Beech king air 100 maintenance manual

 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
Second, a cabin temperature sensor allows the control unit to sense what the existing cabin temperature is. Similarly, a broken wire or a loose ground connection in the circuit will leave the avionics on. Some airplanes contain battery temperature gages, others contain a charge monitoring system.
 
https://akkpallsoft.website/views/article.php
https://akkpallsof21.online/index.php
https://abrendsoft.website/sitemap.xml
https://klodossoft.pw/views/
https://akkpallsoft.fun/views/article.php
https://klodossoft.pw/
https://akkpallsoft.fun/views/article.php
https://abrendsoft.website/images/news.gif

https://abrendsoft.website/images/news.png
https://klodossoft.online/article
https://akkpallsoft.fun/views/index.php
https://brekisoofg.site/views/
https://akkpallsoft.website/views/index.php
 

 

Beech king air 100 maintenance manual

 
Free Turbine vs.

 
https://klodossoft.pw/sitemap.xml
https://brekisoofg.site/views/
https://abrendsoft.website/sitemap.xml
https://brekisoofg.site/index.php
https://klodossoft.pw/index.php
https://abrendsoft.website/images/news.png
https://akkpallsof21.online/sitemap.xml
https://akkpallsoft.website/sitemap.xml
https://klodossoft.pw/article
https://akkpallsoft.fun/index.php
https://klodossoft.pw/views/
https://abrendsoft.website/images/news.png
https://klodossoft.pw/views/index.php
https://abrendsoft.website/views/index.php
 

Beech King Air Series Component Maintenance Manual (part# )

 
https://akkpallsoft.website/
https://akkpallsoft.fun/article
https://akkpallsoft.fun/article
https://akkpallsoft.website/views/article.php
https://klodossoft.pw/views/index.php
https://klodossoft.pw/
https://klodossoft.pw/
https://brekisoofg.site/views/index.php
https://abrendsoft.website/images/news.png
https://brekisoofg.site/views/article.php
https://abrendsoft.website/images/news.gif
https://klodossoft.pw/views/index.php
https://klodossoft.online/sitemap.xml
https://akkpallsoft.fun/article
 

Rules-of-thumb C. Introduction to specific Range SR calculations D. Propeller specifications and definitions B. System description and operation C. Normal procedures and tests D. Abnormalities and emergencies E. Synchronizer or synchrophaser operation F. System description and operation B.

Components which use pneumatic pressure C. Components which use suction D. Bleed air failure warning system if installed E. Normal and emergency procedures Special Equipment miscellaneous A. Engine fire detection and extinguishing B. System description B. Normal operation C. Abnormalities and emergencies Landing Gear System A. Position indication and warning systems B. Manual extension D. System specifications and definitions B. Users of power 1 Main generator buses and current isolation limiters 2 Subpanel and other buses 3 The 5-bus system if applicable D.

Normal operation E. AC power; inverter operation G. Avionics master power circuit Fuel System A. System specifications, definitions, and limitations B. Cockpit controls and gauges C. System layout-tanks, vents, drains D. Normal fuel flow to engine E. Crossfeed operation F. Fuel transfer operation G. Anti-icing equipment-description and operation 1 Engine auto-ignition 2 Engine inertial separators 3 Engine inlet heat 4 Windshield heat 5 Propeller heat 6 Pitot heat 7 Fuel vent heat 8 Stall warning heat 9 Fuel control heat 10 Fuel heat B.

Introduction, definitions, and specifications B. Pressure vessel openings door and emergency exit operation C. Air inflow system supercharger or bleed air D. Air outflow control system E. Cockpit and cabin controls B. System layout and airflow C. Heating and cooling componentscombustion or electric heater, Freon air conditioning, bleed air bypass valves D. Automatic system operation E. Manual system operation F.

Revisions and updating B. Limitations C. Normal checklists D. Emergency and Abnormal checklists E. Performance 1 Takeoff planning 2 Climb, cruise, descent 3 Instrument approach procedures-normal and single-engine F. Weight and balance calculations G. Handling and servicing section Installed avionics equipment Thank you for your feedback!

How do you rate the overall value of this course to you? What topics in this course should have been covered in more depth? What topics in this course were covered too deeply, or took too much time? What suggestions or comments do you have concerning: A. The instructor? Instructional techniques or methods? Handout materials? Physical classroom? Please add any other comments you would like to make in the space below or on the reverse side.

All branches of the U. Armed Forces use various versions of It under the designation C It will remain illuminated and flashing until it is “Pressed to Reset. Only then will it dim to the intensity level selected by the dimming rheostat.

If an additional fault occurs, all illuminated lamps revert to their brightest illumination level until the Fault Warning lamp is again pressed.

This serves as a reminder to place the propeller controls forward before using Beta or Reverse. The “Prop Sync On” light installed only with the Type 1, electromechanical system illuminates when the propeller synchrophaser switch is on and the right main landing gear is not up.

This serves as a reminder to turn prop sync off for takeoffs and landings. The later, Type II electronic system may remain on. What is the correct initial action to take when you first notice the red master fault warning light flashing?

