RAZBAM Metroliner III SA227-BC, Flight Manual

Page 1: ...RAZAIR A1 METRO III AFM 001 RAZBAM FLIGHT MANUAL TURBOPROP MODELS Metroliner III SA227 BC AIRCRAFT ...

Page 2: ...rett engines Ultimately a stretch of the Merlin III was designed sized to seat 22 passengers and called the SA226 TC Metro Because FAA regulations limited an airliner to no more than 19 seats if no flight attendant was to be carried the aircraft was optimized for that number of passengers The standard engines offered were two TPE331 3UW turboprops driving three bladed propellers The Metro and Metr...

Page 3: ...l 1 19 7 Fuel System 1 34 8 Fire Protection System 1 36 9 Pneumatic System 1 37 10 Hydraulic System 1 37 11 Landing Gear 1 38 12 De Icing System 1 39 13 Lighting System 1 39 SECTION 2 AVIONICS 2 1 1 Communications and Navigation 2 2 2 EHSI Electronic Horizontal Situation Indicator 2 8 3 TCAS Traffic Collision Avoidance System 2 14 4 GPS Freeflight 2000 Approach Plus 2 15 5 Autopilot 2 24 SECTION 3...

Page 4: ...nding 4 7 m After Landing 4 7 n Stopping Engines 4 7 2 System Checks and Operation 4 7 a NTS System 4 7 b Start Locks 4 7 3 Speed Reference Cards 4 8 a 10 000 lbs 4 8 b 10 500 lbs 4 8 c 11 000 lbs 4 8 d 11 500 lbs 4 9 e 12 000 lbs 4 9 f 12 500 lbs 4 9 g 13 000 lbs 4 10 h 13 500 lbs 4 10 i 14 000 lbs 4 10 j 14 500 lbs 4 11 k 15 000 lbs 4 11 l 15 500 lbs 4 11 m 16 000 lbs 4 12 ...

Page 5: ... RAZBAM Metroliner team Ronald Zambrano Team Lead Tim Taylor Metal 2 Mesh 3D Modeler José Valdez 3D Modeler Hank Essers Texturizer Larry Zambrano Gauge Coder Bernt Stolle FDE Developer Aaron Swindle Sky Song Soundworks Sound Developer Adam T Researcher Dan M Researcher Lorenz B Researcher and Tester ...

Page 6: ...er as follows 1 Go to the RAZBAM_MetroIIIC folder in the Gauges folder of your FSX Prepar3D installation 2 Select the RM3_RSET xml file 3 Edit the file using a text editor like NotePad 4 To enable a realism setting change the value to 1 To disable it change it to 0 5 The values to edit are a Start Locks RM3_START_LOCKS b Overtemp RM3_ENG_OVERTEMP_FAIL c Overtorque RM3_ENG_OVERTORQUE_FAIL 6 Leave a...

Page 7: ... The following is a chart of the different switches and knobs found on the cockpit and how to navigate them Switch Type Navigation 2 Position Switch Left Click changes the position 3 Position Switch Left Click moves forward Right Click moves backwards Example Left Click ALTER AUTO DP PRIM Right Click DP PRIM AUTO ALTER Multi position Knob Left Click moves forward Right Click moves backwards In som...

Page 8: ...ects CONTROL YOKES In normal conditions the placement of the control yokes hinder access to the switches panel that are located just behind them In the real aircraft both the pilot and copilot has to reach behind them to actuate these switches something that is not possible in the simulation To allow an easier access to the switches panel the yokes can be hidden revealed by clicking on two hot spo...

Page 9: ...y become visible as soon as the button is released SPEED LEVERS The speed levers position prevents access to the engine SYNCROPHASER Switch and makes more difficult reading certain gauges Like the throttle levers there is a visibility control hot spot that will hide reveal these levers Unlike the throttle hot spot the levers will remain hidden until you either click on the hot spot again or on the...

Page 10: ...TAIN The curtain that separates the cockpit from the passenger cargo deck can be hid shown by clicking on the following elements By clicking on the curtain itself By clicking on the fire extinguisher By clicking on the no smoking seatbelt sign ...

Page 11: ...Honeywell TPE 331 turboprops with continuous alcohol water injection AWI Each engine uses a four bladed McCauley 4HFR34C652 or Dowty Rotol propeller GENERAL CHARACTERISTICS Capacity Dimensions Performance Crew 2 Length 59 ft 4 in Max take off weight 16 000 lb Passengers 19 Height 16 ft 8 in Max Altitude 31 000 ft Cargo Volume 143 5 sq ft Wingspan 57 ft Max Speed 246 knots Max weight 8 700 lb Wing ...

