Home

Aircraft & Systems

Contents

1. FLT SPOILERS amp EANUAL wn CARS DODA ELEVATORS E ELEV FEEL i zs L i Ra ATLERONS Pal EEN zx a i ee RUDDER 1 LEADING EDGE FLAPS SLATS FLAPS LANDING GEAR T As installed GROUND SPOILERS P 737 Captain FLIGHT MANUAL Part II Aircraft Systems 126 DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS O22 HYDRAULIC PANEL 1 Ground Interconnect Switch 2 3 Electric Hydraulic Pump Overheat Lights 4 7 Hydraulic Pump Low Pressure Lights 8 9 Engine Hydraulic Pump Switches 10 11 Electric Hydraulic Pump Switches 1 PRESEZUEKE 1 GROUND INTERCONNECT Switch CLOSE isolates system A using units from system B output OPEN connects system A pressure to system B pressure for ground functional checks The ground interconnect valve will open only if the parking brake is set the airplane is on the ground and electrical power is available 2 3 Electric Hydraulic Pump OVERHEAT Lights Illuminated amber hydraulic pump or fluid used to cool and lubricate the corresponding electric motor driven pump has overheated 4 7 Hydraulic Pump LOW PRESSURE Lights Illuminated amber output pressure of associated pump is low Note When an engine fire warning switch is pulled the associated engine driven hydraulic pump low pressure light is deactivated 8 9 Engine Hydraulic Pump Switches ON
2. 4 RA Pitch Command green LEVEL Advisory Indicates vertical speed range to ensure traffic separation 2012 Captain Sim www captainsim com 105 DO NOT USE FOR FLIGHT TCAS VSI MESSAGES 1 TCAS Mode Display 2 TCAS Range 3 Fault Annunciations 4 VSI Flag amber 1 TCAS Mode Display Indicates current TCAS mode system status TCAS amber TCAS system has failed TA ONLY blue TCAS TA only mode is selected TCAS STBY blue TCAS standby mode is selected TEST amber TCAS is in test mode 2 TCAS Range Displays TCAS range in nautical miles 3 Fault Annunciations TD FAIL amber failure in the operation of the traffic display RA FAIL amber RA information available 4 VSI Flag amber Indicates that vertical speed is unreliable is not 737 Captain FLIGHT MANUAL Part II Aircraft Systems 106 DO NOT USE FOR FLIGHT TCAS SYMBOLOGY RA traffic symbol Displayed during TCAS Resolution Advisory when traffic selected on the VSI or Weather Radar Indicator A Weather Radar Indicator Proximate traffic Displayed when traffic selected on the VSI or Weather Radar Indicator and symbol W traffic is within 1200 feet vertical and 6 miles horizontal from present position e TA traffic symbol Displayed during TCAS Traffic Advisory when traffic selected on the VSI or symbol traffic is greater than 1200 feet vertical or 6 miles horizontal from present Other traffi
3. FROM LEFT PNEUMATIC MANIFOLD GALLEY S LAVATORY CONTROLS To operate the WATER SYSTEM use Animation Control Panel 36 DO NOT USE FOR FLIGHT AIR SYSTEM BLEED AIR SYSTEM DESCRIPTION Air for the bleed air system can be supplied by the engines APU or an external air cart source The APU or external cart supplies air to the bleed air duct prior to engine start After engine start air for the bleed air system is normally supplied by the engines The following systems rely on the bleed air system for operation e Air conditioning pressurization Wing and engine thermal anti icing Engine starting Hydraulic reservoirs pressurization Water tank pressurization Switches on the air conditioning panel operate the APU and engine bleed air supply system AIR CONDITIONING SYSTEM DESCRIPTION Conditioned air for the cabin comes from either the airplane air conditioning system or a preconditioned ground source Air from the preconditioned ground source enters the air conditioning system through the mixing and distribution manifold to the cabin distribution ducts The air conditioning system provides temperature controlled air by processing bleed air from the engines APU or a ground air source in air conditioning packs This temperature controlled air is distributed to the cockpit and passenger cabin Conditioned air from the left pack flows directly to the flight deck Excess air from the left pack and the air from the ri
4. PANEL AND BACKGROUND LIGHTING O12 OVERHEAD CIRCUIT BREAKER PANEL LIGHT CONTROLS FLOOD AND AFT ELECTRONIC PANEL LIGHTS CONTROLS A07 DOME LIGHT CONTROL C01 MASTER LIGHTS TEST SWITCH O06 LANDING RUNWAY TURNOFF AND TAXI LIGHTS O29 MISCELLANEOUS EXTERIOR LIGHTS 27 DOORS AND WINDOWS 28 28 29 30 FLIGHT DECK NUMBER TWO WINDOWS PILOT SEAT ADJUSTMENT O23 EXTERIOR DOOR ANNUNCIATOR LIGHTS LOWER CARGO COMPARTMENTS 31 EMERGENCY EQUIPMENT IS e N e e EMERGENCY EVACUATION ROUTES FLIGHT DECK NUMBER TWO WINDOWS OVERWING ESCAPE HATCHES 4 DO NOT USE FOR FLIGHT 32 33 AIRSTAIRS 34 JONYGEN SYSTEMS 34 A09 OXYGEN CONTROLS AND INDICATORS 35 WATER SYSTEM 36 AIR SYSTEM 37 FLIGHT PATH EVENTS AUTO MODE 38 O27 BLEED AIR CONTROLS AND INDICATORS 40 026 AIR CONDITIONING CONTROLS AND INDICATORS 41 013 EQUIPMENT COOLING PANEL 41 025 CABIN ALTITUDE PANEL 42 028 CABIN PRESSURIZATION PANEL 44 AIR SYSTEMS SCHEMATIC 45 JANTI ICE RAIN 45 ANTI ICE COMPONENTS DIAGRAM 45 FLIGHT DECK WINDOW HEAT 45 WINDSHIELD WIPERS AND RAIN REPELLENT 46 PROBE AND SENSOR HEAT 46 ENGINE ANTI ICE SYSTEM 46 WING ANTI ICE SYSTEM 46 O19 WINDOW HEAT PANEL 47 04 RO4 WINDSHIELD FOOT AIR CONTROLS 47 O16 WINDSHIELD WIPER PANEL 48 O20 PITOT STATIC HEAT PANEL 48 O21 WINGS ENGINE ANTI ICE PANEL 49 AUTOMATIC FLIGHT 49 AUTOPILOT SYSTEM 50 AUTOPILOT SCHEMATIC 50 AUTOMATIC DISENG
5. CARGO DOOR 505 cubic feet 370 cubic feet 51 in by in C270 cubic feet on airplanes with Aux Fuel Tank TOTAL CARGO COMPARTMENT VOLUME 875 CUBIC FEET 640 cubic feet on airplanes with Aux Fuel Tank To operate the cargo doors use Animation Control Panel 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 31 DO NOT USE FOR FLIGHT EMERGENCY EQUIPMENT EMERGENCY ESCAPE Emergency escape information included in this chapter includes Emergency evacuation routes Flight deck windows Escape slides Escape hatches EMERGENCY EVACUATION ROUTES Emergency evacuation may be accomplished through four entry service doors and two overwing escape hatches Flight deck crew members may evacuate the airplane through two sliding flight deck windows FLIGHT DECK NUMBER TWO WINDOWS Flight deck sliding windows are opened by squeezing the lock release in the handle rotating the handle inward and sliding the window aft until it locks Window unlocking can also be accomplished using an exterior handle For passenger airplanes at the First Officer s window only for cargo airplanes at both windows 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 32 DO NOT USE FOR FLIGHT OVERWING ESCAPE HATCHES Two escape hatches are located in the passenger cabin over the wings These are plug type hatches and are held in place by mechanica