Something’s wrong. What is it? Dimming of the annunciator panel lights for night flying is accomplished by: 5. After an engine is shutdown in flight due to very low oil pressure A. Which annunciator s will be illuminated? Which annunciator s may be illuminated? For some models this is a tricky question! You are taking off on a short runway which has a chain link fence, a ten foot tall concrete block wall, and a freeway overpass just past the runway end. When your airspeed exceeds 80 knots, you know that you cannot abort and remain on the runway.

The illumination of which red annunciator lights, if any would cause you to abort this takeoff when past 80 knots? This is the shaft horsepower rating, abbreviated SHP. Free Turbine vs. When the speed of the power section is increased or decreased – by moving the propeller lever – the speed of the gas generator remains constant; it changes only in response to power lever movement.

The total flow of fuel and air through engine remain basically constant at any propeller speed, so changing propeller speed does not affect ITT. In contrast, all rotating components in a fixed-shaft engine rotate together. The gearbox makes the rotating components for example, the turbine stages, the propeller, the generator, and the fuel pump – all turn at different speeds, but the speeds are all proportional. With less compressor speed, less airflow enters the engine and ITT will increase dramatically.

Before making any in-flight speed adjustment to the TPE, be certain the power lever has been reduced sufficiently to attain an ITT which can rise without exceeding any desired limit. Compression ratio is Twothirds of the power generated is used to drive the compressor; about one-third drives the gearbox and propeller. After the air enters the inlet – sometimes called the “smile” located on the lower front of the engine, it is compressed by a two-stage compressor and routed to an annular combustion chamber.

Fuel is injected into the combustion chamber initially by five primary fuel nozzles and later in the start sequence by ten secondary nozzles. The resultant gases expand from the combustion chamber passing through a set of stationary guide vanes or stators ensuring impingement on the turbine blades at the correct angle.

The still expanding gases pass through a second and third set of stationary vanes and turbine wheels. The three turbine wheels, on the same shaft as the compressor, drive both the compressor and the gearbox. The exhaust gases are then routed overboard through a curved exhaust duct. The gearbox, located in the front of the engine, provides speed reduction between the turbine shaft and the propeller shaft.

Thus, the reduction gear ratio is slightly over 20 to 1. The accessories driven by the gearbox: 1. Combination centrifugal-type boost pump and gear-type high-pressure fuel pump 3. Oil pressure pump and scavenge pumps 5. Tachometer generator 6. For example: T4. P3 is the pressure of the air discharging from the compressor.

That is, when torque is doubled, power is doubled. When faced with a single-engine approach, doubling your normal torque setting should yield similar performance. Bleed Air Uses Air from engine station number 3 – known as P3 air – is bled from the engine to be used by various engine or airframe components.

These systems are Engine fuel control unit FCU. The operation of the various FCU functions are pneumatically actuated. There is no bleed air shutoff for this system. Engine inlet heat. Cockpit control switches, left and right, select whether or not bleed air will be directed to the inlet lip of the cowling and to the inlet of the compressor to provide ice protection for the engine.

Environmental bleed air. This provides the cabin’s source of pressurization and most of its heating. P3 air is directed to a Flow Control Unit “Flow Pak” , where it mixes with ambient air and is then supplied to the cabin. Instrument bleed air. This air passes through a pres- sure regulator and is then used by various airframe components: the wing and tail deice boots and the door seal, for example.

The regulated air blows through an ejector, or venturi, which causes a suction to be created. Lubrication System The lubrication system is designed to provide a continuous supply of clean lubricating and cooling oil to the engine bearings, reduction gears, torque sensing system, and all accessory drive gears.

An external oil tank is located on the right side of the engine. A dipstick attached to the oil cap is provided for preflight. A popout button is located on the oil filter bypass valve, located above the oil cap, forward of the oil filter.

Extremely cold oil can cause the button to pop. Check it after the flight, and reset it if found popped. If the button pops again, or for no apparent reason, the oil filter should be checked for contamination.

Note: The button is virtually impossible to see or feel on the B without removing the upper forward engine cowling, making it virtually impossible to check during a routine preflight inspection. The unfeathering pump picks up oil from the oil tank, boosts it to a high pressure value, and sends it to the propeller where there is normal seepage back into the engine gearbox.

If the engine is not turning, no scavenge pumps are operating to return this oil to the tank. Thus, the oil tank will show an erroneously low reading after unfeather pump usage. In extreme cases, the tank can be pumped dry. Vigorous propeller rotation by hand can operate the scavenge pumps sufficiently to return the oil to the tank. Oil is typically changed every hours.

Oil-To-Fuel Heat Exchanger An oil-to-fuel heat exchanger, located in the oil tank, regulates the fuel temperature automatically when the engine is running to prevent freezing of water that is suspended in the fuel.