Page 12: ...RAZAIR A1 METRO III AFM 001 1 1 AIRCRAFT CONTROLS ...

Page 13: ...e RPM d Engine Fuel Flow e Engine Oil Temperature Pressure f Fuel Quantity g Fuel Pressure 8 Flight Control Gauges a Outside Air Temperature b Elevator Trim Position Indicator c Flaps Position Indicator d Hydraulic Pressure e Landing Gear Position Indicator 9 Left Hand Communication Panel a VHF 1 b NAV 1 c ATC Transponder 10 Right Hand Communication Panel a ADF 1 b NAV 2 c VHF 2 11 Left 6 Right Ha...

Page 14: ...er f DC Bus Ammeter g Nose Gear Steering System Panel h Engine Start System Panel i Cabin Pressurization Controls 2 Left Essential Buss Breaker Panel 3 Left Hand Essential Bus Transfer Switches 4 Miscellaneous Controls a Cargo Door Control Panel b Copilot Flight Instruments Light Knob 5 Right Essential Buss Breaker Panel 6 Non Essential Buss Control Switch 7 Non Essential Buss Breaker Panel 8 Righ...

Page 15: ...ight Hydraulic Fluid Cutoff Switches 9 SAS Clutch Servo Switch 10 Aux Elevator Trim Switch 11 Yaw Damper Switch 12 Rudder Trim Wheel 13 Aileron Trim Knob 14 Cockpit Light Switches a Glareshield Lights Accessible from the pilot position b Console Backlight c Center Instruments Accessible from the copilot position 15 Propeller Synchrophaser Switch 16 Gust Lock Lever 17 Throttle Friction Lock Lever 1...

Page 16: ... A stripped needle that indicates maximum airspeed based on aircraft altitude 3 Three thumb indicators that rotate to display a White Minimum speed for aircraft control b Yellow Minimum speed for safe climbing c Blue Maximum speed for landing gear operation The maximum operational speed up to 17 800 feet is 246 Knots Above that altitude the maximum operational speed will be the following Altitude ...

Page 17: ...ude above ground level AGL from 0 up to 2 500 feet The OFF flag appears in two occasions a When the aircraft AGL altitude exceeds 2 500 feet and b when the radar altimeter has no power The radar altimeter also has a Minimum AGL Altitude Selector and Indicator This feature warns the pilot whenever the aircraft AGL altitude is below the selected AGL altitude by illuminating a warning light in the up...

Page 18: ...VOIDANCE SYSTEM SAS The Metroliner III is equipped with a stall avoidance system SAS which is armed at liftoff and disarmed as speed increases Fig 10 SAS Gauge Fig 11 SAS Test Overhead Panel Fig 12 SAS ON OFF Switches Fig 13 SAS Servo Switch ...

Page 19: ...g in the SAS vanes A green SAS DEICE light will illuminate indicating that SAS heat has been selected M850 CHRONOMETER Both the Pilot and Copilot have a M850 chronometer among their instruments These chronometers are independent of each other although they keep the same time The chronometers provide the following information 1 UTC Time default also known as ZULU Time 2 Local Time 3 Elapsed Flight ...

Page 20: ...CH TRIM There are no trim tabs on the elevators pitch trim is accomplished by moving the entire horizontal stabilizer On the real aircraft pitch trim is controlled by two buttons located on both control yokes not modelled There is an auxiliary trim switch located on the pedestal marked AUX TRIM Left or right clicking on this switch will provide UP or DOWN pitch trim Fig 15 1 Stabilizer position is...

Page 21: ...ugh two independent bus systems Fig 21 Battery and generator switches DC POWER DC power supplies basic electrical power for the airplane This system consists of two starter generators one in each engine two nickel cadmium batteries and a ground power unit BATTERIES Three position switches one for each battery are located on the left switch panel They are labeled BATTERY L or R OFF and RESET Fig 21...

Page 22: ... TEMP IND TEST Fig 23 1 and RANGE EXTEND Fig 23 2 Temperatures between 50 and 100ºF can be read by clicking on the RANGE EXTEND switch This switch adds 50ºF to the battery temperatures and displays the results The actual temperature will be the scale reading minus 50ºF GENERATORS Two engine driven generators mounted on each engine are the airplane s primary source of DC power Each generator output...

Page 23: ... selected POWER DISTRIBUTION Aircraft power is distributed through three DC and four AC busses DC power is distributed through the Left Essential Bus LEB the Right Essential Bus REB and the Non Essential Bus NEB Both the LEB and RB are limited to 225 amperes while the NEB is limited to 150 amperes The LEB is located in the left console The REB and NEB are located in the right console Each bus is c...

