Get the latest indepth reviews, ratings, pricing and more for the 2015 Honda Fit from Consumer Reports. The Sling 4s smooth handling and unparalleled performance and efficiency make The Airplane Factorys new fourseat homebuilt a winner. Chuck Plains 11112012 162922 1075 forum posts 240 photos As I dont shop on the interwebs unless I build up a paypal balance I happily found this foam board. Our goal at Crashtesthobby. com is to help you have fun flying radio control planes. We believe in planes that fly well that will last and can survive the crashes and. Auxiliary aircraft systems for the purpose of this overview are any system in the airplane that either support other essential systems or are systems that play. AD No. MAKE Condensed description of ad note 161619 Eurocopter Superceded by 131619 1395 Twin Commander Cracks in upper picture window frame channels. Auxiliary Aircraft Systems. Electrical system. Airplanes are equipped with either a 1. A basic airplane electrical system consists of the following components Alternatorgenerator. Battery. Masterbattery switch. Alternatorgenerator switch. Bus bar, fuses, and circuit breakers. Voltage regulator. Ammeterloadmeter. Associated electrical wiring. Engine driven alternators or generators supply electric current to the electrical system. They also maintain a sufficient electrical charge in the battery. Electrical energy stored in a battery provides a source of electrical power for starting the engine and a limited supply of electrical power for use in the event the alternator or generator fails. Most direct current generators will not produce a sufficient amount of electrical current at low engine r. Therefore, during operations at low engine r. Alternators have several advantages over generators. Alternators produce sufficient current to operate the entire electrical system, even at slower engine speeds, by producing alternating current, which is converted to direct current. The electrical output of an alternator is more constant throughout a wide range of engine speeds. Some airplanes have receptacles to which an external ground power unit GPU may be connected to provide electrical energy for starting. These are very useful, especially during cold weather starting. Follow the manufacturers recommendations for engine starting using a GPU. The electrical system is turned on or off with a master switch. Turning the master switch to the ON position provides electrical energy to all the electrical equipment circuits with the exception of the ignition system. Equipment that commonly uses the electrical system for its source of energy includes Position lights. Anticollision lights. Landing lights. Taxi lights. Interior cabin lights. Instrument lights. Radio equipment. Turn indicator. Fuel gauges. Electric fuel pump. Stall warning system. Pitot heat. Starting motor. Many airplanes are equipped with a battery switch that controls the electrical power to the airplane in a manner similar to the master switch. In addition, an alternator switch is installed which permits the pilot to exclude the alternator from the electrical system in the event of alternator failure. Figure 1 On this master switch, the left half is for the alternator and the right half is for the battery. With the alternator half of the switch in the OFF position, the entire electrical load is placed on the battery. Therefore, all nonessential electrical equipment should be turned off to conserve battery power. A bus bar is used as a terminal in the airplane electrical system to connect the main electrical system to the equipment using electricity as a source of power. This simplifies the wiring system and provides a common point from which voltage can be distributed throughout the system. Figure 2 Electrical system schematic. Fuses or circuit breakers are used in the electrical system to protect the circuits and equipment from electrical overload. Spare fuses of the proper amperage limit should be carried in the airplane to replace defective or blown fuses. Circuit breakers have the same function as a fuse but can be manually reset, rather than replaced, if an overload condition occurs in the electrical system. Placards at the fuse or circuit breaker panel identify the circuit by name and show the amperage limit. An ammeter is used to monitor the performance of the airplane electrical system. The ammeter shows if the alternatorgenerator is producing an adequate supply of electrical power. It also indicates whether or not the battery is receiving an electrical charge. Ammeters are designed with the zero point in the center of the face and a negative or positive indication on either side. Figure 3 Ammeter and loadmeter. When the pointer of the ammeter on the left is on the plus side, it shows the charging rate of the battery. A minus indication means more current is being drawn from the battery than is being replaced. A full scale minus deflection indicates a malfunction of the alternatorgenerator. A full scale positive deflection indicates a malfunction of the regulator. In either case, consult the AFM or POH for appropriate action to be taken. Not all airplanes are equipped with an ammeter. Some have a warning light that, when lighted, indicates a discharge in the system as a generatoralternator malfunction. Refer to the AFM or POH for appropriate action to be taken. Another electrical monitoring indicator is a loadmeter. This type of gauge, illustrated on the right in figure 3, has a scale beginning with zero and shows the load being placed on the alternatorgenerator. The loadmeter reflects the total percentage of the load placed on the generating capacity of the electrical system by the electrical accessories and battery. When all electrical components are turned off, it reflects only the amount of charging current demanded by the battery. A voltage regulator controls the rate of charge to the battery by stabilizing the generator or alternator electrical output. The generatoralternator voltage output should be higher than the battery voltage. For example, a 1. The difference in voltage keeps the battery charged. Hydraulic systems. There are multiple applications for hydraulic use in airplanes, depending on the complexity of the airplane. For example, hydraulics are often used on small airplanes to operate wheel brakes, retractable landing gear, and some constant speed propellers. On large airplanes, hydraulics are used for flight control surfaces, wing flaps, spoilers, and other systems. A basic hydraulic system consists of a reservoir, pump either hand, electric, or engine driven, a filter to keep the fluid clean, selector valve to control the direction of flow, relief valve to relieve excess pressure, and an actuator. The hydraulic fluid is pumped through the system to an actuator or servo. Servos can be either single acting or double acting servos based on the needs of the system. This means that the fluid can be applied to one or both sides of the servo, depending on the servo type, and therefore provides power in one direction with a single acting servo. A servo is a cylinder with a piston inside that turns fluid power into work and creates the power needed to move an aircraft system or flight control. The selector valve allows the fluid direction to be controlled. This is necessary for operations like the extension and retraction of landing gear where the fluid must work in two different directions. The relief valve provides an outlet for the system in the event of excessive fluid pressure in the system. Each system incorporates different components to meet the individual needs of different aircraft. A mineral based fluid is the most widely used type for small airplanes. This type of hydraulic fluid, which is a kerosene like petroleum product, has good lubricating properties, as well as additives to inhibit foaming and prevent the formation of corrosion. It is quite stable chemically, has very little viscosity change with temperature, and is dyed for identification. Since several types of hydraulic fluids are commonly used, make sure your airplane is serviced with the type specified by the manufacturer. Refer to the AFM, POH, or the Maintenance Manual. Figure 4 Basic hydraulic system. Landing gear. The landing gear forms the principal support of the airplane on the surface.