By so doing, fuel flow through the heat exchanger is temporarily stopped, thus providing increased fuel pressure to the engine while engine speed is low. Oil pressure prevents springs and counterweights from feathering the propeller. At shutdown, however, when oil pressure is lost, the blades must be prevented from feathering because a feathered propeller will give too much rotational load to the engine starter. This is unlike the free-turbine PT6 engine, in which the propeller is not connected to the compressor and starter.

In that engine, a feathered propeller provides no additional starting load, so no start locks are required. Small metal pistons or pins, housed within cylinders – one for each propeller blade – are driven by springs into position to prevent the blade from feathering.

These are the start locks. After the engine is idling properly, merely moving the power lever slightly aft of Ground Idle into Reverse will cause the blade angle to decrease enough to move away from the start lock. With the friction removed the lock slips outward, and now the blade angle will be free to reach any position requested by the pilot or the propeller governor.

As long as the start lock remains engaged, the blade will stay at the minimum-load position This action – which makes the propeller blade angle attempt to reach 8. This flat blade pitch will yield the maximum engine spooldown time for better cooling. Torque Sensing System A torque sensing system measures the twist of the torsion shaft connecting the rear of the turbine group to the high-speed pinion gear in the gearbox. It can sense both positive and negative torque.

Oil pressure, modulated by the torque sensor, sends a signal to a transducer for the torquemeter. Because the system can be as much as ft-lbs in error, cruise power is set by using ITT, not torque, for primary reference.

The other DCpowered engine gauges in the B fail to a zero reading when they lose power. Strangely enough, however, when the torque gauge loses power it will fail to its redline value, ft-lbs. Either the engine starter motor or a propeller creates negative torque.

Thus, negative torque occurs during engine starting and after in-flight flameouts. A different result occurs in flight because of this, however, than occurs during engine starting.

Let us explain. In flight, this sends the blade angle toward feather, reducing drag tremendously. As the blade angle streamlines with the relative wind, little negative torque remains and the NTS system stops dumping oil. As the propeller governor attempts to return the propeller to the selected speed, it causes blade angle to decrease until the windmilling propeller again exceeds the 20 HP negative torque threshold and NTS begins another cycle. Consequently, this is not an automatic feathering system but is instead an effective automatic drag-reduction system.

In an emergency, the pilot need not rush so quickly to feather that a mistake is likely. Instead, he can take his time so that feathering can be accomplished without hurrying.

During engine starting, the propeller start locks prevent any increase in blade angle when NTS activates. NTS must be checked prior to each flight. The harness they connect to sends a signal to a DC-powered compensating resistor which corrects the ITT reading, so that theoretically the indicated temperatures reach the same temperature limit when both engines reach their rated power limit.

The actual metering of the fuel flow is accomplished by regulating P3 air pressure in the FCU. Compressor inlet conditions, as sensed by a “P2T2” sensor, also affect fuel flow values to the engine. If this sensor becomes blocked with ice – very unlikely! Activation of engine inlet heat should cure the abnormality within approximately three minutes.

This device meters fuel flow to the engine when in the Ground mode of operation, when the Power Lever is aft of Flight Idle, to maintain the engine speed selected by the Speed Lever. As the Power Lever changes the blade angle in the Ground or Beta mode, the USG keeps engine speed constant by increasing fuel flow whenever propeller load increases, and decreasing fuel flow when propeller load decreases.

More often than not, however, the speed lever is all the way aft when the engine is operating on the ground. Similarly, when the power lever is moved behind Ground Idle into reverse, the USG reset function should cause its setting to be automatically increased to help prevent engine bog-down.

Thus, rarely does the pilot – during routine operation – have a chance to observe the true constant speed operation of the USG. The OSG may be tested after starting before the propeller start locks have been removed, when the Propeller Governor is rendered ineffective because of the fixed 2. If the coupling which drives the FCU should ever break, the result will be an unexpected increase in fuel flow to the maximum attainable value Thus the Beta range of blade angles expands as the Flight Idle low pitch stop “follows-up” the power lever position.

Because of this, the power lever should not be retarded while in the process of identifying a failed engine, since windmilling drag may increase. Fuel Control Unit The device, mounted on the engine-driven fuel pump, which in turn is mounted on the gearbox, which regulates fuel flow to the engine. Fixed-Shaft Engine A type of turboprop engine wherein all moving components – the gas generator section, the gearbox, and the propeller – are mechanically connected or fixed together and rotate at the same time.

Ground Mode Engine operational mode in which propeller pitch is hydro-mechanically controlled from the cockpit Power Lever. Also known as Beta Mode. Blade angle is automatically increased to a higher pitch to reduce airframe drag due to the propeller. Power Lever Cockpit lever used to change propeller pitch during Ground mode and to select fuel flow during Flight mode. Start Lock Mechanical latching device on each propeller blade used to maintain the propeller near flat pitch 2. Start locks prevent the propeller from feathering when prop oil pressure is lost at shutdown.

No feathering can occur when the start locks are engaged. Torque A force that produces a twisting effect. Underspeed Governor The flyweight operated fuel metering device, housed in the fuel control unit, that establishes engine speed during Ground mode of engine operation. This is the minimum angle which the propeller governor may select.