Page 24: ...cuit breaker as well as the 26 VAC busses Consequently either inverter provides power to all four AC busses MASTER WARNING SYSTEM The master warning system consists of an annunciator panel a valve position annunciator panel and various other lights Most lights are located on the annunciator panel An illuminated light alerts the pilot to a system malfunction red a system operating parameter amber o...

Page 25: ...e switch will check all the warning system lights ANNUNCIATOR REASON FOR ILLUMINATION Illuminates only during test Excessive temperature is detected in associated engine nacelle Cabin door not properly closed A battery ground fault has been detected Oil pressure is below 40 psi Hydrauilic pump pressure is low Cargo door not properly closed Cabin altitude is above 10 000 feet One of the main gear d...

Page 26: ...ceptacle The indicated battery is disconnected SAS Servo switch is disconnected The indicated SRL computer is not working Normal with less than 80 rpm The indicated 115 VAC bus is deenergized The indicated generator is not working Nose Wheel Steering system is disconnected The indicated SAS system is disconnected R BETA LOW SUCTION L CHIP DET R CHIP DET L XFER PUMP R XFER PUMP GPU PLUG IN L BAR DI...

Page 27: ... is active The SAS heating system is operating VALVE POSITION ANNUNCIATOR PANEL The valve annunciator panel Fig 29 is located on the instrument panel above the main annunciator panel These lights are tested with the main annunciator panel PRESS TO TEST switch ANNUNCIATOR REASON FOR ILLUMINATION Engine fuel shutoff valve is closed The engine hydraulic shutoff valve is closed The fuel crossflow valv...

Page 28: ...EXT TEST switch is actuated The FIRE EXT TEST is good OIL COOLER INLET DUCT HEAT CYCLE LIGHTS The heat cycle lights for oil cooler inlet ducts are located on the left forward side console ANNUNCIATOR REASON FOR ILLUMINATION Indicated oil cooler inlet duct anti ice thermostat is operating to heat the oil cooler inlet duct FUEL BYPASS LIGHTS The fuel bypass lights are located on the pilot s instrume...

Page 29: ...RAZAIR A1 METRO III AFM 001 1 18 DOOR UNSAFE SWTICHES NORMAL The cargo door is not closed or safe The door handle is in the open position and the click clack warning switches are operating correctly ...

Page 30: ... Garret AiResearch and are designated TPE 331 The engines incorporate a factory installed alcohol water injection system AWI The TPE 331 is dry rated at 1 000 shp for takeoff and continuous operation It is wet rated at 1 100 shp for a maximum of five minutes from the start of takeoff roll Fig 31 Engine Stations Major Sections and Fuel Flow The engine systems include the following Instrumentation S...

Page 31: ...ates the fuel bypass to maintain engine temperature at safe levels Engine torque marked in percentage of torque from 0 to 120 100 is equal to the maximum continuous rating of 1 000 shp at 100 rpm RPM the engine rpm gauges are calibrated in percentage of maximum continuous rpm which is 100 Fuel Flow calibrated in pounds per hour Fuel Quantity calibrated in 100s pounds Engine Oil Pressure calibrated...

Page 32: ...ust Gas Temperature ATTENTION Maximum Operational EGT is 6500 C Fig 34 Propeller Torque ATTENTION Torque increases at lower Propeller Speeds Fig 35 Engine RPM Fig 36 Engine Fuel Flow Fig 37 Engine Oil Pressure and Temperature Fig 38 Fuel Quantity ...

Page 33: ...The speed switching functions of the SRL include 1 Automatic control of the start sequence from 10 to 60 rpm 2 SRL EGT computation above 80 rpm and 3 Enabling CAWI operation and EGT temperature limiting above 90 rpm The automatic start fuel enrichment modulates the start fuel enrichment valve to provide an appropriate amount of fuel during the start The SRL EGT computation results in an indicated ...

Page 34: ...t contains an underspeed governor an overspeed governor and manual control of fuel metering The underspeed governor operates to prevent the rpm from going below a value set by the speed lever If engine speed should decrease below the selected setting the underspeed governor increases the fuel flow to oppose the speed decrease The underspeed governor can be set between 71 and 97 rpm by the speed le...

Page 35: ...uminated below 805 rpm if a SRL OFF light is illuminated when rpm is over 80 a malfunction is indicated TEMPERATURE LIMITER SYSTEM The system consists of a temperature limiter and a fuel bypass valve The system functions automatically to limit EGT to 6500 C by opening the fuel bypass valve and bypassing metered fuel back to the fuel pump The temperature limiter is integrated with the SRL computer ...

