Wiring Diagram for the Piper PA-38 Tomahawk

main gear struts are single-leaf steel springs. The springs, axles and fittings of the main gear are interchangeable. The nose gear is steerable by use of the rudder pedals through a 60 degree arc, 30 degrees each side of center. The optional toe brakes, if installed, aid in the execution of tighter turns. The standard brake system includes a master cylinder and brake fluid reservoir which is installed on the top left forward face of the firewall. The parking brake handle/knob is mounted below and near the center of the (5). To the parting brake, first depress and hold the toe brake pedals and then pull out on the parking brake handle/knob. To release the parking brake, first depress and hold the toe brake pedals and then push in on the parking brake handle/knob. WARNING No braking action will occur if handle/knob is pulled prior to brake application When the optional dual toe brake system is installed. a toe brake pedal is included on each rudder pedal. Each toe brake includes a separate brake cylinder above the pedal. With this installation. the left or the right brake may be operated separately to aid in steering and turning. *6.00 x 6 wheel assemblies are standard on aircraft with serial nos. 38-81A0001 and up. Optional on earlier aircraft. ISSUED: JANUARY 20, 1978 REVISED: APRIL 28, 1989 REPORT: 2126 7-3 SECTION 7 DESCRIPTION & OPERATION REPORT: 2126 7-4 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK WHEEL ASSEMBLIES Figure 7-1 NOSE WHEEL MAIN WHEEL ISSUED: JANUARY 20, 1978 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK SECTION 7 DESCRIPTION AND OPERATION FLIGHT CONTROL CONSOLE Figure 7-3 7.9 FLIGHT CONTROLS Dual flight controls are standard equipment on the PA-38-112. The flight controls actuate the primary control surfaces through a cable system, and the controls are balanced for light operating forces. The horizontal surface of the tail is a fixed stabilizer with a moveable elevator. A trim control wheel mounted between the seats operates the longitudinal trim function of the elevator (Figure 7-3). Rotation of the wheel forward gives nose down trim and rotation aft gives nose up trim. A trim position indicator is mounted adjacent to the trim control wheel. The rudder is conventional in design and operation. A ground adjustable trim tab is attached to the trailing edge of the rudder. The wing flaps are manually operated by the flap control level located between the seats. The flaps are connected to the lever through a torque tube and push rods. The flaps can be set into three positions: fully retracted, 21] ISSUED: JANUARY 20, 1978 REVISED: APRIL 28, 1989 REPORT: 2126 7-5 SECTION 7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK degrees extended, and fully (34 degrees) extended. To extend the flaps, pull the flap handle aft to the desired flap setting, hesitating momentarily as the ratchet locks into position. To retract the flaps, press the button on the end of the flap handle to disengage the ratchet and push the flap handle to the desired flap setting. When the flap setting is changed, there is an associated pitch change in the airplane. This pitch change can be corrected either by elevator trim or increased control wheel force. 7.11 ENGINE CONTROLS Engine controls consist of a throttle control and a mixture control lever. These controls are located on the control quadrant on the lower center of the instrument panel (Figure 7-5) where they are accessible from both seats. The controls utilize teflon-lined control cables to reduce friction and binding. The throttle lever is used to adjust engine 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 lever in the full lean position. For information on the leaning procedure, see the Avco-Lycoming Operator's Manual. The friction adjustment wheel in the center of the control quadrant may be adjusted to increase or decrease the friction holding the throttle and mixture controls or to lock the controls in a selected position. The carburetor heat control lever is located on the left of the control quadrant on the instrument panel. The control is placarded with two positions: "ON" (down), "OFF" (up). 