The lower line, referenced to the right side of the plot, shows typical fuel flows which are selected by the Main Fuel Valve or the Underspeed Governor, both parts of the Fuel Control Unit. Moderate taxi thrust??? All TPE’s have this feature. However, since some earlier TPE models did not, this is not a recommended procedure for pilots at any time. The aircraft buses only see the voltage of the left battery, approximately 24 volts. Batteries are connected in parallel.

Bus voltage should be approximately 24 Volts. Note: The batteries cannot be connected in series if an external power unit is connected, if a generator is on, or if the aircraft is in flight, left squat switch in Air position. Refer to the next page for a more complete discussion of the starting modes. The starter motor activates, spinning the engine. Speed switches do not function. The engine continues to accelerate to the selected idle speed, depending upon the position of the power and speed levers.

The change in engine indications implies that blade angle and engine load are changing, thus the locks have been released. Similar to the ground start cycle in many ways, the major difference is that the unfeathering pump actuates instead of the starter motor.

Thus, engine rotation is provided by the relative wind turning the propeller while the oil vent valve opens and the fuel anti-ice lockout valve closes. The engine continues to accelerate to flight idle speed. If the automatic air start cycle does not function properly, you may try to achieve a start by holding the Unfeather Pump switch on.

The primary use of the crank cycle is to remove residual heat before restarting an engine following a short shutdown period. As you view these schematics, make note of the direction in which the arrows are drawn. They will show that, under certain operating conditions, oil flow and blade angle change will occur in only one direction. Under other operating conditions, however, a modulating function allows oil flow and blade angle change to occur in either direction, as indicated by lines drawn with arrows on both ends.

Flight Mode In the Flight mode, or Propeller Governing mode, the Propeller Governor receives engine oil, boosts it to a higher pressure value with an internal pump, and regulates oil flow to the propeller. When the propeller experiences an overspeed condition, the governor responds by releasing oil from the propeller, causing the blade angle to increase.

Conversely, when an underspeed condition exists, the governor responds by sending oil to the propeller to decrease blade angle. Because the governor is modulating oil, its output pressure is less than psi and the Beta annunciator is not illuminated. The Propeller Governor is no longer modulating oil, but is sending all it can to the Prop Pitch Control in an attempt to rectify the underspeed condition.

The Prop Pitch control is now providing the modulation of oil Because the governor is not modulating oil, its output pressure is greater than psi and the Beta annunciator is illuminated.

The open Feather Valve releases prop oil and the blade angle increases, or goes toward feather. As the blade angle streamlines with the relative wind, insufficient negative torque remains to activate the Sensor, and the Feather Valve closes. No prop oil pressure exists until the Unfeather Pump operates. Normally the Beta annunciator will not illuminate because the Unfeather Pump does not usually create pressures in excess of psi. As prop oil is dumped to the engine, its pressure drops below psi, causing the NTS annunciator to extinguish.

Start Locks prevent the propeller blades from feathering, even though oil is released. Prop oil is dumped to the engine, allowing springs and counterweights to send the blade angle to feather. When the Unfeather Pump operates – triggered either by its own switch, the NTS Test switch, or by the initiation of an automatic Air Start cycle – pressurized oil is available at the Prop Pitch Control, where it may be sent to the propeller to bring the blades out of feather.

To guarantee that the Start Locks will be set on the ground, the power lever should be positioned aft of Ground Idle into Maximum Reverse, causing the Prop Pitch Control to request the most negative blade angle.

When prop oil pressure is above psi with the Unfeather Pump operating, the NTS annunciator should illuminate.

Each column is a separate limitation. The limits do not necessarily occur simultaneously. Turning off the battery and generator switches – thus eliminating all DC and AC electric power – will leave only one engine instrument operative for each engine.

Which one? Which two engine gauges are needed to compute shaft horsepower? Bleed air comes from engine station number , which is defined as the inlet. In addition to its routine purpose of cooling, cleaning, and cushioning bearing surfaces, the oil system also provides for What are the two methods or actions which create nega- tive torque, due to the gearbox driving the turbine shaft? If a propeller fails to engage its start locks at shutdown, and a restart is attempted with the blades having leaked part-way toward feather, what will likely result?

What steps must be taken to properly engage the pro- peller start locks if the locks were not successfully engaged at shutdown? Fifteen minutes after you taxi in and shutdown, you must start again. How should you initiate this start? What steps could have been taken to decrease the likeli- hood of the high ITT noted in the previous question?

When should the Prime or SPR function not be used? Your first action should be to The longest period of time that the ignition system may be operated continually is If you always start the right engine first, how can you verify that the left engine is supplying pneumatic pressure?

While conducting your Before Takeoff check, you ob- serve that the Suction gauge reads a normal value but that the Pneumatic Pressure gauge reads zero. What is probably wrong? A gyro suction gauge reading above the green arc may indicate a need for: 7.