Page 36: ...es Fig 47 Ignition System Switches Location The ignition system is controlled by two switches on the left console labeled AUTO CONT IGNITION The AUTO position default position allows the SRL Autostart computer to control ignition during start An additional feature of the AUTO position is that it energizes the ignition if the negative torque sensing NTS system is activated Engine failure or flameou...

Page 37: ...ure power lever and speed lever position to maintain a selected rpm Moving the power levers behind the FLT IDLE 10 throttle will turn on a light marked L BETA or R BETA indicating that the propeller is ready for full reverse operation FEATHERING The feathered angle of the propeller is the angle that produces minimum drag Clicking on the ENGINE STOP AND FEATHER control Figure 45 shuts off fuel and ...

Page 38: ...ing flight results in loss of positive torque and the windmilling propeller produces negative torque which results in drag that decreases performance and increases yaw The engine has a negative torque sensing NTS system that provides for automatic drag reduction without any action on the pilot s part It is NOT an autofeather system but rather a system that increases blade angle to reduce windmilli...

Page 39: ...orward of the FLT IDLE propeller pitch control is provided by the speed levers The power lever can move freely between HIGH full forward and FLT IDLE positions It is not possible to move aft of FLT IDLE while the aircraft is in the air SPEED RPM LEVER Two speed levers operate in a quadrant on the center pedestal which is marked RPM HIGH forward and LOW aft The speed lever connects to the propeller...

Page 40: ...the power lever is aft of GROUND IDLE the propeller is developing reverse thrust Movement of the speed lever between high and low rpm adjusts the propeller governor During flight propeller governor rpm should be set at either 97 or 100 with the speed lever Normally 100 rpm is used for climb and 97 is used for cruise Prior to landing the speed lever is moved forward setting the propeller governor a...

Page 41: ...GROUND IDLE NOTE The only way to put the power throttle levers below FLT IDLE is by using the keyboard FSX P3D limits the movement of the throttle to 0 in the cockpit Reverse thrust is only achieved by going below 0 into negative throttle values CAUTION Attempted reverse with the speed levers below the HIGH rpm position may result in engine overtemperature condition NOTE a It is recommended that t...

Page 42: ...t as described in the Abnormal Procedures Section 1 The SPEED SW SELECT must be in OFF prior to a manual start 2 After clicking on the START button the SPEED SW SELECT switch is moved to the MANUAL position as the rpm reaches 10 3 After engine rpm has stabilized return the SPEED SW SELECT switch to the AUTO position Fig 52 POWER SW SELECT Switch Fig 53 POWER SW SELECT Switch location ABORTED START...

Page 43: ...OUS ALCOHOL WATER INJECTION CAWI The CAWI system is used during takeoff to recover power lost at high density altitudes The CAWI system includes a storage tank in the nose section two pumps and a spray ring and nozzles in the engine inlet CAWI may be used only for takeoff and for a maximum of five minutes In flight use of CAWI is prohibited The CAWI storage tank holds 16 gallons of usable SWI flui...

Page 44: ...nd an unmarked center OFF position fig 56 Fig 56 CAWI Control switches Fig 57 CAWI control switches location INDICATION Two annunciator lights marked AWI No 1 PUMP ON and AWI No 2 PUMP ON are illuminated whenever the associated AWI pump is running ad developing acceptable pressure If the WATER INJECTION switch is OFF holding the AWI PUMP TEST switch to the No 1 or No 2 position should turn on the ...

Page 45: ...met FUEL SYSTEM The fuel system consists of the fuel storage and vent fuel transfer and engine feed and indicating systems The total usable fuel capacity is 4 342 pounds 648 US gallons at 6 7 pounds per gallon FUEL STORAGE The fuel storage consists of two integral wet wing tanks and a vent system Fig 58 Fig 58 Fuel Storage tanks FUEL TRANSFER AND ENGINE FEED SYSTEM Fuel to each engine is supplied ...

Page 46: ...shutoff valve in the wheel well that is controlled by the FUEL SHUTOFF switch on the center console Fig 59 These normally open valves allow fuel to pass to the engines The amber L or R FUEL shutoff valve light illuminates when the respective valve is closed FUEL QUANTITY INDICATOR The FUEL QTY gauge Fig 38 on the instrument panel is calibrated in pounds x 100 This gauge is equipped with two pointe...

Page 47: ...RE light turns off when the fire condition disappears The PRESS TO TEST switch on the annunciator panel checks that the FIRE lights work as intended ENGINE FIRE EXTINGUISHING Each engine nacelle contains a fire extinguisher bottle their activation is controlled from the cockpit by using the fire extinguisher control assembly by means of a covered three indicator switchlight To activate the fire ex...