7.13 FUEL SYSTEM Fuel is stored in two sixteen gallon (15 gallons usable) fuel tanks, giving the airplane a total capacity of thirty-two U.S. gallons (30 gallons usable). The tanks are secured to the leading edge of each wing with rivets. When installed, a filler neck indicator aids in determining fuel remaining when the tanks are not full. The fuel tank selector control (Figure 7-5) is located in the center of the engine control quadrant. The button on the selector cover must be depressed and held while the handle is moved to the OFF position. The button releases automatically when the handle is moved back to the ON position. A fuel quantity gauge for each fuel tank is located on either side of the fuel tank sclector, each gauge on the same side as the corresponding fuel tank. REPORT: 2126 7-6 ISSUED: JANUARY 20, 1978 REVISED: APRIL 28, 1989 OFF CARR HEAT PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK PARK FUSH 15 USCAL USGABE FUEL (SURGAL DETABLE CONTROL QUADRANT FUEL SELECTOR Figure 7-5 ISSUED: JANUARY 20, 1978 SECTION 7 DESCRIPTION & OPERATION N ** REPORT: 2126 7-7 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK An auxiliary electric fuel pump is provided in case the engine-driven pump fails. The electric pump should be ON for all takeoffs and landings and when switching tanks. The fuel pump switch is located in the switch panel to the left of the throttle quadrant. The fuel drains should be opened daily prior to the first flight to check for water or sediment. Each tank has an individual drain at the bottom, inboard rear corner. A fuel strainer, located on the lower left front of the fire wall, has a drain which is accessible from outside the left nose section. The strainer should also be drained before the first flight of the day. Refer to paragraph 8.21 for the complete fuel draining procedure. The fuel pressure gauge is mounted in a gauge cluster located to the right of the control quadrant (refer to Figure 7-13). An engine priming system is installed to facilitate starting. The primer pump is located to the lower right of the control quadrant. 7.15 ELECTRICAL SYSTEM The electrical system includes a 14-volt, 60-ampere alternator, a voltage regulator, an over voltage relay, a battery contactor and a 12-volt, 25-ampere hour battery (Figure 7-9). The battery is entirely enclosed in a vented stainless steel box mounted in the engine compartment on the upper right forward side of the firewall. The voltage regulator and overvoltage relay are located on the right aft side of the firewall behind the instrument panel. Electrical switches are located on the lower part of the instrument panel just left of center, and the circuit breakers are located on the lower right of the instrument panel. Each circuit breaker on the panel is of the push to reset type and is clearly marked as to its function and amperage. Circuit provisions have been included to handle the addition of various items of optional equipment (Figure 7-11). If a breaker_pops, it should be allowed to cool for a couple of minutes before resetting the breaker. Rheostat knobs to the left of the circuit breakers control the intensity of of instrument and radio lights. The master switch and magneto switch are on the lower left instrument panel below the left control wheel. REPORT: 2126 7-8 ISSUED: JANUARY 20. 1978 REVISED: MAY 10, 1982 FUEL SYSTEM SCHEMATIC ISSUED: JANUARY 20, 1978 Figure 7-7 REPORT: 2126 7-9 CARBURETOR. TO PRIMER NOZZLES FUEL PRESS. SENDER ENGINE DRIVEN FUEL PUMP ELECTRIC FUEL PUMP FUEL FILTER FUEL SELECTOR FILLER CAP THROTTLE SELECTOR KNOB- MIXTURE CONTROL PRIMER (OPTIONAL). FUEL PRESSURE GAUGE ☑ ⇓ } QUANTITY GAUGES LEFT FUEL TANK VENT PA-38-112, TOMAHAWK PIPER AIRCRAFT CORPORATION RIGHT FUEL TANK FILLER CAP ( DESCRIPTION & OPERATION VENT SECTION 7 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK Standard electrical accessories include a starter, a key lock ignition, an electric fuel pump, an audible stall warning, fuel gauges, an ammeter, and an alternator warning light. The system provides for the addition of such optional accessories as interior and exterior lights, a heated pitot head, and communication and navigational equipment. The anti-collision and landing lights are controlled by rocker switches on the switch panel. WARNING Strobe lights should not be operating when flying through overcast and clouds since re- flected light can produce spacial disorientation. Do not operate strobe lights in close proximity to ground, during takeoff and landing. The master switch is a split rocker switch. One side of the switch is for the battery ("BAT") and the other is for the alternator ("ALT"). The words “master switch" as used in this handbook and unless otherwise indicated. refer to both the "BAT" and "ALT" switches, and they are to be depressed simultaneously to ON or OFF as directed. The ammeter is mounted in the instrument cluster to the right of the engine control quadrant. The ammeter as installed indicates the electrical load on the alternator in amperes. With all the electrical equipment