Will the operation of the optional flight hour meter Hobbs Meter be affected if both left and right bleed air switches are simultaneously moved to the bottom position in flight? If so, how? Travel readings are taken at the leading edge. The neutral position is indicated by a pointer at the leading edge of the stabilizer with respect to a rivet on the aft fuselage. Travel of the stabilizer is controlled by the combination of two switches in the cockpit Power is supplied from one switch to an electrical actuator motor in the empennage that regulates the movement of the horizontal stabilizer; the other switch supplies the electrical ground for the motor.

The stops for the horizontal stabilizer are built into the actuator motor. An audio stabilizer movement system is installed to advise the pilot each time the stabilizer moves. The signal is in the form of intermittent tones which come through the speaker or headphone while the stabilizer is in motion.

This sound is independent of the radio system and will be heard any time the stabilizer moves. An out-of-trim warning system is installed to advise the pilot of a mistrim condition during takeoff. A squat switch on the right landing gear will deactivate the system on lift-off so that the trim can function in any position within its range, without the horn sounding.

This is a handy method for adding incremental drag during a visual approach. Here’s what to do. Keep your eye on the flap indicator as you move the switch to the DN position. The motor incorporates a dynamic braking system, through the use of two sets of motor windings, which provides a quick-stopping action and helps prevent overtravel of the flaps.

The gearbox drives four flexible driveshafts connected to jackscrews at each flap. The flaps are operated by a sliding lever located just below the condition levers on the pedestal.

They can be seen only when the flaps are extended. Maximum speed for Approach flaps is knots. Maximum speed for more than Approach naps is knots. The published idle power, Haps down, stall speed is cator by: knots, and is designated on the airspeed indi- 4. Stall speed with idle power, flaps up, zero bank angle, knots calibrated and 9, pounds weight is knots indicated airspeed. If these airspeed and values are multiplied by 1.

Which one is the proper “over the fence” landing speed? What is a likely cause of this malfunction? If so, how would you do it? Describe how you would retract flaps from Down to Ap- proach. The unit drives three jackscrew actuators, one at each main gear and one at the nose gear.

Dual windings in the motor form a dynamic braking system which, along with limit switches on the gearbox, prevent overtravel of the landing gear.

Torque tubes are used between the gearbox and the main gear actuators, while sprockets and roller chains are used to drive the nose gear actuator. A springloaded friction-type clutch in the gearbox is provided to prevent damage to the structure and drive mechanism, in the event of a drive malfunction. In addition, the system is protected from electrical overload by a current limiter or circuit breaker device located in the lower forward belly area.

A tug operator must take care not to exceed this limit, since doing so will cause damage to the system. The shock link also dampens the transmission of excessive shock loads to the rudder pedals. When retracted, the nose wheel is automatically centered and the steering linkage becomes inoperative.

Caution: Never tow the airplane while the rudder control lock is installed. It may damage the steering mechanism. Maximum speed for gear extension is knots. Maximum speed for gear retraction is knots. Maximum speed when the gear is extended is knots.

Describe the difference between a landing gear safety squat switch and a landing gear down lock switch. You perform an incorrect balked landing and – after add- ing power and props – leave the flaps down while you retract the gear Shuttle valves permit only one pilot – left or right seat – to operate the brakes at any one time. This retains the pressure in the brake lines. The parking brake is released by depressing the pilot’s pedals to equalize the pressures on both sides of the valve, then pushing the parking brake handle in to open the valve, followed by releasing the pedal pressure.

Brake Shuttle Valves Installed only with the “parallel” braking system The shuttle valve provides braking by the pilot or the copilot, not both together. Once braking has been initiated by one crew member, there is very little chance that the other crew member will be able to initiate braking until the first person releases the brakes entirely. This is due to the fact that the initiator has a much larger surface area of shuttle for his pressure to act against.

Be certain that both pilot’s agree upon who is doing the braking. If both pilots apply pressure simultaneously, one pilot may end up controlling the left brake while the other pilot controls the right brake! Beechcraft brake systems with shuttle valves except for BB through BB in the King Air series contain the parking brakes hydraulic check-valves in the pilot’s brake lines upstream of the shuttle valve.

This means that only the leftseat plot can set and properly release the parking brake. On a preflight, you notice that the left main strut is totally flat.

Should you start up and taxi to the shop? Where is the hydraulic fluid reservoir for the brakes? How can the pilot in the right seat set the parking brake? A vibration shortly after takeoff, which shakes the instru- ment panel for a few moments, is often an indication that:. Describe the procedure for conducting a wear check on the brakes.

The presentation is designed for those who believe that electricity, at best, is akin to some type of voodoo – magical and mysterious. We hope that our discussion here will dispel some of the darkness that surrounds this important subject. To the electrical engineers who read these notes forgive us when we err on the side of simplicity. Perhaps one reason why electricity is so mystifying is that what makes a motor turn or a light bulb illuminate cannot be seen by the naked eye: those electrons rushing through the wires are just too darn small!

On the other hand, the rotation of the water wheel down by the old mill stream is easily understood – the weight of the water flowing over the wooden buckets or blades causes the rotation. Similarly, when we open the tap of a water faucet, what happens is predictable and understandable: the more we open the spigot, the faster the water comes out, expelled by the pressure in the pipe.