Page 48: ...ruments b the suction phase of the deice boots and c control of the pressurization system An amber LOW SUCTION warning light illuminates if the suction drops below limits The suction indicator on the instrument panel is direct reading and does not require electrical power HYDRAULIC SYSTEM The main hydraulic system is pressurized by two engine driven pumps one on each engine The system provides pre...

Page 49: ...dard braking system is manual LANDING GEAR The landing gear is controlled by the LANDING GEAR LEVER located in the center console Clicking on the lever will rise or lower the landing gear The LDG POS indicator will display landing gear position Fig 65 Landing Gear Lever Fig 66 LDG POS indicator test Fig 67 LDG POS indicator transition Fig 68 LDG POS indicator gear down Green lights indicate that t...

Page 50: ...lets are heated by hot bleed air tapped from the engine The propellers pitot tubes and SAS vanes are electrically operated The deicing system switch board is located in the left hand instruments panel LIGHTING SYSTEM EXTERIOR LIGHTS Exterior lighting consists of navigation rotating beacon wing ice landing taxi strobe logo and recognition lights The exterior lighting system is equipped with Five na...

Page 51: ... of general illumination of the instrument panel overhead floodlights pilot and copilot instruments lights engine and auxiliary instruments lights map lights and console and pedestal lights Pilot and copilot flight instrument lights are controlled by individual dimmers on the left and right forward consoles Fig 71 PIlot s Instruments lights control Fig 72 Copilot s instruments lights control The f...

Page 52: ...e to activate the exterior and interior lights by using the standard keyboard commands and or external control boxes Since the aircraft uses three position rocker switches instead of simple ON OFF toggles a special code was required that cannot be handled from outside the virtual cockpit ...

Page 53: ...RAZAIR A1 METRO III AFM 001 2 1 AVIONICS ...

Page 54: ...the main instruments panel divided in Left Hand and Right Hand sets Fig 74 Communications and Navigation instruments panel The left hand panel is used by the pilot and contains the following instruments from left to right Audio control panel VHF1 Receiver Transmitter NAV1 Receiver ATC Transponder The right hand panel is used by the copilot and contains the following instruments from left to right ...

Page 55: ...requency display 6 Standby frequency display OPERATION The units are OFF by default to turn them ON click on the OUTER Power Volume knob The display will appear and the unit will be ready for operation To change a frequency click on the outer knob to change whole values in the 118 to 136 range Clicking on the inner knob will change values in the 0 000 to 0 975 range To switch between the Active an...

Page 56: ...ency display OPERATION The units are OFF by default to turn them ON click on the OUTER Power Volume knob The display will appear and the unit will be ready for operation To change a frequency click on the outer knob to change whole values in the 108 to 117 range Clicking on the inner knob will change values in the 0 000 to 0 975 range To switch between the Active and Standby frequencies click on t...

Page 57: ...elector knob as follows Outer knob Left Click to change the 1000s number group Right Click to change the 100s number group Inner knob Left Click to change the 10s number group Right Click to change the 1s number group ADF RECEIVER The aircraft has one ADF receiver It is capable of receiving in the FSX Prepr3D assigned frequency range of 100 0 to 1799 9 KHz The displays for the ADF receivers are ba...

Page 58: ...ondary Information Label 6 Distance in nautical miles to selected DME Station OPERATION The unit is OFF by default to turn it ON click on the Power Switch The display will appear and the unit will be ready for operation The unit will always display the distance in nautical miles to the selected DME station Click on the CHNL switch to change between DME1 and DME2 Click on the MODE switch to change ...

Page 59: ...r the DME IDENT Morse code g ADF1 Enables audio reception for the ADF1 IDENT Morse code h ADF2 Enables audio reception for the ADF2 IDENT Morse code i MKR Enables audio reception for MARKER Beacons signals 2 MICROPHONE a VHF1 Selects VHF1 for radio transmission b VHF2 Selects VHF2 for radio transmission OPERATION All AUDIO functions except for the VHF1 and VHF2 reception switches work as a toggle ...

Page 60: ...e copilot have their own individual EHSI They can be configured independently but all navigation data is shared Fig 81 PIlot s EHSI Display and Control panel Fig 82 Copilot s EHSI Display and Control panel Fig 83 EHSI Display Fig 84 EHSI Control panel The EHSI will display data from the following instruments ATTENTION It is not possible to deselect the audio output for the VHF1 COM1 radio Clicking...