6. COOLING Illuminated amber no airflow from selected cooling fan ALTERNATE 2 Equipment EQUIP COOLING Switch NORMAL normal cooling fan activated ALTERNATE alternate cooling fan activated 025 CABIN ALTITUDE PANEL 1 CABIN Altitude ALT Differential Pressure ALT DIFF PRESS Indicator ag HORN L y AN CUTOUT Inner Scale indicates cabin altitude in feet sa Outer Scale indicates the difference between cabin 2 pressure and ambient pressure in psi 2 Altitude ALT HORN CUTOUT Switch PUSH PRESS IO EE s e Cuts out intermittent cabin altitude warning OFF LDG horn 125 FSI e altitude warning horn sounds when cabin reaches 10 000 feet altitude 3 CABIN Rate of CLIMB Indicator Indicates cabin rate of climb or descent in feet per minute 2012 Captain Sim www captainsim com Ci 37 Captain FLIGHT MANUAL Part II Aircraft Sy stems 42 DO NOT USE FOR FLIGHT 028 CABIN PRESSURIZATION PANEL AUTO CFF FAIL PESLENE e S LAND ALT 1 AUTO FAIL Light OO N AUTO FAIL Light Off Schedule Descent Light Standby Light Manual Light Flight Altitude Indicator Flight Altitude Selector Landing Altitude Indicator Landing Altitude Selector Cabin Rate Selector Outflow Valve Position Indicator Cabin Altitude Indicator Outflow Valve Switch Spring Loaded To Center Cabin
7. Displays magnetic heading The magnetic compass may be folded out of view for an unobstructed view through the windshield A standby magnetic compass correction card provides appropriate heading corrections FLIGHT MANAGMENT NAVIGATION SYSTEM DESCRIPTION Navigation systems include the radio navigation systems transponder and weather radar RADIO NAVIGATION SYSTEMS AUTOMATIC DIRECTION FINDING ADF An automatic direction finding ADF system enables automatic determination of magnetic and relative bearings to selected facilities Two ADF receivers are installed The No 1 receiver uses the narrow pointer on the RMIs The No 2 receiver uses the wide pointer The audio is heard by using the ADF receiver control on the audio selector panel ADF bearing pointers will not display correct magnetic bearing when the compass information is lost or invalid Relative bearings are indicated by pointers if the receiver is operating VHF NAVIGATION SYSTEM VHF NAV Two NAV receivers and controls panels are installed The VHF navigation control panel is used to tune VOR and ILS frequencies VOR information is displayed on the RMIs when a valid in range VOR station is tuned The HSI displays course deviation when operating in the VOR mode The deviation bar and glideslope pointer are controlled by the controls for the operating system 737 Captain FLIGHT MANUAL Part II Aircraft Systems 110 DO NOT USE FOR FLIGHT VHF NAVIGA
8. Localizer Symbol Shutter 7 Slip Skid Indicator 8 Flight Director Command Bars 9 Symbolic Airplane 10 Flight Director Computer Warning Flag 11 Localizer Symbol And Deviation Scale 11 1 Bank Indicator and Scale index indicates roll angle against calibrated scale scale has minor markings at 10 degrees and 20 degrees and major markings at 30 degrees and 60 degrees 2 Attitude Display e tape moves relative to symbolic airplane displaying pitch and roll signals from the vertical gyro e pitch up scaled in 5 degree increments to 15 degrees then with marks at 30 50 70 and 90 degrees e pitch down scaled with marks at 5 10 20 30 50 70 and 90 degrees 3 Glideslope Pointer and Deviation Scale pointer indicates glideslope position scale indicates deviation glideslope flag covers the display when the signal is not valid Pointer out of view a VOR frequency is tuned 2012 Captain Sim www captainsim com 95 DO NOT USE FOR FLIGHT 4 Glideslope GS Warning Flag In view e glideslope information is unreliable with ILS frequency tuned e parallels the glideslope warning flag on the HSI 5 GYRO Warning Flag In view e display is unreliable some failures cause indications of 90 degrees left bank e electrical power loss 6 Localizer Symbol Shutter In view e glideslope not captured e glideslope capture but VOR LOC flag on HSI in view 7 Slip Skid Indicator Bal
9. R 7 ATC FAIL Light Illuminated indicates transponder malfunction 8 Traffic Collision Avoidance System TCAS Range Selector Selects range for TCAS operation 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 114 DO NOT USE FOR FLIGHT WEATHER RADAR The primary use of this radar is to aid the pilot in avoiding thunderstorms and associated turbulence Since each operator normally develops specific operational procedures for use of weather avoidance radar the following information is presented for use at the operator s discretion Operational techniques for the radar are similar to earlier generation weather avoidance radars The proficient operator manages antenna tilt control to achieve best knowledge of storm height size and relative direction of movement RADAR PRINCIPLES Radar is fundamentally a distance measuring system using the principle of radio echoing The term RADAR is an acronym for Radio Detecting and Ranging It is a method for locating targets by using radio waves The transmitter generates microwave energy in the form of pulses These pulses are then transferred to the antenna where they are focused into a beam by the antenna The radar beam is much like the beam of flashlight The energy is focused and radiated by the antenna in such a way that it is most intense in the center of the beam with decreasing intensity near the edge The same antenna is used for both t
10. SECONDARY PANEL 1 3 REVERSER UNLOCKED Light Illuminated amber indicates the thrust reverser doors are not locked C tf D REVERSER ETRRTVAL AEVERSER BTARTVALVE wen a g en Brno ral a 2 4 START VALVE OPEN Light PRESSURE BYPASS PRESSURE BYPASS re 4 Illuminated amber indicates the engine starter A valve is open air is being supplied to the starter m motor 9 100 10 ig 5 7 LOW OIL PRESSURE Light Illuminated amber indicates engine oil pressure is below 35 psi 11 Suus 6 8 OIL FILTER BYPASS Light Illuminated amber indicates an impending bypass of the main oil filter x 9 10 Oil Pressure OIL PRESS Indicator 13 14 QUANTITY _ GALLONS QANTITY GALLONS Displays engine oil pressure in psi C11 ENGINE OIL QUANTITY TEST SWITCH 1 Engine Oil Quantity Test Switch Push oil quantity indicators move toward zero ENG OIL 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT O18 ENGINE START SWITCHES 1 2 Engine Start Switch GRD solenoid held spring loaded to Opens OFF LOH cnp OFF the starter valve and provides high energy ignition to Ty FLT two igniters when the Engine Start Lever is moved from CUTOFF to IDLE ignition TT LOW IGN P
11. The anti ice and rain systems include Flight Deck Window Heat Probe and Sensor Heat Windshield Wipers and Rain Engine Anti Ice System Repellent Wing Anti Ice System ANTI ICE COMPONENTS DIAGRAM ELEVATOR PITOT PROBES 2 PLACES FLIGHT DECK WINDOWS WINDOW HEAT WINDSHIELD WIPER RAIN REPELLENT ANGLE AIRFLOW SENSOR ENGINE TEMPERATURE PROBE COWL LIP LEADING EDGE SLATS PITOT STATIC PROBES PLACES FLIGHT DECK WINDOW HEAT Flight deck windows 1 2 4 and 5 consist of glass panes laminated to each side of a vinyl core Flight deck window 4 has an additional vinyl layer and acrylic sheet laminated to the inside surface Flight deck window 3 consists of two acrylic panes separated by an air space A conductive coating on the outer glass pane of windows 1 and 2 permits electrical heating to prevent ice build up and fogging A conductive coating on the inner glass pane of windows 4 and 5 permits electrical heating to prevent fogging Window 3 is not electrically heated WINDSHIELD WIPERS AND RAIN REPELLENT The rain removal system for the forward windows consists of windshield wipers and rain repellent One windshield wiper is located on each No 1 window Each wiper is electrically operated by separate systems Both wiper systems are controlled by a common switch Each push of a rain repellent switch applies a measured amount of repellent on the related No 1 windshield 2012 Captain Sim www captain