We believe that electric power operation will be easier to understand If we compare it to the more familiar operation of water power. When you read the term voltage mentally replace it with pressure. For example, water doesn’t flow through a faucet unless there is a pressure difference across the faucet: more pressure in the pipe than in the sink.

Likewise, electrons don’t flow through a Nav light unless there is a voltage difference across it: more voltage at the input wire than at the output wire, or ground wire. An electrical ground is where electrons come from and return to. It is aircraft structure; what we ride in.

Likewise, water comes from and returns to the ground, the earth we stand on. Something has to motivate the water to leave the ground and flow to us. Sometimes a pond up on a hill will do the trick, but often we have to supply the motivation ourself, via an electric or mechanical pump. Similarly, a battery or a generator can motivate electrons to come to an electrical system component.

The battery like the pond has limited capacity, whereas the generator like the pump can keep on supplying electrons almost without limit. The term ampere abbreviated “amp” can mean gallons per hour gph since it represents a particular amount of current, a particular number of electrons which pass through a wire each second.

In fact, if the word “amp” were always replaced with the phrase “a certain huge number of electrons per second” the meaning would remain identical. Let’s see how this can work. Consider the following couple of sentences: “Within limits, the aircraft’s generators maintain a constant output voltage of However, If the generator is asked to supply a load in excess of amps, it is unable to maintain proper voltage.

However, if the pump is asked to supply a demand In excess of gph, it is unable to maintain proper pressure. Versions of the “water analogy” presented here have been used successfully for years in teaching electricity to many college classes. Try it. You’ll like it. Expressed in simpler terms, it ‘feels’ battery voltage. The B contains a “Dual Battery Start Control Panel,” a rather complicated device which allows the batteries to be combined in either a parallel or series manner.

Rarely used, the series set-up allows twice as much voltage to be available about 48 volts , but at the starter relays only. In actual practice, most operators have reported limited success using “Series” starts. While the Battery Select switch is in “Normal” the parallel set-up is activated, and the output from the batteries is at normal battery voltage but with twice the capacity. That is, instead of having a single battery which can provide 34 amps for one hour a 34 amp-hr capacity , we now have a combination of two batteries which has a 68 amp-hr capacity.

In the presentation of the B electrical system presented here, we will be using the normal, parallel, set-up exclusively. When the battery switch is turned on, the Battery Relay BR closes, allowing battery voltage to be present on all other buses as well as the Hot Battery Bus.

Readings of approximately 28 volts on both voltmeters verify proper EPU operation. Turning the battery on first allows the avionics master circuit to turn off the radios, saving them from any unexpected voltage transient which the EPU may give. The avionics master circuit will be presented later in this chapter of the Ground Training Notes. Keeping it on while the EPU is in use provides a buffering action to absorb voltage fluctuations caused by erratic EPU operation, and provides a back-up power source during the start in the event the EPU ceases operation.

Keep in mind that a hot start would begin to occur if all electric power were lost as an engine accelerates after light-off but before reaching self— sustaining speed! However, while using the EPU to operate the heater or air conditioner, making periodic checks of aircraft voltage – verifying that it is still 28 volts – is quite important. If the EPU ceases operation the batteries will begin to discharge rapidly. If voltage is not being monitored, there will be no immediate indication of this condition.

All B’s contain a 5 amp circuit breaker in the EPU receptacle, protecting the wiring to the external power relay. The external power relay will not close if the CB is tripped. Beginning with BE an external power overvoltage sensor was added which opens the relay if voltage exceeds approximately 31 volts, and the battery switch must be on before the external power relay will close. This light is triggered whenever battery charge current exceeds 7 amps for more than approximately 6 seconds.

If the right engine is at Flight idle instead of Ground Idle, the higher engine speed can cause so much current to be supplied by the right generator across the right amp current limiter that there is an excellent chance of blowing the limiter. Be certain the first engine is at Ground Idle before starting the second. The second engine start is usually significantly cooler than the first because the starter is driving the engine more effectively with generator voltage than with battery voltage alone.

Similarly, use of an EPU for starting, when convenient, is highly beneficial because of the higher voltage available. The choice of which engine to start first is not critical, and there are as many good reasons for alternating starts as there are for always starting the right engine first. They will “parallel” almost perfectly every time. With few exceptions, the main buses feed electric power to larger loads components which use more current and the other buses feed power to smaller loads.

The subpanel buses or left and right loops receive power from the main buses through “subpanel feeder” wires, as do the fuel panel buses. For redundancy, each bus is “dual fed” – it has two methods of receiving electric power. However, this is not always the case. Can you spot the three buses that are not dual fed? However, some individual components on these buses, such as fuel firewall shutoff valves, are dual fed since they receive power from both the Hot Battery Bus and from the Fuel Panel Bus.

Also, the No. Although a very rare occurrence, a ground fault is produced when some low resistance item that missing wrench? In the situation shown above, the sources of electric power two generators and the batteries feed into the shorted Right Loop through the bus feeder wires between the main buses and the loop. Each of these wires contains a 50 amp circuit breaker which should overheat and trip, breaking the path for electron flow.

