Pilot's Operating Handbook for the Mooney M20F Executive

INDUCTION AIR VALVE MONG ALTERNATE AIR (WHEN FILTER IS OBSTRUCTED) FUEL-AIR MIXTURE The fuel injector unit of the 10-360 engine has provisions for adjusting the fuel-to-air ratio as required at different altitudes. The fuel-to-air ratio (mixture) is regulated by the hexagon shaped push-pull control located between the throttle and pro- peller controls in the cabin. This control has a vernier adjust- ment feature for obtaining precise mixture settings. An exhaust gas temperature gage is provided to indicate the optimum mix- ture setting. ENGINE COOLING The engine baffling directs air flow over the cylinders for cool- ing in flight. Cowl flaps are provided on the lower cowling to allow more free air flow on the ground and during low speed, high power conditions (i.e., climb conditions). Cowl flaps should always be open on the ground, and prolonged engine operation on the ground should be avoided to prevent engine overheating. A push-pull control is provided below the in- strument panel and to the right of the pilot for operation of the cowl flaps. 3 ENGINE LUBRICATION The engine has a pressure-type wet-sump lubrication system. It has an eight quart capacity; however, as a general rule, when the oil level drops below six quarts, one quart is added. This will maintain the oil level between the six and seven quart level. See Part III for type of oil used and time between oil changes. An oil temperature thermostat, located in the oil reservoir, is set for 180° F. to assure adequate operating engine oil tem- peratures. The oil cooler is mounted on the lower left side of the cowling. An oil filter is available as optional equipment. ENGINE IGNITION The ignition system has the following features: 1. Two Bendix magnetos, the left magneto being equipped with a set of retard breaker points. 2. A starting vibrator, located on the upper firewall, which furnishes a shower of sparks for starting. 3. A switch. which combines both ignition and starting functions. 4. Shielded spark plugs and ignition harness to suppress radio noises. When the push-type starter switch is activated in the "start" position, the starter vibrator sends an interrupted current through the retard-breaker points while the right magneto is grounded out. The left magneto then provides a fixed retard and a long duration, boosted spark for starting. FUEL SYSTEM Fuel bladders have been installed on this aircraft, see supplement. This has reduced the fuel capacity to 27.4 gallons of usable fuel in each tank and 54.8 gallons total. The bladders had a history of letting in water, so an AD was issued. See last page of Operating Limits for required pre- flight requirements. mark on the indicator. Tank vents allow ventilation as fuel is depleted and overflow when fuel expands in hot weather. The fuel tanks each have a sump drain under the wing from which fuel may be sampled to check for water or sediment contamina- tion. A small plastic cup with anactuator prong is provided to obtain fuel samples. If water is present in the fuel, a distinct line separating the water from the gasoline may be seen through the plastic cup. Water. being heavier, will be on the bottom of the cup, and the light green colored fuel will be on top. A or blue Revised March 1967 SAMPLING FUEL FROM MAIN TANKS Aluminum fuel lines feed the fuel from the tank to a two-way, positive-setting selector valve on the floor ahead of the pilot's seat. The selector valve feeds fuel from one of the tanks at a time, and also has an "off" position for extended periods of storage or for emergency use. The selector valve also con- tains a sump drain which is actuated by pulling the ring adjacent to the fuel valve handle. Switch the selector valve handle to the right and left tanks to drain the respective lines. Be sure sump drain returns to normal closed position after releasing the ring. Fuel is fed from the selector valve through the elec- tric boost pump, then to the engine driven pump and into the fuel injector unit. The electric boost pump is turned on for take-off and landing to provide fuel pressure if the engine driven pump malfunctions. 5 SELECTOR DRAIN VALVE WARNING or 100LL Under no circumstances should aviation fuel of a lower grade than 100/130 ctane be used. Aviation. fuels may be distinguished by their color: 80 octane is red, 91 octane is blue, and 100 octane is green. 100LL ELECTRICAL SYSTEM The electrical system is provided with a 50-amp., 12-volt gen- erator and a 35 amp-hour battery which is located aft of the baggage compartment. All electrical systems can be turned off by the master switch which actuates a relay located at the battery. The master switch for the electrical system is located 6 at the left-hand side of the flight panel. The electrical system operates all the electrical accessories listed below: 1. Radios 2. Engine starter 3. Starter vibrator 4. Navigation lights and interior lights 5. Landing light 6. Rotating beacon (if installed) 7. Heated pitot (if installed) 8. Turn coordinator 9. Cigarette lighter 10. Electric landing gear (if installed) 11. Fuel gages 12. Electric fuel pump 13. Stall warning horn 14. Landing gear warning horn and warning lights NOTE: The engine has its own separate electrical system and will continue to run, even though the master switch has been turned off, or even though the ac- cessory electrical system should malfunction. 15. Electric flaps 16. Electric DG Interior Lights Panel illumination is provided by two adjustable spot lights mounted on the headliner and individual post lights for the in- strument panel. These lights are controlled by a rheostat. The fuel selector valve is illuminated by a small light mounted under the panel on the left side. The intensity of this light is con- trolled by rotating the lens housing. Ammeter The ammeter in the engine instrument cluster will indicate if the battery is charging or discharging. A malfunction in the generator or voltage regulator will be shown as an ammeter discharge at flight power settings. A low battery will cause a high charge indication. Revised March 1967 7 Electrical Panel The electrical panel is divided into two parts: a. The electrical toggle switches, on the lower left side of the pilot's panel, act in combination both as on-off switches and as breaker switches. Should any of these circuits be over- loaded, the switch automatically turns to the "off" position. These switches are, from left to right: 1. The electrical fuel pump 2. An optional equipment switch (Marker beacon) Elec. DG 3. An optional equipment switch (Glide slope) Strobe 4. An optional equipment switch (Pitot heat) 5. An optional equipment switch (Rotating beacon) 6. The navigation lights 7. The landing light b. The breaker switches which are located on the lower right side of the copilot's panel, are covered by a special breaker switch cover. These switches are of the push-to-reset type. AIRFRAME The structure of the Executive 21 is of conventional all-metal design. The cabin section consists of tubular steel structure. covered with aluminum sheet metal. The center windshield post and the firewall are stainless steel. The wing. stabilizer, and fin have a main spar design and an auxiliary spar with stressed skin to carry torsional loads. The tail cone is a conventional semi-monocoque design. The seat design features contoured construction. The front seats are adjustable fore and aft and have adjustable three-position backs. The rear seat back may be removed for additional cargo space. The entire empennage pivots around two attachment points to the tail cone to provide stabilizer trim. A screw mechanism actuates the empennage movement at the rear bulkhead when the trim control wheel is operated. 8 Revised March 1967