Avionics Manual for the Piper PA-38 Tomahawk

side panel provides an alternate static source for the system when opened.** A correction card, indicating the change in altimeter reading and indicated airspeed when the alternate static source is in use, is mounted on the left side of the control quadrant cover. Static lines can be drained through a valve located inside an opening on the lower left side of the fuselage interior. A heated pitot head which alleviates problems with icing and heavy rain is available as optional equipment. The switch for the heated pitot head is located on the electrical switch panel to the left of the control quadrant. To prevent bugs and water entering the pitot hole, a cover should be placed over the pitot head while the airplane is moored. 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. *S/N 38-78A0001 thru 38-81A0006 **S/N 38-78A0001 thru 38-81A0006, and S/N 38-81A0007 and up. REPORT: 2126 7-16 ISSUED: JANUARY 20, 1978 REVISED: APRIL 28, 1989 REVISED: APRIL 30, 1981 ISSUED: JANUARY 20, 1978 2 3 4 PITOT-STATIC SYSTEM Figure 7-15 REPORT: 2126 7-17 PA-38-112, TOMAHAWK PIPER AIRCRAFT CORPORATION SECTION 7 DESCRIPTION & OPERATION 1. ALTERNATE STATIC SOURCE (S/N 38-78A0001 THRU 38-81A0006) 2. ALTIMETER 3. RATE OF CLIMB INDICATOR 4. AIRSPEED INDICATOR 5. STATIC PICKUP PADS 6. STATIC LINE 7. PITOT LINE 8. STATIC DRAIN (S/N 38-78A0001 THRU 38.81A0006) STATIC DRAIN AND ALTERNATE STATIC SOURCE (S/N 38-81A0007 AND UP) 9. PITOT HEAD 6 78 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK 1 12 13 10 11 6 7 8 1. DEFOG OUTLET 2. DEFOG AIR CONTROL 3. CABLE GUIDE 4. DEFOG CONTROL CABLE 5. CLIMATE CONTROLS 6. MUFFLER HEAT COLLECTOR 7. HEATER CONTROL 8. HEATED AIR DISTRIBUTION BOX 9. HEATER CONTROL CABLE 10. AIR VENT INTAKE 11. VENT DRAIN 12. VENT CONTROL AND OUTLET 13. HEAT DUCT OUTLETS S/N 38-78A0001 THRU 38-80A0198 6 7 8 12 10 1. DEFOG OUTLET 2. DEFOG AIR CONTROL 3. CABLE GUIDE 4. DEFOG CONTROL CABLE 5. CLIMATE CONTROLS 6. MUFFLER HEAT COLLECTOR 7. HEATER CONTROL 8. HEATED AIR DISTRIBUTION BOX 9. HEATER CONTROL CABLE 10. AIR VENT INTAKE 11. VENT DRAIN 12. VENT CONTROL AND OUTLET 13. HEAT DUCT OUTLETS S/N 38-81A0001 AND UP HEATING AND VENTILATING SYSTEM Figure 7-17 ISSUED: JANUARY 20, 1978 REVISED: JANUARY 15, 1981 REPORT: 2126 7-18 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK SECTION 7 DESCRIPTION & OPERATION 7.23 HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system (Figure 7-17) is provided by a shroud attached to the mufflers. Fumes in the cockpit could be an indication of an exhaust leak; therefore, if unusual odors are detected, the heater should be turned off and the system inspected before further operation. The amount of heat and the routing of airflow can be regulated with the controls located on the left instrument panel. Heater air may be directed to the outlets in the lower firewall below the instrument panel and the ducts mounted along the center tunnel on the right and left cockpit floor or to defroster outlets at the base of the windshield. Fresh air intakes are located on each side of the fuselage in the area aft of the engine cowling. Adjustable outlets on each lower corner of the instrument panel allow fresh air to be admitted and directed. An on-off lever is mounted below each fresh air outlet. 7.25 CABIN FEATURES For comfort and visibility, the seats are adjustable forward and aft. The seat tracks are inclined and provide automatic vertical adjustment; the seat is raised in the forward position and lowered in the aft position. The seat adjustment levers are on the centers of the seat frames just below the forward edges of the cushions. Both seat backs tilt forward to allow access to the baggage compartment. Safety belts are standard equipment on both seats. Interia reels for the shoulder straps are offered as optional equipment. For normal body movements, the inertia reel extends or retracts as required, but during sudden forward movement, the reel locks in place to prevent the strap from extending. Standard interior equipment includes a pilot storm window, door pulls with integral armrests, a glare shield, an ash tray, and a carpeted floor. The microphone and earphone jacks are between the seats on the center console. A tinted rear window is also standard equipment. Standard equipment on later model aircraft incorporates a glare shield with hand holds and side panel map pockets. Each cabin door has an interior latch below the side window. The latch is engaged when the handle is in the down position. The overhead latch in the center of the cockpit secures both doors (Figure 7-19) Before flight, the ISSUED: JANUARY 20, 1978 REVISED: JANUARY 15, 1981 REPORT: 2126 7-19 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK REPORT: 2126 7-20 UPPER LATCH MAIN LATCH UPPER AND MAIN DOOR LATCHES Figure 7-19 ISSUED: JANUARY 20, 1978 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK SECTION 7 DESCRIPTION & OPERATION latches on both doors plus the overhead latch should be secured in the latched position. A key lock is installed on the exterior overhead latch. Optional equipment available for the cabin includes a tinted windshield and side windows, sun visors and entrance steps. 