In that manner, this bus is automatically isolated. These CB’s should not be reset in flight. The rush of electrons from the sources of power to the short will cause bus isolation to occur by overheating and tripping only one subpanel bus feeder CB, “LH 2”.

Since the really important fuel panel components are also being powered from the Hot Battery Bus, no major component has been lost, and there is no need to reset this CB until safely on the ground with maintenance personnel available. However, the flow of electrons from both the right generator and from the batteries must pass through the left current limiter, which overheats and melts to isolate the fault from these two sources of power.

The left loadmeter will show full load as the left generator continues to feed into the short, since there is no automatic protection against generator overload Overvoltage protection, yes. Overload protection, excessive current protection, no. When the crew notices the pegged out loadmeter, they should turn off the affected generator.

If the crew were to allow the generator to continue overloading for some time, the unit would likely overheat and cause its own eventual failure. Although the Generator Control Units provide protection against many undesirable things – overvoltage, reverse current – they do not provide overload protection. When it is stated that the generator is a amp unit, it is merely indicating the maximum value of current which the unit can provide, under proper conditions, without overheating and while still maintaining proper output voltage.

But if both generators fail or are turned off, then the batteries may discharge quite rapidly since they are the only remaining power source. To prolong the time before the batteries become totally discharged, all nonessential electrical components should be turned off.

This action will guarantee that neither the electric heater nor the air conditioner – both very high-load items – can operate, and also will terminate the 15 to 20 amp draw of the blower. Other high-load items include windshield heat and prop heat. By itself, the blown current limiter prevents the generator on that side from recharging the batteries: no particular problem, since the other generator is still capable of charging them.

All buses continue to receive 28 volts. However, when the failed current limiter is combined with a failed generator, then problems develop, as shown by the next examples.

The remaining generator, the operative one, cannot recharge the battery because it cannot “get to it” across the open current limiter. The situation presented on page 96 is easy to notice; in addition to the illumination of the ‘Generator Out’ annunciator, you may notice some failed avionics, and, when the voltmeters are checked, no voltage will be shown on the side with the open limiter. The situation described on page 97 is much harder to detect, because all systems will continue functioning until the batteries are so depleted that they cannot supply sufficient current.

The key to recognizing this double failure is that there will be a slight difference between the voltmeter readings. The voltage on the side of the failed generator will be coming from the batteries only, through the good limiter. When voltmeters are checked following the generator failure, it takes a careful eye to notice that one meter reads slightly below normal.

To summarize, both voltmeters should read normal voltage, 28 volts, following a generator failure. If they do not, a current limiter is open, and a landing should be made as soon as practical to fix the two problems that exist: generator failure and current limiter failure. Also, keep in mind that a generator failure often means a starter failure as well, so where you shutdown may be where you sit until a replacement unit is installed. Current Limiter Check Procedures If battery voltage can be observed on both voltmeters, without generators on, then both current limiters are intact.

Make this easy check before every start, and after every shutdown right before the battery switch is turned off. Checking voltage on the side of an operating generator is not a valid current limiter integrity test.

Additionally, since most current limiter failures occur during a generator-assisted start of the second engine, verify that both voltmeters show 28 volts before turning on the second generator. Therefore, the nominal battery voltage is 1. The battery is considered to be discharged when its terminal voltage equals 1.

Unlike lead-acid batteries, there is no way of determining the precise state of charge of nickel-cadmium batteries without discharging the battery at a known current rate, checking the time for discharge, and then calculating what the state of charge had been.

Since terminal voltage will remain almost constant over a wide range of charge levels, its measurement will not provide a valid indication.

If the current is decreasing, then the battery is charging normally and the light should eventually extinguish. However, if the current is increasing, then a problem exists: the NiCad battery has a damaged cell or cells within it, and has begun to experience a “Thermal Runaway”. If it is allowed to continue to receive charge, the charge current will increase at a faster and faster rate, causing lots of heat and gas generation, until a very hazardous situation may develop.

In some cases, explosion and fire have followed a severe thermal runaway. The FAA has mandated that all NiCad batteries be monitored for thermal runaway with a system to alert the crew of the condition.

Some airplanes contain battery temperature gages, others contain a charge monitoring system. The King Airs with factoryinstalled original equipment, or Beech retrofit kits, use charge monitoring, not temperature monitoring, since the charge system provides an earlier, more reliable, warning in their opinion.

Whenever you are concerned about a battery – because the light takes too long to extinguish after starting or because it comes on in flight – conduct a battery charge verification procedure as described in the abnormal procedures checklist. This involves turning the battery switch off while monitoring the loadmeters. A significant decrease in generator load, as the generator continues to supply other loads but stops charging the battery, indicates that the battery is taking a lot of current.

This is not cause for alarm if it is soon after starting, but if it continues over the next few minutes, with the charging current getting larger, then the early stage of a thermal runaway has been detected and the battery switch should be left off. Turn it back on momentarily when operating gear and flap motors for landing.