Page 61: ...FM 001 2 9 NAV1 and NAV 2 receivers DME1 and DME2 GPS ADF1 Directional Gyro TCAS EHSI DISPLAY The EHSI has three display areas The primary display area the upper display area and the bottom display area Fig 85 EHSI Display ...

Page 62: ...yed depends on the navigation source VOR DME or GPS but it will include bearing distance and indicated airspeed The upper area also displays Coordinated Universal Time UTC true airspeed TAS ground speed GS wind speed WS and wind direction WDR BOTTOM DISPLAY AREA The bottom display area indicates if TCAS information is being displayed and the selected moving map TCAS range DATA COLOR CODING Alphanu...

Page 63: ... data modes you have to click on the DATA MODE switch which is locate above the AUDIO CONTROL PANEL Fig 86 Data Mode selector switch Fig 87 NAV Mode selected Fig 88 GPS Mode selected Fig 89 Data Mode selector switch location SELECTING PRIMARY NAV SOURCE The Course Pointer is driven by the selected Primary Nav Source which can be either the NAV1 or NAV2 receiver To select which receiver is the prim...

Page 64: ...tified by its green color DG2 Selects NAV2 as the primary nav source for course pointer It can be easily identified by its blue color BEARING POINTERS FOR NAV1 NAV2 The EHSI provides two independent bearing pointers which function in the same way as a traditional radio magnetic indicator RMI for both the primary and secondary nav sources NAV1 Course Pointer NAV1 Bearing Pointer NAV2 Bearing Pointe...

Page 65: ...screen area for the map data Fig 94 360 Degree view mode Fig 95 ARC view mode The view can be changed by clicking on the corresponding button in the EHSI control panel To select the 360 degree view click on the HSI button To select the ARC view click on the ARC button DISPLAYING THE MOVING MAP The EHSI can display a moving map with navigation data such as flight plan route if a flight plan is pres...

Page 66: ...lay for decluttering purposes To display hide a selected pointer you only have to click on either the NV1 or NV2 button in the EHSI control panel The buttons work as a toggle switch so repeatedly clicking on them will cycle through the display hide option DISPLAYING THE ADF POINTER The ADF bearing pointer is hidden by default to make it visible click on the ADF button in the EHSI control panel The...

Page 67: ...view in the EHSI even if the TACS system is in the OFF position The operational mode determines the type of data received by the system The only option enabled is the TCAS both WX and T WX are disabled GPS FREEFLIGHT 2000 APPROACH PLUS This SA 227 BC model has a GPS navigator installed It is based on the Trimble 2000 Approach Plus It provides with flight plan navigation position finding flight pro...

Page 68: ...function buttons 10 Message annunciator NAVIGATION DABASE The navigation database is the standard one included in FSX and Prepar3D It provides access to worldwide data on Airports VORs NDBs Intersections and Airspace boundaries The information is only available if a flight plan is loaded OPERATION To operate the GPS you only have to click on the power switch The GPS will enter into a self test mod...

Page 69: ...S The information displayed by the GPS depends on the selected mode There are five operational modes NAV Displays navigation and position information on your selected route WPT Displays waypoint specific information FPL Displays and navigates a loaded flight plan CALC Allows fuel and airdata computations AUX Displays other information such as system data There are four function keys DIRECT TO Used...

Page 70: ...pages displayed on the top line starting with the default page and rotating the outer knob clockwise are TO Waypoint Bearing Distance and ETE estimated time en route TO waypoint ETE and ETA estimated time of arrival in Zulu time Heading TAS True Airspeed and wind Heading Ground Track and Drift Angle Current Track and recommended altitude DTK Desired Track Fly left or right to correct XTK cross tra...

Page 71: ...e the current waypoint you must click on the DIRECT TO function key The waypoint Type is indicated by a single letter code A Airport I Intersection V VOR N NDB U User T ATC BOTTOM LINE The data displayed on the bottom line depends on waypoint type For Airports Identifier city name facility name Radio frequencies available Airport elevation Type of lighting Active runway runway type and length Acti...

Page 72: ...approaches can be reviewed and selected Fig 101 Typical WPT Aproach Mode Display TOP LINE The data displayed on the top line is always the same Airport Identifier Currently selected approach name Clicking on the outer knob changes the selected approach BOTTOM LINE The data displayed on the top line is always the same Selected Transition Name Selected Transition s Leg information Left Clicking on t...

Page 73: ...e current leg in the route Clicking on either to outer or inner knobs will change the bottom display indicating the next legs in the flight plan Fig 102 Typical FPL Mode 1 display MODE 2 The top line displays the selected leg in the route The bottom line displays the following leg information Bearing Distance and ETE Clicking on either to outer or inner knobs will change the selected leg in the fl...