12. Turbulence Key 4 Flight Mode Selector 5 Engage Key 6 Brightness Control 7 Select Key 8 Clear Key EAE 9 Enter Key Het 10 Keyboard J 11 Recall Key 7 ax 12 Page Reverse Key Fs d 13 Page Forward Key 1 Cathode Ray Tube Display e Displayed data is called a page e Each page can display 6 lines 13 characters per line 2 CRT Display Symbols question marks e Indicates lines of unentered data CARET e Indicates the place where information is to be inserted e Displaces the asterisk on that line asterisk Identifies the line where an ENT entry can be made 3 TURB turbulence KEY PRESS e Causes the CRT to display the turbulent air penetration speed pitch attitude and N1 settings e The EPR indicator bugs move to values corresponding to the N1 values e Overrides the CRZ flight mode position 4 FLIGHT MODE SELECTOR ROTATE Selects the phase of flight for which data is desired STBY Standby Used for data entry and automatic system verification TO Takeoff Displays takeoff EPR limits for the temperature entered CLB Climb Displays climb EPR and speeds for the desired climb profile Best economy maximum rate or crew selected speeds CRZ Cruise Displays cruise EPR and speeds for the desired cruise schedule Best economy LRC long range cruise or crew selected speeds DES Descent Provides descent speed time and distance for best economy or crew
13. a RSS 121 DO NOT USE FOR FLIGHT CONDITION ENGINES GFERATING CENTER FEEDING FUEL FEED EV SIME DRIVEN FUEL PUHA CROSSFEED i MANUEL EFUELING E a E E 2 VALVE 2 E k k FUELING STATION ML PU FUEL VALVE TG craft System 122 DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS O04 FUEL CONTROL PANEL 1 20 Fuel Valve Closed Light 2 21 Filter Icing Light 3 Fuel Temperature Indicator 4 22 Fuel Heat Valve Open Light 5 Crossfeed Valve Open Light 6 23 Fuel Heat Switch 7 Crossfeed Selector 8 9 Center Tank Fuel Pump Low Pressure Light 10 11 16 19 Fuel Pump Switch 12 15 Main Tank Fuel Pump Low Pressure Light 1 20 FUEL VALVE CLOSED Light Extinguished related engine fuel shutoff valve is open Illuminated blue e bright related fuel shutoff valve is in transit or valve position and engine start lever or engine fire warning switch disagree e dim related fuel shutoff valve is closed 2 21 FILTER ICING Light Extinguished fuel filter operating normally Illuminated amber indicates an iced or contaminated filter 3 Fuel Temperature FUEL TEMP Indicator Indicates fuel temperature in No 1 tank 4 22 Fuel Heat VALVE OPEN Light Illuminated blue e bright fuel heat valve is
14. a 79 A ku When a complete detour is impractical penetration of weather patterns may be required Avoid adjacent cells by at least 20 nautical miles A Blind Alley or Box Canyon situation can be very dangerous when viewing the short ranges Periodically switch to longer range displays to observe distant conditions As shown below the short range returns show an obvious corridor between two areas of heavy rainfall but the long range setting shows a larger area of heavy rainfall 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 120 DO NOT USE FOR FLIGHT FUEL SYSTEM DESCRIPTION The fuel system supplies fuel to the engines and the APU Fuel is contained in three tanks located within the wings and wing center section Refer to Engine and APU chapter for a description of the engine and APU fuel systems FUEL FEED Both engines are normally pressure fed from the center tank until the center tank quantity decreases to near zero The engines are normally then pressure fed from their respective main tanks Check valves are located throughout the fuel system to ensure the proper direction of fuel flow and to prevent transfer of fuel between tanks FUEL PUMPS Each fuel tank uses two AC powered fuel pumps which are fuel cooled and lubricated Center tank check valves open at a lower pressure than do the main tank check valves This ensures that ce
15. a warning tone takeoff configuration and cabin altitude by an intermittent horn and landing gear positions by a steady horn The fire warning is given by a fire warning bell Ground proximity warnings and alerts as well as windshear warnings and alerts are given by voice warnings Generally aurals automatically silence when the associated non normal condition no longer exists 737 Captain FLIGHT MANUAL Part II Aircraft Systems 134 DO NOT USE FOR FLIGHT INTERMITTENT CABIN ALTITUDE CONFIGURATION WARNING The takeoff configuration warning is armed when the airplane is on the ground and either or both forward thrust levers are advanced for takeoff An intermittent warning horn sounds if Leading Edge devices are NOT configured for takeoff or Speed Brake lever is NOT in the DOWN position or Stabilizer Trim is NOT set in the takeoff range or Trailing Edge flaps are NOT in the flaps 1 through 25 takeoff range The warning indication is cancelled when the configuration error is corrected The Cabin Altitude Warning Horn activates when cabin altitude exceeds 10 000 feet An intermittent warning horn is heard The Cabin Altitude Warning Horn may be silenced by momentarily pressing the ALT HORN CUTOUT switch on the Cabin Altitude Panel LANDING GEAR CONFIGURATION WARNINGS Visual indications and aural warnings of landing gear position are provided by the landing gear indicator lights and landing gear warning horn VISUAL INDICATI
16. and autopilot and autothrottle disconnect warnings are discussed in the Automatic Flight chapter The conditions which excite the fire warning bell are discussed in the Fire Protection chapter Conditions which require the immediate attention of the flight crew are indicated by red warning lights located in the area of the pilots primary field of vision These lights indicate APU engine or wheel well fires autopilot and unsafe landing gear conditions Conditions which require the timely attention of the flight crew are indicated by amber caution lights Blue lights inform the flight crew of electrical power availability valve position equipment status and flight attendant or ground communications Blue lights are for information and do not require immediate flight crew attention Some system blue lights indicate a transitional state by illuminating bright as valves or components reposition then returning to a dim blue when the required configuration is reached Green lights indicate a fully extended configuration e g landing gear and leading edge devices For specific information regarding red amber blue and green lights refer to the appropriate systems chapters Stall warning is provided by a control column shaker on the captain s control column or as installed on each control column Various aural signals call attention to warnings and cautions An aural warning for airspeed limits is given by a clacker the autopilot disconnect by
