOIR FILTER LOW PRESSURE CONTROL SECTION 7 DESCRIPTION AND OPERATION HIGH PRESSURE CONTROL -THERMAL RELIEF GEAR UP SHUTTLE VALVE- GEAR DWN NOSE GEAR UP MAIN GEAR MAIN GEAR HYDRAULIC UP CYLINDER -NOSE GEAR HYDRAULIC CYLINDER GEAR UP CHECK VALVE PRESSURE SWITCH MANUAL FREE FALL EMERGENCY EXTEND AUTOMATIC GEAR DOWN AND EMERGENCY FREE FALL GEAR VALVE (NOTE 2) AUTO OVERRIDE RESTRICTOR NIPPLE PUMP DOWN OR DIAPHRAGM (NOTE 1) -STATIC FROM PRESSURE HEAD ON FUSELAGE SIDE RAM AIR MAINTAIN UP (NOTE 1) AUTOMATIC GEAR DOWN PRESSURE SENSING CHAMBER (NOTE 1) NOTE 1. AIRCRAFT EQUIPPED WITH BACKUP GEAR EXTENDER. 2. AUTOMATIC GEAR DOWN REFERENCE IS FOR AIRCRAFT EQUIPPED WITH THE BACK UP GEAR EXTENDER. LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 Figure 7-7 REPORT: VB-750 7-9 SECTION 7 DESCRIPTION AND OPERATION (1) LEASE ORIDE ER FULL ELEASE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE AIRCRAFT EQUIPPED WITH THE BACKUP GEAR EXTENDER FLIGHT CONTROL CONSOLE Figure 7-9 7.13 FLIGHT CONTROLS Dual flight controls are provided as standard equipment. A cable system provides actuation of the control surfaces when the flight controls are moved in their respective directions. The horizontal surface (stabilator) is of the flying tail design with a trim tab/servo mounted on the trailing edge. This tab serves the dual function of providing trim control and pitch control forces. The trim function is controlled by a trim control wheel located on the control console between the two front seats (Figure 7-9). Rotating the wheel forward gives nose down trim and rotation aft gives nose up trim. The stabilator provides extra stability and controllability with less area, drag and weight than conventional tail surfaces. The rudder is conventional in design and incorporates a rudder trim. The trim mechanism is a spring- loaded recentering device. The trim control is located on the right side of the pedestal below the throttle quadrant. Turning the trim control clockwise gives nose right trim and counterclockwise rotation gives nose left trim. Ailerons are provided with differential deflection. This feature reduces adverse yaw in turning maneuvers, and thus reducing the amount of coordination required. REPORT: VB-750 7-10 ISSUED: AUGUST 1, 1975 REVISED: JANUARY 31, 1987 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 7 DESCRIPTION AND OPERATION Manually controlled flaps are provided. They are extended by a control cable and are spring-loaded to the retracted (up) position. The control is located between the two front seats on the control console. To extend the flaps pull the handle up to the desired flap setting of 10, 25 or 40 degrees. To retract, depress the button on the end of the handle and lower the control. A balanced control system is used for light operating forces. When extending or retracting flaps, there is a pitch change in the aircraft. This pitch change can be corrected either by stabilator trim or increased control wheel force. When the flaps are in the retracted position the right flap, provided with a over-center lock mechanism, acts as a step. NOTE The right flap will support a load only in the fully retracted (up) position. When loading and unloading passengers make sure the flaps are in the retracted (up) position. ISSUED: AUGUST 1, 1975 REPORT: VB-750 7-11 7-12 REPORT: VB-750. FUEL SYSTEM SCHEMATIC Figure 7-11 ISSUED: AUGUST 1, 1975 FILLER CAP OUTBOARD SIGHT GAUGE LEFT TANKS FLOW DIVIDER FUEL NOZZLES VENT LINE ENGINE FUEL PUMP FINGER SCREEN INBOARD FUEL FLOW GAUGE FUEL PRESSURE GAUGE FUEL INJECTOR SIGHT GAUGE FUEL SELECTOR AND FILTER FINGER SCREEN RIGHT TANKS FILLER CAP FUEL PUMP INBOARD SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-32R-300, CHEROKEE LANCE OUTBOARD -FUEL QUANTITY GAUGES PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 7 DESCRIPTION AND OPERATION FUEL SYSTEM SUMP DRAIN INSIDE PUSH DOWN TO DRAIN FUEL DRAIN LEVER Figure 7-13 7.15 FUEL SYSTEM The standard fuel capacity of the Cherokee Lance is 98 gallons, of which 94 gallons are usable. The tanks are attached to the wing structure with screws and nut plates and can be removed easily for service or inspection. When using less than the standard 98 gallon capacity of the tanks, fuel should be distributed equally between each side. The fuel selector control is located below the center of the instrument panel on the sloping face of the control tunnel (refer to Figure 7-1). It has three positions, one position corresponding to each wing tank plus an OFF position. ISSUED: AUGUST 1, 1975 REPORT: VB-750 7-13 SECTION 7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE To avoid the accumulation of water and sediment, the fuel system should be drained daily prior to first flight and after refueling. Each tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank. The fuel strainer and a system quick drain valve are located in the fuselage at the lowest point of the fuel system. It is important that the fuel system be drained in the following manner: 1. 