Page 74: ...The fuel management pages also estimate the amount of fuel required to arrive at the current destination If you are flying a multi leg flightplan the data reflects calculations from present position through the flight plan to final destination The pages available in this mode are Time Distance and Speed Calculations Fuel Management Fuel Remaining Fuel At Arrival Minimum Fuel Total Fuel Used Engine...

Page 75: ...RAZAIR A1 METRO III AFM 001 2 23 Fig 105 Typical CALC Mode Mode 2 display AUX MODE The auxiliary AUX mode displays current time information only Fig 106 Typical AUX Mode display ...

Page 76: ...unction that in FSX P3D is a function of the autopilot Only basic autopilot functions are enabled Yaw Damper Altitude Hold Heading Hold OPERATIONS To activate the autopilot you have to click on the YAW DAMPER switch Fig 101 1 located in the center console Fig 107 Virtual Cockpit Autopilot Controls ALTITUDE HOLD Autopilot Altitude is controlled by the Altitude Selector Fig 101 2 ...

Page 77: ... desired altitude click on the outer and inner knobs until the wanted altitude is displayed To activate the altitude hold click on the ARM button The ARM warning display will turn on indicating the system is enabled The ALERT display will turn on when the difference between aircraft current altitude and the selected altitude is less than one thousand feet HEADING HOLD The autopilot heading is cont...

Page 78: ...lot On Off This can be overridden by the Yaw Damper Switch when it is in the ON position YD Activates the Yaw Damper This will be overridden by the Yaw Damper Switch BC Back Course On Off APP Approach hold On Off NAV NAV hold On Off HDG Heading Hold On Off ALT Altitude Hold On Off This can be overridden by the Altitude Selector s ARM Switch IAS Airspeed Hold on Off Not available This aircraft does...

Page 79: ...RAZAIR A1 METRO III AFM 001 3 1 PASSENGER CARGO HANDLING ...

Page 80: ...e real aircraft s manual The payload managers can also open close the main and cargo doors If for any reason one of the built in fire extinguishers has been fire the payload manager can reset it The payload manager will help you determine if the aircraft is too heavy for a safe takeoff METRO The Metroliner s payload manager is designed to handle both passenger and cargo To place a passenger in a s...

Page 81: ...ones click on the green button To remove cargo click on the red button Using the wheel in either green or red button will add subtract cargo faster Fig 111 Expediter payload manager Cargo zones 1 thru 4 have a 1 150 pounds weight limit while cargo zone 5 has a 600 pounds weight limit The payload manager will not allow you to place weight above the limit for any cargo zone ...

Page 82: ...RAZAIR A1 METRO III AFM 001 4 1 OPERATIONAL PROCEDURES ...

Page 83: ...st Switch CENTERED 11 Light Control Knobs AS REQUIRED 12 Unfeather Test Switch CENTERED INSTRUMENT PANEL 1 Static Selector NORMAL 2 Cabin Altitude and Rate indicators and Controls CHECK SET 3 All Rocker Switches except battery switches OFF 4 Pitch Trim CHECK 5 Fuel Counter ZEROED 6 Fuel Quantity CHECK 7 Crossflow Switch CLOSED 8 Temperature Controls AS REQUIRED 9 Cabin Pressure Dump Switch DUMP 10...

Page 84: ... Panel Lights PRESS TO TEST 4 Fire Extinguisher System TEST 5 Inverter Check No 2 then No 1 ON 6 All Instruments and Clocks CHECKED SET RIGHT ENGINE RECOMMENDED FIRST 7 SRL OFF Light CHECK ON 8 Boost Pumps CHECKED AS DESIRED 9 Propellers UNFEATHERED CLEAR 10 Start Mode Switch AS DESIRED 11 Engine Start Button CLICK 12 RPM 10 TO 12 13 Ignition Light ON AT 10 RPM 14 EGT MONITOR 7700 MAXIMUM FOR ONE ...

Page 85: ...ION 11 CAWI SYSTEM CHECK 12 Ignition Switches AUTO OR CONT 13 Ice Protection System CHECK AS REQUIRED 14 Fuel Quantity CHECK 400 POUNDS IS MAXIMUM IMBALANCE WHEN TOTAL FUEL IS LESS THAN 2 000 POUNDS 200 POUNDS ISMAXIMUM IMBALANCE WHEN TOTAL FUEL IS GREATER THAN 2 000 POUNDS 15 Fuel Crossflow Valve CHECK CLOSED 16 Navigation Equipment AS REQUIRED 17 Interior Exterior Lights AS REQUIRED TAKEOFF DRY ...