17. and selecting performance functions for display LOAD KEY Permits flight data entry to enable the system to compute takeoff EPR gross weight optimum descent distance and airspeeds ALTITUDE INTERCEPT KEY Used to solve time distance and flight level intercept problems during climb and descent FL Flight KEY Used to determine optimum flight level maximum altitude capability and wind altitude trade considerations GS Ground Speed KEY Computes ground speed and wind or time and distance to a waypoint or destination RNG Range KEY Displays total endurance distance and time remaining to reserve fuel quantity or empty tanks at any flight level FUEL KEY Displays total fuel fuel reserves and fuel over destination TEMP Temperature KEY Displays ISA deviation TAT SAT TAS VREF KEY Displays reference speeds for landing flaps and the current gross weight TRIP KEY Displays most economical cruise flight level for trip distances ISA deviation and wind if known WIND KEY Displays automatically computed or manually entered wind data 11 RCL Recall PRESS with performance function displayed Changes the display to the selected flight mode 12 PAGE REVERSE KEY PRESS Reverse the display one page for both flight modes and performance functions wit multiple pages After the first page is reached the system cycles back to the last page 13 PAGE FORWARD KEY PRESS e Advances the display one page for both flight mo
18. angle for climb or descent Command bars can be selected to 10 degrees down to 15 degrees up Not effective if ALT HOLD switch is ON Glide slope is captured GA mode is active 737 Captain FLIGHT MANUAL Part II Aircraft Systems 59 DO NOT USE FOR FLIGHT ALTITUDE ALERT L18 R18 ALTITUDE ALERT LIGHT ALTITUDE Altitude Alert Light ALERT Illuminated amber Airplane is within the range of 1000 to 375 feet of the selected altitude 04 ALTITUDE ALERT CONTROLLER ALTITUDE ALERT Controller e Displays the selected alerting altitude e Covered by a warning flag if the Captain s altimeter signal is lost or if electrical power is lost A01 ALTITUDE ALERT SPEAKER 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 60 DO NOT USE FOR FLIGHT COMMUNICATIONS CALL SYSTEM The call system is used as a means for various crewmembers to gain the attention of other crewmembers and to indicate that interphone communication is desired Attention is gained through the use of lights and aural signals chimes or horn VHF COMMUNICATIONS Primary short range voice communications is provided in the VHF range by two independent radios Each radio provides for selection of an active frequency and an inactive preselected frequency Voice transmission and reception are controlled at the related ASP VHF 1 is located on the left aft electronic panel VHF 2 on the right The VHF
19. are powered by hydraulic systems A and B Antiskid protection is provided on all brakes When autobrakes are selected pressure is automatically applied in conjunction with the antiskid system LANDING GEAR OPERATION The landing gear are normally controlled by the LANDING GEAR lever On the ground an override trigger in the lever used to bypass the landing gear lever lock NOSE WHEEL STEERING The airplane is equipped with nose wheel steering Primary steering is controlled through the nose wheel steering wheel Limited steering control is available through the rudder pedals MECHANICALLY CONMECTED STEERING VALVE STEERING DEPAESSURIZATICH VALVE NOSE WHEEL STEERING 2012 Captain Sim www captainsim com ir 129 DO NOT USE FOR FLIGHT BRAKE SYSTEM Each main gear wheel has a multi disc hydraulic powered brake The brake pedals provide independent control of the left and right brakes The brakes are powered by the two independent hydraulic systems Hydraulic system A supplies pressure to the inboard brakes and hydraulic system B supplies pressure to the outboard brakes The nose wheels have no brakes The brake system includes brake accumulator e autobrake system antiskid protection e parking brake BRAKE ACCUMULATORS Each brake system has an accumulator which stores hydraulic pressure and is used as a backup system in the event of a system hydraulic failure If normal system pressure is lost trapped hyd
20. aurals to sound e atleast 10 seconds on ground above indications always occur first followed by any additional aurals as installed e System test is inhibited from lift off to 1000 feet radio altitude 3 Ground Proximity FLAP GEAR Inhibit Switch FLAP GEAR INHIBIT inhibits or cancels warnings alerts caused by flaps not in 30 or 40 position or landing gear not down NORMAL guarded position flap and landing gear position logic is provided for GPWS 737 Captain FLIGHT MANUAL Part II Aircraft Systems 139 DO NOT USE FOR FLIGHT CUSTOMER CARE You are invited to join Captain Sim community forum DAILY NEWS For Captain Sim daily news please follow us at Twitter or Facebook VIDEO CHANNEL For Captain Sim videos please watch our YouTube channel TECH SUPPORT The 737 Captain is one of the most advanced complete and accurate digital replica of the Boeing 737 aircraft ever available for any game platform Our product is not perfect unfortunately nothing is But we are working on improvements If you have some important issue to report please check in to Your Profile then click Product Name gt Customer Support gt and use the Trouble Ticket System We process all tickets and consider the most significant issues for the next service packs SPECIAL THANKS Mark Fletcher Dirceu Seabra Paul Sweeney Brendan Downie Marko Raicevic Peter Orosz Wilfredo Tour 2012 Captain Sim www captainsim com
21. bars provide commands to fly to and maintain selected heading on HSI VOR LOC e VOR LCC light illuminated amber armed command bars provide commands to fly to heading on HSI VOR LOC light illuminated green capture command bars provide commands to fly to or localizer course selected on HSI VOR capture 1 dot 5 degrees LOC capture 2 dots 2 degrees AUTO APP VOR LOC light illuminated amber armed command bars provide commands to fly to and maintain selected heading on HSI 2012 Captain Sim www captainsim com 58 DO NOT USE FOR FLIGHT VOR LOC light illuminated green capture command bars provide commands to fly to and maintain localizer course LOC capture 2 dots 2 degrees GLIDE SLOPE light illuminated amber armed command bars provide commands to fly existing attitude commands GLIDE SLOPE light illuminated green capture command bars provide commands to fly to and maintain glide slope MAN GS VOR LOC and GLIDE SLOPE lights illuminated green capture command bars provide commands for fixed intercept angle to the localizer command bars provide commands to fly to pitch up or down to intercept the glide slope 2 Altitude Hold ALT HOLD Switch OFF spring loaded e Deselects altitude hold e Trips off at glide slope capture ON e Command bars reference to pressure altitude from ADC e Cannot be selected when Mode Selector is in GA position 3 Pitch Command PITCH CMD Control Selects fixed pitch