The single inverter selector switch contains two separate poles internally. It selects No. The inverter Select Relay is only energized when inverter No. When No. The Inverter Control CB’s are located on the cockpit pedestal. This circuit is designed to be “fail-safe,” meaning that typical failures of the circuit will allow the radio equipment to continue operating. To achieve this design goal, the avionics power relays were chosen to be the Normally-Closed type: spring-loaded closed, electric current required to open.

You will notice that no current is flowing to the relays when the switch is on, the circuit being broken when the switch is in that position. Similarly, a broken wire or a loose ground connection in the circuit will leave the avionics on. Conversely, in the extremely rare case in which the Avionics Master switch develops an internal short – keeping the circuit closed at all times – the relays are energized open and the radios lose power.

But all is not lost! By merely tripping the Avionics Master circuit breaker the pilot can break the control circuit, the relays will close, and avionics power will be restored! The discussion of external power which was given earlier in this section taught that the battery switch should be on before the external power unit is turned on. One reason for this involves the circuit we are now examining.

Notice that when the aircraft is sitting on the ramp before start, with all electric power off, the avionics relays are closed. No power is reaching the radios, however, since the main buses are still “dead”. When the battery is turned on, a momentary application of battery voltage reaches the avionics in the split second it takes for the avionics relays to energize open.

History proves that this mild little “zap” is benign, causing no radio harm. Now suppose that one day a malfunctioning EPU were putting out high voltage. If the battery has not been turned on first, then the zap the radios experience Will be at this excessive voltage level, increasing the chance for damage. Remember: turn the battery switch on before the external power unit is turned on.

For example, when the “Prop Sync” CB is pulled by someone or trips open automatically, the propeller synchrophaser system stops operating. Some breakers, on the other hand, serve multiple and often obscure functions. If one of these breakers should trip in flight more than one result will occur.

Although the breaker served Its purpose by opening and thereby preventing excessive temperature rise caused by excessive current flow in some circuits not only is that circuit protected but any other circuits connected to that particular breaker are also without power and disabled. The listing presented here will provide help in knowing what to expect if certain CB’s trip.

A useful analogy can be made by comparing the work- ings of an aircraft’s DC electrical system to the workings of a water supply system in a house. Match the following words or phrases with their best counterparts. When you turn on the battery switch to check your fuel quantity before start, you notice that the right fuel gauge reads zero and the right fuel pressure annunciator is not on. Describe the likely cause of these discrepancies. You had started the right engine first, and you observe that the loadmeters show a marked difference just after starting, with the left generator carrying much more load than the right.

That is, the “generator paralleling” is poor. This may indicate that. To troubleshoot this malfunction, describe what you would do.

What should you do now? Which circuit breakers are you NOT to reset in flight? You have secured the right engine in flight. The right load. With The right voltmeter should now read volts. Your airplane has experienced a double generator fail- ure. It is night, you are in the clouds above the freezing level, and you cannot begin descent for about another 30 minutes because of terrain considerations.

Discuss what you will do to prolong the time remaining before the battery is completely discharged. Less than six gallons are unusable. When filled with Jet A fuel at a typical density of 6.

In round numbers, you have 2, pounds when the main tanks are full and an extra pounds when the aux tanks are full. Figure 1: Tanks and filler caps.

To reduce wing bending stress, the main tanks should be filled first and consumed last. There is a handy and easy method of converting pounds of jet fuel to gallons when the density is 6. Simply add half of the pounds to itself. Or, expressed another way, multiply the number of pounds by 1.

The answer you obtain is the number of gallons So move the decimal point one space to the left divide by 10 and you will have the final answer. Then order gallons. You are burning pounds per hour in cruise today? You shut down with pounds remaining on each side and you told the FBO to “fill the mains?

Do not put any fuel into the auxiliary tanks unless the main tanks are full. If fuel is in the auxiliary tank, it must be depleted before using fuel in the main tank. Do not take off if fuel quantity gauges indicate in yellow arc or less than pounds of fuel in each main tank.

Buy It Now. Add to cart. Looks like we’re having trouble connecting to our server. Refresh your browser window to try again. Refresh Browser. An error occurred, please try again. Does not ship to Finland See details for shipping. Located in: Bumpass, Virginia, United States. Seller does not accept returns See details – for more information about returns.

Report this item Report this item – opens in new window or tab. About this item. This translation tool is for your convenience only.

The accuracy and accessibility of the resulting translation is not guaranteed. Note: The accuracy and accessibility of the resulting translation is not guaranteed. Seller assumes all responsibility for this listing. Item specifics. Seller Notes:. Issued May 28, Original manual, not a copy. Loose Leaf in Original Binder. Aircraft Type:. Twin Engine.

Aircraft Maintenance:. Maintenance Manual. Beech Aircraft Corporation. United States. Shipping and handling. Item does not ship to Finland. Item location:. Bumpass, Virginia, United States. Ships to:. Change country: -Select- United States. Sales Tax for an item