Page 86: ...ASE 11 NWS Power Lever Button AS DESIRED 12 VR Speed ROTATE 13 Landing Gear after liftoff UP 14 V50 Speed MAINTAIN UNTIL OBSTACLES ARE CLEARED 15 Flaps UP CLIMB 1 Climb Speed ATTAIN 2 Water Injection Switch OFF 3 Bleed Air Switches AS DESIRED 4 Climb Power NOT TO EXCEED 6500 C EGT OR 100 TORQUE 5 Propeller Synchrophaser Switch CLIMB CRUISE 6 Ignition Switches AUTO OR CONT 7 Ice Protection Systems ...

Page 87: ...s Signs ON 2 Exterior and Interior Lights AS REQUIRED 3 Propeller Synchrophaser Switch TAKEOFF LANDING 4 Speed Levers HIGH RPM 5 Friction Controls SPEED LEVERS AS DESIRED POWER LEVERS OFF 6 Landing Gear Hydraulic Pressure and Indicators DOWN CHECK 7 Flaps AS REQUIRED 8 Cabin Differential Pressure CHECK ZERO 9 Nose Wheel Steering Switch ARMED 10 Ignition Switches AUTO OR CONT 11 Fuel Crossflow Valv...

Page 88: ...itch DUMP 4 Bleed Air Switches OFF 5 Generator Switches OFF 6 Engine Stop Buttons CLICK 7 Power Levers REVERSE AT APPROXIMATELY 50 REVERSE 8 Fuel Boost Switches OFF 9 Inverter Switch OFF 10 Exterior and Interior Lights OFF 11 Battery Switches OFF 12 Parking Brake AS REQUIRED SYSTEM CHECKS AND OPERATION NTS SYSTEM Check Propeller governor rest function by setting speed lever low and advancing power...

Page 89: ...ef V1 103 103 FLAPS UP 112 VR 103 103 FLAPS 110 V2 115 119 FLAPS 105 VYSE 124 FULL 101 11 000 Lbs Takeoff Dry Wet Landing Ref V1 101 103 FLAPS UP 114 VR 101 103 FLAPS 112 V2 114 118 FLAPS 107 VYSE 124 FULL 103 V1 Engine failure recognition speed or takeoff decision speed VR Rotation speed The speed at which the aircraft s nosewheel leaves the ground V2 Minimum takeoff safety speed VYSE Best rate o...

Page 90: ...101 FLAPS UP 118 VR 100 101 FLAPS 115 V2 110 114 FLAPS 110 VYSE 126 FULL 106 12 500 Lbs Takeoff Dry Wet Landing Ref V1 100 101 FLAPS UP 120 VR 100 101 FLAPS 116 V2 109 112 FLAPS 111 VYSE 127 FULL 107 V1 Engine failure recognition speed or takeoff decision speed VR Rotation speed The speed at which the aircraft s nosewheel leaves the ground V2 Minimum takeoff safety speed VYSE Best rate of climb sp...

Page 91: ...102 FLAPS UP 124 VR 104 102 FLAPS 120 V2 111 111 FLAPS 114 VYSE 130 FULL 110 14 000 Lbs Takeoff Dry Wet Landing Ref V1 104 105 FLAPS UP 126 VR 107 105 FLAPS 121 V2 113 113 FLAPS 116 VYSE 131 FULL 112 V1 Engine failure recognition speed or takeoff decision speed VR Rotation speed The speed at which the aircraft s nosewheel leaves the ground V2 Minimum takeoff safety speed VYSE Best rate of climb sp...

Page 92: ...110 FLAPS UP 130 VR 112 110 FLAPS 125 V2 116 116 FLAPS 119 VYSE 133 FULL 115 15 500 Lbs Takeoff Dry Wet Landing Ref V1 109 113 FLAPS UP 132 VR 115 113 FLAPS 127 V2 118 118 FLAPS 121 VYSE 134 FULL 116 V1 Engine failure recognition speed or takeoff decision speed VR Rotation speed The speed at which the aircraft s nosewheel leaves the ground V2 Minimum takeoff safety speed VYSE Best rate of climb sp...

Page 93: ...115 FLAPS UP 134 VR 117 115 FLAPS 128 V2 119 120 FLAPS 122 VYSE 135 FULL 118 V1 Engine failure recognition speed or takeoff decision speed VR Rotation speed The speed at which the aircraft s nosewheel leaves the ground V2 Minimum takeoff safety speed VYSE Best rate of climb speed ...