22. be categorized into three main divisions the AC power system the DC power system and the standby power system AC POWER SYSTEM Each AC power system consists of a generator bus a main bus and a transfer bus The left AC power system also includes a ground service bus Transfer bus 1 supplies power to the AC standby bus If the source powering either AC power system fails or is disconnected a transfer relay automatically selects the opposite generator bus as an alternate power source for the transfer bus Generator busses can be powered from the engine generators by momentarily positioning the related generator switch to ON This connects the voltage regulator to the generator and connects the generator to its associated generator bus Selecting a new power source disconnects the existing power source When the APU is operating selecting either APU GEN switch ON connects APU power to its associated generator bus 737 Captain FLIGHT MANUAL Part II Aircraft Systems 63 DO NOT USE FOR FLIGHT AC POWER SCHEMATIC EXTESRAL EU L I I GOMERATOR EU 1 GENERATOR GUS 2 GAD SORWICE ELAY ALTERRATE MORAL T TRANSFERS TEARS CORE SELAT 1 RELAY 5 5 SAN 1157 AC 1157 AL RUS F PAIN GUS 1 HAIM WUS 2 Airplane Configuration Battery Switch Of Standhy Power Switch AUTO Bus Transfer Switch AUTO ENGINE GENERATOR CONNECTED T RESPECTIVE BUS DC POWER SYST
23. beacon OUTER blue illuminates over an outer marker beacon OUTER L19 R19 RADIO ALTIMETER One low range radio altimeter and two indicators provide indication of airplane height above the ground up to 2500 feet absolute altitude A radio altimeter indicator is located on each pilot instrument panel When the captain s radio altimeter is inoperative all modes of the GPWS are inoperative 1 Minimum Descent Altitude Light 2 Radio Altimeter Test Switch 3 Minimum Descent Altitude Cursor 4 Warning Flag 5 Altitude Pointer 6 Minimum Descent Altitude Cursor Control 1 Minimum Descent Altitude MDA Light Illuminated amber altitude pointer is at or below MDA cursor 2 Radio Altimeter Test Switch Push e altitude pointer drives to 100 feet e warning flag in view 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 102 DO NOT USE FOR FLIGHT the MDA light illuminates if the altitude pointer drives to a position at or below the altitude indicated by the minimum descent altitude cursor 3 Minimum Descent Altitude MDA Cursor Displays selected altitude reference selected by the MDA cursor control 4 Warning Flag In view e power failure e loss of return signal below 2500 feet e incorrect altitude tracking e radio altimeter test switch pushed 5 Altitude Pointer Power off pointer moves to the top of the scale under the mask
24. characteristic of a severe thunderstorm the radar displays the storm as a strong echo Drop size is the most important factor in high radar reflectivity The radar display has been calibrated to show five levels of target intensity Black level 0 and levels 1 4 grades of Amber CONTROLS AND INDICATORS P05 WEATHER RADAR PANEL 1 Range Selector 2 Brightness Control 3 Dimmer Control 2 gj 185 BRT 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 116 DO NOT USE FOR FLIGHT PO2 WEATHER RADAR CONTROL PANEL 1 Weather WX Radar Function Selector any 2 Antenna Tilt Control 3 Gain Control 1 Weather WX Radar Function Selector STBY Fully energizes the system circuitry but no radar transmissions occur in the SBY mode of operation The antenna is parked at 0 degrees azimuth and 30 degrees tilt down with the antenna drive motors locked WX NORM Selects the normal condition of operation for weather detection The system will transmit after a 60 second warm up time is completed The radar system initializes to the Wx mode 80 nm Note The 60 second warm up period can be monitored upon power up of the system When the knob is switched directly from OFF to ON mode the display will blank Just before the warm up period is complete the screen will turn black for a few seconds then the radar will begin transmitting and the screen will display radar returns No r
25. during fair weather instead of while trying to penetrate a storm front This section concerns itself with a more detailed discussion of some of these controls and how to make the most efficient use of them Note Your radar is a weather avoidance device It should never be used for weather penetration It will help you see and plan avoidance maneuvers around significant weather encountered during flight TILT MANAGEMENT Effective antenna tilt management is the single most important key to more informative weather radar displays The prime factors must be kept in mind for proper tilt management e The center of the radar beam is referenced to the horizon by the aircraft vertical reference system e Adjusting the antenna tilt control will cause the center of the radar beam to scan above or below the plane of the attitude reference system When flying at high altitudes the use of proper tilt management ensures observation of weather targets without over scanning For example a low altitude storm detected on the long range setting may disappear from the display as it is approached While it may have dissipated during your approach toward the storm don t count on it It may be that you are directing the radiated energy from the antenna above the storm as you get closer Judicious management of the antenna tilt control will avoid over scanning a weather target EARLY DETECTION OF ENROUTE WEATHER To set the antenna tilt to optimize the radar s a
26. is normal or FUEL PUMP switch is OFF 10 11 16 19 FUEL PUMP Switch ON activates fuel pump OFF deactivates fuel pump 12 15 Main Tank Fuel Pump LOW PRESSURE Light Illuminated amber fuel pump output pressure is low or FUEL PUMP switch is OFF Note Two LOW PRESSURE lights illuminated in same tank illuminates MASTER CAUTION and FUEL system annunciator lights One LOW PRESSURE light causes MASTER CAUTION and FUEL system annunciator lights to illuminate on MASTER CAUTION light recall Extinguished fuel pump output pressure is normal CO7 FUEL QUANTITY INDICATIONS 1 Fuel Quantity Test Switch 2 4 Fuel Quantity Indicator i 4 Ns 2 FUEL EN 1 Fuel Quantity Test QTY TEST Switch Indicator test is described in Supplementary Procedures 2 4 Fuel Quantity Indicator e indicates usable fuel in the related tank e standby AC power is required www captainsim com CU gt 2 C 737 Captain FLIGHT MANUAL Part II Aircraft Systems 124 DO NOT USE FOR FLIGHT CO6 TOTAL FUEL AND VREF INDICATOR 1 Zero Fuel Weight Counter 2 Landing Flap Selector 3 Vref Pointer 4 Total Fuel Weight Counter 5 Zero Fuel Weight Selector 1 ZERO FUEL Weight Counter Indicates airplane zero fuel weight selected by the ZERO FUEL weight selector 2 Landing Flap Selector Adjusts the VREF pointer for the landing flap setting 3 Vref Pointer Indica