turned off and the master switch on, the ammeter will indicate the charging rate of the battery. As each electrical unit is switched on, the ammeter will indicate the total ampere draw of all the units including the battery. For example, the maximum continuous load for night flight with radios on is about 30 amperes. This 30 ampere value plus about 2 amperes for a fully charged battery will appear continuously under these flight conditions. The amount of current shown on the ammeter will tell immediately if the alternator system is operating normally, as the amount of current shown should equal the total amperage drawn by the electrical equipment which is operating. The overvoltage relay protects the electronics equipment from a momentary overvoltage condition (approximately 16.5 volts and up) or a catastrophic regulator failure. If no output is indicated on the ammeter during flight, all unnecessary electrical equipment should be turned off to reduce the electrical load. The 5 ampere field circuit breaker should be checked and reset if open. If the breaker is not open, the "ALT" half of the REPORT: 2126 7-10 ISSUED: JANUARY 20, 1978 REVISED: MARCH 1, 1979 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK ANNUNCIATOR LIGHT ALTERNATOR FIELD 5A SA 15A ALT, 50t 75A AMMETER SECTION 7 DESCRIPTION & OPERATION OPTIONAL OVER- (HEAD LIGHT SWITCH STARTER SWITCH EXTERNAL POWER RECEPTACLE I EXT. POWER SOL. 25A.H. BATTERY WL 12V STARTER SOLENOID MASTER SOLENOID Lanmo STARTER MOTOR 60 AMP ALTERNATOR VOLTAGE REGULATOR Q.V. RELAY YEL OF G IGND-OREG BATD- RED OFI A+ GND MASTER SWITCH ALTERNATOR AND STARTER SCHEMATIC S/N 38-78A0001 THRU 38-78A0800 Figure 7-9 ISSUED: JANUARY 20, 1978 REVISED: JANUARY 15, 1981 REPORT: 2126 7-11 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK WARN ALT OUTPUT ALT FIELD 60A START & ACCESS OPTIONAL ALT ALT INOP SENSE Hi. START SWITCH EXT POWER SOL AMPS FLOOD LIGHT AUX START (MOTOR VOLTAGE REG. +1 START SOL EXT POWER RECEPTACLE / Hi 25 AM, 12v CLOCK (OPT) HOUR (OPT) MASTER SWITCH Ov RELAY ALTERNATOR AND STARTER SCHEMATIC S/N 38-78A0801 AND UP ISSUED: JANUARY 15, 1981 Figure 7-9a REPORT: 2126 7-11b PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK SECTION 7 DESCRIPTION & OPERATION master switch should be turned off for 1 second to reset the overvoltage relay. If the ammeter continues to indicate no output, electrical load should be maintained at the absolute minimum and the flight should be terminated as soon as practicable. 7.17 INSTRUMENT PANEL The instrument panel (Figure 7-13) is designed to accommodate instruments and avionics equipment for VFR and IFR flight. Radio equipment is mounted in the center and right instrument panel; flight instruments are mounted on the left. An engine instrument cluster in the lower instrument panel just right of the control quadrant includes a fuel pressure gauge, an ammeter, an oil temperature gauge and an oil pressure gauge. Fuel quantity indicators for each tank are mounted in the control quadrant on either side of the fuel selector. The tachometer is located to the left of the control quadrant. The alternator warning light is in the upper left instrument panel. Circuit breakers are on the lower right of the instrument panel and electrical switches are just left of the control quadrant. Heater controls are to the left of the pilot's control wheel. Fresh air vents are located to the extreme left and right lower corners of the instrument panel. Standard instruments include a compass, an airspeed indicator, a recording tachometer, an altimeter, the engine instrument cluster, the fuel quantity gauges and the alternator warning light. The magnetic compass is mounted in the center of the cockpit at the top of the windshield. A variety of optional items are available for installation in the instrument panel. These options include a suction gauge on the upper left; an attitude gyro, a directional gyro, a true airspeed indicator, a vertical speed indicator and a turn coordinator in the flight instrument group; and an aircraft hour meter on the extreme right of the panel. The gyros are vacuum operated through the optional vacuum system, and the turn coordinator is electric. An optional primer system* is operated by a primer pump to the lower right of the control quadrant. An electric clock is available for installation in the upper left corner of the panel. The optional outside air temperature gauge is located in the overhead cockpit area. *Standard on aircraft with serial nos. 38-79A0001 and up. Optional on earlier aircraft. ISSUED: JANUARY 20, 1978 REVISED: NOVEMBER 2, 1981 REPORT: 2126 7-13