7.27 BAGGAGE AREA A 20 cubic foot baggage area, located behind the seats, is accessible from the cabin. Maximum capacity is 100 pounds. Tie-down straps are available and they should be used at all times. NOTE It is the pilot's responsibility to be sure when the baggage is loaded that the aircraft C.G. falls within the allowable C.G. range. (See Weight and Balance Section.) 7.29 STALL WARNING An approaching stall is indicated by an audible alarm located behind the instrument panel. The indicator activates at between five and ten knots above stall speed. 7.31 FINISH All exterior surfaces are primed with etching primer and finished with acrylic lacquer. To keep the finish attractive, economy size spray cans of touch-up paint are available from Piper Dealers. 7.33 EMERGENCY LOCATOR TRANSMITTER* The Emergency Locator Transmitter (ELT), when installed, is enclosed under a hinged cover on the aft portion of the cockpit center console. The unit meets the requirements of FAR 91.52. The transmitter operates on a self-contained battery. *Optional equipment ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: OCTOBER 13, 1978 7-21 SECTION 7 DESCRIPTION & OPERATION PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK A battery replacement date is marked on the transmitter label. To comply with FAA regulations, the battery must be replaced on or before this date. The battery must also be replaced if the transmitter has been used in an emergency situation or if the accumulated test time exceeds one hour, or if the unit has been inadvertently activated for an undetermined time period. When installed in the airplane, the ELT transmits through the antenna mounted on the fuselage. The unit is also equipped with an integral portable antenna to allow the locator to be removed from the airplane in an emergency and used as a portable signal transmitter. The locator should be checked during the preflight ground check to make sure that it has not been accidentally activated. Check by tuning a radio receiver to 121.5 MHz. If there is an oscillating sound, the locator may have been activated and should be turned off immediately. Rearm the unit and then recheck. NOTE If for any reason a test transmission is necessary, the test transmission should be conducted only in the first five minutes of any hour and limited to three audio sweeps. If tests must be made at any other time the tests should be coordinated with the nearest FAA tower or flight service station. NARCO ELT 10 OPERATION On the unit is a switch placarded “ON," "OFF," and "ARM." the "ARM" position allows the unit to be set to the automatic mode so that it will transmit only after activation by impact and will continue to transmit until the battery is drained to depletion or until the switch is manually moved to the "OFF" position. The "ARM" position should be selected whenever the unit is in the airplane. The "ON" position is provided so the unit can be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to periodically test the function of the transmitter. The "OFF" position should be selected while changing the battery or to discontinue transmission after the unit has been activated. REPORT: 2126 7-22 ISSUED: JANUARY 20, 1978 REVISED: JANUARY 15, 1981 PIPER AIRCRAFT CORPORATION PA-38-112, TOMAHAWK SECTION 7 DESCRIPTION & OPERATION A button labled "RESET" is located above the selector switch. To rearm the unit after it has been turned off or after it has been activated, the "RESET" button should be pressed in after the selector switch has been placed in the "ARM" position. This will end transmission and rearm the unit. CCC CIR 11 OPERATION On the unit itself is a three position selector switch placarded “OFF,” "ARM" and "ON." The "ARM" position is provided to set the unit to the automatic position so that it will transmit only after impact and will continue to transmit until the battery is drained to depletion or until the switch is manually moved to the "OFF" position. The "ARM" position should be selected whenever the unit is in the airplane. The "ON" position is provided so the unit can be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to periodically test the function of the transmitter. Select the "OFF" position when changing the battery, when rearming the unit if it has been activated for any reason, or to discontinue transmission. NOTE If the switch has been placed in the "ON" position for any reason, the "OFF" position has to be selected before selecting "ARM." If "ARM" is selected directly from the "ON" position, the unit will continue to transmit in the "ARM" position. 7.35 SERIAL NUMBER PLATE The manufacturer's name plate is located on the underside of the aft fuselage, forward of the tail skid. The serial number should always be used in referring to the airplane in service and warranty matters. ISSUED: JANUARY 20, 1978 REPORT: 2126 7-23