27. normal temperature rise indicates excessive generator load or poor condition of the generator drive Lack of adequate cooling will generally cause the temperature RISE to decrease 5 Standby Power STANDBY PWR OFF Light Illuminated amber AC standby bus is inactive 8 STANDBY POWER Switch AUTO guarded position e In flight or on the ground and AC transfer busses powered AC standby bus is powered by AC transfer bus 1 DC standby bus is powered by DC bus 1 In flight loss of all AC power AC standby bus is powered by the battery bus through the static inverter DC standby bus is powered by the battery bus On the ground loss of all AC power No automatic transfer of power AC and DC standby busses are not powered on 737 200 models with unmodified standby system OFF center position e STANDBY PWR OFF light illuminates e standby bus static inverter and DC standby bus are not powered BAT unguarded position e AC standby bus is powered by the battery bus through the static inverter e DC standby bus is powered by the battery bus 9 Drive Temperature DRIVE TEMP Switch RISE IN Selects RISE or IN temperature to be displayed on the GEN DRIVE OIL TEMP indicator Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 68 DO NOT USE FOR FLIGHT 009 GROUND POWER AND GEN AMMETERS PANEL 1 4 Ammeter Gab POWER 2 Ground Power Available Light canda 3 Ground Powe
28. officer panel instruments backlight Control 012 OVERHEAD CIRCUIT BREAKER PANEL LIGHT CONTROLS 1 Circuit Breaker instruments backlight Control CIRCUIT BEARER 2 Overhead Panel and and standby magnetic compass controls compass instruments backlight Control FLOOD AND AFT ELECTRONIC PANEL LIGHTS CONTROLS P16 FLOOD LIGHT CONTROLS 2 Captain s Flood Light Control 3 First Officer s Flood Light Control 1 White Dome Light Control 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 25 DO NOT USE FOR FLIGHT C01 MASTER LIGHTS TEST SWITCH 1 Master Lights Test Switch O06 LANDING RUNWAY TURNOFF AND TAXI LIGHTS 1 2 Outboard Landing Light Switch 3 Position 3 4 Inboard Landing Light Switch 5 6 Runway Turnoff Light Switch 7 Taxi Light Switch 1 2 OUTBOARD LANDING Light Switch 3 position RETRACT outboard landing lights are retracted and extinguished EXTEND outboard landing lights are extended and extinguished ON outboard landing lights are extended and illuminated 3 4 INBOARD LANDING Light Switch OFF inboard landing lights are extinguished ON inboard landing lights are illuminated 5 6 RUNWAY TURNOFF Light Switch OFF runway turnoff lights located in leading edge of wing root are extinguished ON runway turnoff lights are illuminated 7 TAXI Light Switch OFF nose wheel taxi light extinguished ON nose wheel taxi light i
29. or down left click for best indicator presentation 3 GAIN Control The gain control adjusts the radar GAIN PREFLIGHT PROCEDURES The system never transmits in the OFF STBY or TEST modes Note A 60 second warm up time period is required before the system will transmit 1 Place the radar controls in the following positions e Function switch to TEST e Tilt to UP 7 The test pattern will appear 2 With the function switch in TEST or STBY taxi to a clear area where there are no people aircraft vehicles or metallic buildings within approximately 100 yards 3 Rotate the function switch to NORM The indicator will automatically display in the Wx mode Weather targets will be displayed in grades of amber 4 Select 50 nm range 5 Select CTR mode to observe black contour areas if any 6 Repeat the manual tilt adjustment this time between the 0 and down 15 degrees positions 7 Return the function switch to TEST or STBY before taxiing 8 When you are ready for weather detection after takeoff or just before place the function switch to NORM 737 Captain FLIGHT MANUAL Part II Aircraft Systems 118 DO NOT USE FOR FLIGHT OPERATION IN FLIGHT GENERAL It is the purpose of this section to help you become a proficient radar operator as soon as possible However it is realized that proficiency can only improve with usage It is therefore recommended that the operator become familiar with the operation of the system
30. plugged into HEADSET jack O15 CALL SYSTEM 1 Ground Call Switch 2 Attendant Call Switch 3 Flight Deck Call Light 1 Ground Call GRD CALL Switch Push sounds a horn in nose wheel well until released 2 Attendant Call ATTEND CALL Switch Push e sounds a two tone chime in the passenger cabin 3 Flight Deck CALL Light Illuminated blue flight deck is being called by flight attendants or ground crew Extinguished when Captain Call or Pilot Call switch released 2012 Captain Sim www captainsim com GHT MANUAL Part II Nircraft Systems 62 DO NOT USE FOR FLIGHT ELECTRICAL SYSTEM DESCRIPTION Primary electrical power is provided by two engine driven generators which supply three phase 115 volt 400 cycle alternating current Each generator supplies its own bus system in normal operation and can also supply essential loads of the opposite side bus system when one generator is inoperative Transformer rectifier TR units and a battery supply DC power The battery also provides backup power for the AC and DC standby systems The APU operates a generator and can supply power to both AC generator busses on the ground or one AC generator bus in flight There are two basic principles of operation for the 737 electrical system e There is no paralleling of the AC sources of power e source of power being connected to a generator bus automatically disconnects an existing source The electrical power system may
31. selected speeds HOLDING Holding Used to obtain holding EPR speed and endurance time CON Continuous Provides maximum continuous EPR limit and engine out data GA Go Around Displays go around EPR limit for existing altitude and temperature 5 ENGAGE KEY PRESS with a flight mode selected e Drives the EPR and or airspeed bugs to the displayed values The key light extinguishes and the engaged mode is displayed on the flight mode annunciator Other CDU displays can be selected without changing the engaged mode ILLUMINATED Indicates the data displayed is not driving the bugs When a performance function is displayed the Engage Key does not illuminate since performance functions cannot be engaged 12 Captain Sim www captainsim com 79 DO NOT USE FOR FLIGHT 6 BRT brightness Control ROTATE Controls CRT brightness 7 SEL Select Key PRESS e Moves the Caret down one line each time it is pressed e possible Caret positions are limited to those lines which display an asterisk e Caret cycles to the top line if at the lowest line 8 CLR Clear Key PRESS e Causes data on the line corresponding to the Caret to be removed from the display e The CLR key must be pressed any time a new numeric entry is desired 9 ENT Enter PRESS Commands the computer to accept the data which has been keyed in and displayed 10 KEYBOARD e The keyboard contains double function keys for entering numerics