2. 3. 4. Drain each tank through its individual quick drain located at the lower inboard rear corner of the tank, making sure that enough fuel has flowed to ensure the removal of all water and sediment. Place a container beneath the fuel sump drain outlet located under the fuselage. A special container is furnished for this operation. Drain the fuel strainer by pressing down on the lever located on the right side of the cabin on the forward edge of the wing spar housing (Figure 7-13). Move the selector through the following sequence: OFF position, left, right, while draining the strainer. Make sure that enough fuel has flowed to drain the fuel line between each tank outlet and the fuel strainer, as well as the strainer itself. With full fuel tanks, it will take approximately 6 seconds to drain all of the fuel from the line from either tank to the fuel strainer. When the tanks are less than full, it will take a few seconds longer. Examine the contents of the container placed under the fuel sump drain outlet. When the fuel flow is free of water and sediment, close the drain and dispose of the contents of the bottle. CAUTION When draining fuel, care should be taken to ensure that no fire hazard exists before starting the engine. After using the underseat quick drain, check from the outside to make sure that it has closed completely and is not leaking. Fuel quantity gauges for each of the tanks are located in the engine gauge cluster on the left side of the instrument panel. A fuel pressure indicator is also incorporated in the engine gauge cluster. A fuel quantity indicator to measure the fuel not visible through the filler neck in each wing is installed in the inboard fuel tank. This gauge indicates usable fuel quantities from 5 gallons to 25 gallons in the ground attitude. The sole purpose of this gauge is to assist the pilot in determining fuel quantities of less than 25 gallons during the preflight inspection. An electric fuel pump is provided for use in case of failure of the engine driven pump. The electric pump operates from a single switch and independent circuit protector. It should be ON for all takeoffs and landings. REPORT: VB-750 7-14 ISSUED: AUGUST 1, 1975 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 7 DESCRIPTION AND OPERATION ON ON ON ON ON ON ANTI FUEL PUMP COLL LIGHT LANDING LIGHT PITOT HEAT TRIS ANPLANE MOST BEC AS A NOWWAL CATEGO STATED IN THE FORM O ATRICANE LENCE WITH THE OPERATING LVERS, INCLUDING SPINS, APPROVED MANUALS. NO ACROBATIC · THIS AIRCRAFT APPROVED FOR VFR, IFR DAY AND NIGHT NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR SI O FAR 135 FOR FLIGHT WITH THE DOOR REMOVED, SEE THE LIMITATIONS & PROCEDURES SECTIONS OF THE PILOT'S OPERATING HANDBOOK PHONE MIKE SWITCH PANEL Figure 7-15 7.17 ELECTRICAL SYSTEM The 14-volt electrical system includes a 12-volt battery for starting and to back up alternator output. Electrical power is supplied by a 60 ampere alternator. The battery, a master switch relay, a voltage regulator and an overvoltage relay are located beneath the floor of the forward baggage compartment. Access to these electrical components is gained by removing the compartment floor and the access panel located on the left side of the forward fuselage. Electrical switches are located on a panel to the pilot's left (Figure 7-15) and all circuit breakers are on the lower right instrument panel (refer to Figure 7-19). Two thumb-wheel rheostat switches to the left of the circuit breakers control the navigation lights and the intensity of the instrument panel lights. Standard electrical accessories include the starter, the electric fuel pump, the stall warning indicator, the cigar lighter, the ammeter, and the annunciator panel. The annunciator panel includes alternator and low oil pressure indicator lights. When the optional gyro system is installed, the annunciator panel also includes a low vacuum indicator light. The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly, and that he should check and monitor the applicable system gauge to determine when or if any necessary action is required. ISSUED: AUGUST 1, 1975 REPORT: VB-750 7-15