32. the APU bleed air valve Shutdown can also be accomplished by pulling the APU fire switch CONTROLS AND INDICATORS C09 ENGINE INSTRUMENTS PRIMARY PANEL 1 2 Engine Pressure Ratio Indicator 3 4 EPR Reference Selector 5 6 N1 Rpm Indicator 7 8 Exhaust Gas Temperature Indicator 9 10 N2 Indicator 11 12 Fuel Flow Indicator 1 2 Engine Pressure Ratio EPR Indicator e Indicates the ratio of turbine discharge pressure Pt7 to compressor inlet pressure Pt2 e Used as the primary thrust setting reference e Provides digital display of indicated EPR Read EPR on outer scale and in the large upper digital display for thrust settings 3 4 EPR Reference Selector ROTATE an M indicating manual mode appears on the dial face positions the EPR reference bug and changes the reference EPR digital readout in the lower window correspondingly 5 6 RPM Indicator e Indicates low pressure compressor speed in percent of RPM e Self powered 7 8 Exhaust Gas Temperature Indicator e Indicates turbine exhaust gas temperature in degrees C as sensed by thermocouples e Uses AC power from the Standby Bus 737 Captain FLIGHT MANUAL Part II Aircraft Systems 76 DO NOT USE FOR FLIGHT 9 10 N2 Indicator e Indicates high pressure compressor speed in percent of RPM e Self powered 11 12 Fuel Flow Indicator Indicates fuel consumption rate in pounds per hour 610 ENGINE INSTRUMENTS
33. www captainsim com Aircraft Systems 4 DO NOT USE FOR FLIGHT FLIGHT CONTROLS SYSTEMS DESCRIPTION The primary flight control system uses conventional control wheel column and pedals linked mechanically to hydraulic power control units which command the primary flight control surfaces ailerons elevators and rudder The flight controls are powered by redundant hydraulic sources system A and system B Either hydraulic system can operate all primary flight controls The ailerons and elevators may be operated manually if required The rudder may be operated by the standby hydraulic system if system A and system B pressure is not available The secondary flight controls high lift devices consisting of trailing edge TE flaps and leading edge LE flaps and slats LE devices are powered by hydraulic system A In the event hydraulic system A fails the TE flaps can be operated electrically The leading edge devices may be extended by the Standby hydraulic system No alternate retraction system is provided for the leading edge devices PILOT CONTROLS The pilot controls consist of two control columns two control wheels two pairs of rudder pedals SPEED BRAKE lever FLAP lever stabilizer trim wheel AILERON trim wheel RUDDER trim wheel YAW DAMPER switch The control wheels are connected through transfer mechanisms which allow the pilots to bypass a jammed control or surface There is a rigid connection between both pairs of rudde
34. 012 Captain Sim www captainsim com 21 DO NOT USE FOR FLIGHT LIGHTING Lighting systems described include e exterior lighting e flight deck lighting EXTERIOR LIGHTING Exterior lighting consists of these lights e landing runway turnoff taxi position navigation anti collision wing illumination wheel well OUTBOARD LANDING LIGHTS Outboard landing lights are installed in the outboard flap track fairings The lights are designed to extend and shine forward parallel to the waterline of the airplane The lights may be extended at any speed INBOARD LANDING LIGHTS Two inboard landing lights are in the wing leading edge The lights shine forward and down in a fixed position RUNWAY TURNOFF LIGHTS Runway turnoff lights are in each wing root The lights illuminate the area in front of the main gear TAXI LIGHTS The taxi light is mounted on the nose wheel strut and points in the same direction as the nose wheel The light will not extinguish automatically when the nose gear is retracted For increased service life of the taxi light it is recommended that the taxi light not be used for takeoffs or landings POSITION LIGHTS The navigation lights are the standard red left forward wingtip green right forward wingtip and white aft tip of both wings position lights ANTI COLLISION LIGHTS Two red anti collision strobe lights are located on the top and bottom of the fuselage WING ILLUMINATION LIGHTS Wing li
35. 1 antenna is located on the upper fuselage VHF 2 on the lower fuselage CONTROLS AND INDICATORS P12 P13 VHF COMMUNICATION PANEL 7 Frequency Indicator 8 Frequency Selector 9 Communication COMM Test Switch 1 Frequency Indicator Indicates selected frequency 2 Frequency Selector Rotate selects frequency in related indicator e outer selector changes three left digits e middle selector changes two right digits e inner selector changes receiver volume but not side tone 3 Communication COMM TEST Switch Push e removes automatic squelch feature permitting reception of background noise and thereby testing receiver operation e improves reception of weak signals 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 61 DO NOT USE FOR FLIGHT P14 P15 A08 AUDIO SELECTOR PANEL ASP 1 6 13 Transmitter Light 1 6 7 12 17 20 23 24 Receiver Switches 14 Filter Switch 15 Transmitter Selector T 16 Volume Control 21 Push to Talk Switch 14 EF 22 Oxy Boom Switch 18 18 24 024 COCKPIT VOICE RECORDER E 3 1 Area Microphone e mm 2 Monitor Indicator oN C er 3 Test Switch ff oN d ERASE 4 Erase Switch p 5 Headset Jack HEADSET tal COCKPIT VOICE RECORDER 3 TEST Switch Push e after a slight delay monitor indicator rises into green band e atone may be heard through a headset
36. 12 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 81 DO NOT USE FOR FLIGHT Low Oil Quantity Light APU Low Oil Pressure Light APU High Oil Temperature Light APU Overspeed Light APU Exhaust Gas Temperature EGT Indicator APU Generator AC Ammeter LOW OFL LOW OIL HIGH OIL OVER r 1 PRESSURE TEMP 3 k PE N N 1 Low Oil Quantity Light Illuminated blue APU oil quantity is insufficient for extended operation Light is disarmed when APU switch is OFF 2 APU LOW OIL PRESSURE Light Illuminated amber e during start until the APU oil pressure is normal e oil pressure is low causing an automatic shutdown after start cycle is complete e light is disarmed when APU switch is OFF 3 APU HIGH OIL TEMPERATURE Light Illuminated amber e APU oil temperature is excessive causing APU to initiate an automatic shutdown e light is disarmed when APU switch is OFF 4 APU OVERSPEED Light Illuminated amber e APU RPM limit has been exceeded resulting in an automatic shutdown e overspeed shutdown protection feature has failed a self test during a normal APU shutdown e APU start is aborted prior to reaching governed speed light will extinguish following a normal start e light is disarmed when APU switch is OFF 5 APU Exhaust Gas Temperature EGT Indicator Displays APU EGT 6 APU Generator AC Ammeter Displays APU generator load current 20
37. 12 Captain Sim www captainsim com 82 DO NOT USE FOR FLIGHT O17 APU SWITCH OFF normal position when APU is not running positioning switch to OFF with APU running initiates APU shutdown trips APU generator off the bus es if connected and closes APU bleed air valve ON normal position when APU is running START momentary positioning APU switch from OFF to START and releasing it to ON initiates an automatic start sequence 737 Captain FLIGHT MANUAL Part II Aircraft Systems 83 DO NOT USE FOR FLIGHT FIRE PROTECTION SYSTEM DESCRIPTION There are fire detection and extinguishing systems for engines e lavatories APU e cargo compartments The engines also have overheat detection systems The main gear wheel well has a fire detection system but no fire extinguishing system ENGINE FIRE EXTINGUISHER SCHEMATIC L BOTTLE DISCHARGE CONTROLS AND INDICATORS P11 OVERHEAT FIRE PROTECTION PANEL SWITCHES LIGHTS 1 7 Overheat Detector Switch 2 Wheel Well Fire Warning Light 3 APU Detector Inoperative Light 4 APU Fire Warning Switch 5 Fire Warning Bell Cutout Switch 6 10 Engine Overheat Light 8 9 Engine Bottle Discharge Light 11 Overheat Inoperative and Fire Test Switch 12 16 Engine Fire Warning Switch 13 15 17 Fire Warning Switch Override 14 APU Bottle Discharge Light 18 Extinguisher Test Switch 19 Extinguisher Test Lights 2012 Captain Sim
38. 26 AIR CONDITIONING CONTROLS AND INDICATORS CONT CABIN AIR TEMP 5 CABIN 1 3 Air Mix Valve Indicator 2 SUPPLY PASS 2 Air Temperature Source Selector 4 6 Duct Overheat Light 5 Air Temperature Indicator 1 3 7 Control Cabin Temperature Selector 8 Passenger Cabin Temperature Selector m a 5 7 1 3 AIR MIX VALVE Indicator Indicates position of air mix valves e controlled automatically with related temperature selector in AUTO e controlled manually with related temperature selector in MANUAL 2 AIR Temperature TEMP Source Selector SUPPLY DUCT selects main distribution supply duct sensor for TEMP indicator PASS CABIN selects passenger cabin sensor for TEMP indicator 4 6 DUCT OVERHEAT Light Illuminated amber e bleed air temperature in related duct exceeds limit e air mix valves drive full cold e requires reset 5 Air Temperature TEMP Indicator Indicates temperature at location selected with AIR TEMP source selector 7 8 Control CONT CABIN and Passenger PASS CABIN Temperature Selector AUTO automatic temperature controller controls passenger cabin or flight deck temperature as selected MANUAL air mix valves controlled manually Automatic temperature controller bypassed 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 41 DO NOT USE FOR FLIGHT O13 EQUIPMENT COOLING PANEL 1 Equipment Cooling OFF Light EQUIP
39. AGEMENTS 50 AUTOPILOT REVERT TO MAN CONDITIONS 51 CONTROL WHEEL STEERING CWS DO NOT USE FOR FLIGHT 51 FLIGHT DIRECTOR 53 ALTITUDE ALERT SYSTEM 53 GO AROUND SWITCH 54 W02 CONTROL WHEEL 54 L16 GPS NAV SWITCH 54 L10 R10 AUTOPILOT DISENGAGE LIGHT RED 54 C03 STABILIZER OUT OF TRIM LIGHT AMBER 55 G03 AUTOPILOT PANEL 57 L12 12 APPROACH PROGRESS DISPLAY 57 G02 G04 FLIGHT DIRECTOR 59 ALTITUDE ALERT 60 JCOMMUNICATIONS 60 CALL SYSTEM 60 VHF COMMUNICATIONS 60 P12 P13 VHF COMMUNICATION PANEL 61 P14 P15 AUDIO SELECTOR PANEL ASP 61 024 COCKPIT VOICE RECORDER 61 015 CALL SYSTEM ELECTRICAL 62 AC POWER SYSTEM 63 DC POWER SYSTEM 64 STANDBY POWER SYSTEM 65 ELECTRICAL PANEL 66 O07 AC AND DC METERING PANEL 67 008 GENERATOR DRIVE AND STANDBY POWER PANEL 68 009 GROUND POWER AND GEN AMMETERS PANEL 68 010 BUS SWITCHING 70 5 APU D l h l D l i l i l i 5 88 70 POWER PLANT SCHEMATIC 70 ENGINE FUEL SYSTEM 70 OIL SYSTEM 70 ENGINE START SYSTEM 70 ENGINE IGNITION SYSTEM 4 POSITION START SWITCH 70 THRUST REVERSER 72 PDCS SYSTEM DESCRIPTION 74 APU SYSTEM 75 C09 ENGINE INSTRUMENTS PRIMARY PANEL 76 C10 ENGINE INSTRUMENTS SECONDARY PANEL DO NOT USE FOR FLIGHT 76 C11 ENGINE OIL QUANTITY TEST SWITCH 77 O18 ENGINE START SWITCHES 77 P10 ENGINE CONTROLS 77 A05 THRUST REVERSER OVERRIDE SWITCHES 78 P03 PDCS CONTROL DISPLAY UNIT CDU 79 PDCS DISPLAY
40. AV receiver No 1 mL e NORMAL VHF navigation source is from default as 8 VHF NAV receiver a ui I e BOTH ON 2 switches the VHF navigation source to E ditus VHF NAV receiver No 2 NORMAL 737 Captain FLIGHT MANUAL Part II Aircraft Systems 113 DO NOT USE FOR FLIGHT SECONDARY NAVIGATION SYSTEMS P07 IRANSPONDER PANEL Wg 1 Transponder Mode Selector 2 Transponder ATC Switch STE ATC AT Gans ay 3 5 ATC Code Selector es om BEB ED 4 ATC Identification Switch 5 _ TEAS RANGE 9 6 Code Indicator y m HE EA 7 ATC Fail Light gt Traffic Collision Avoidance System TCAS Range 2 iari Selector 9 Flight Level Switch 10 TAU Envelope Switch 1 Transponder Mode Selector TEST starts ATC transponder functional test STBY does not transmit Note Transponder modes are enabled only when the airplane is airborne except for mode S which operates continuously when the transponder mode selector is out of STBY ALT OFF deactivates altitude reporting ALT ON enables altitude reporting TA enables display of traffic advisory TCAS targets TA RA enables display of traffic advisory and resolution advisory TCAS targets 3 5 ATC Code Selector Rotate sets transponder code in transponder 6 ATC Code Indicator Displays transponder code Displays operating transponder 1 or 2 Displays response indicator
41. AY 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 29 DO NOT USE FOR FLIGHT PILOTS EYE LOCATOR To assist the pilot in obtaining the optimum eye position for panel scan and runway visibility an eye locator is installed on the center windshield post For the optimum eye position the three spheres should be lined up CONTROLS AND INDICATORS To operate the doors use Animation Control Panel O23 EXTERIOR DOOR ANNUNCIATOR LIGHTS 2 9 Door Annunciations Illuminated amber related door is unlocked 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 30 DO NOT USE FOR FLIGHT LOWER CARGO COMPARTMENTS The lower cargo compartments if equipped with smoke and fire detectors and with a built in fire extinguisher system controlled from the flight deck satisfy the requirements for Class C compartments There are two cargo compartment doors on the lower right side of the fuselage Both are plug type inward opening pressure doors hinged at their upper edges and operated manually from either inside or outside the airplane Except for slight difference in shape both doors are similar in design and operation The door is locked closed by four latches AUX FUEL TANK As installed 3 CARGO DOOR _ KE in by 48 CARGO FWD CARGO COMPARTMENT COMPARTMENT
42. Altitude Selector Flight Ground Switch Pressurization Mode Selector Cabin Flight Altitude Placard Illuminated amber automatic pressurization control failure Control automatically transfers to the standby mode 2 OFF Schedule SCHED DESCENT Light Illuminated amber airplane descended before reaching the planned cruise altitude set in the FLT ALT indicator 3 Manual Light Illuminated green pressurization system operating in the manual mode STANDBY Light Illuminated green pressurization system operating in the standby mode 5 Flight Altitude FLT ALT Indicator indicates selected cruise altitude set before takeoff 6 Flight Altitude Selector Push Rotate to set planned cruise altitude 7 Landing Altitude LAND ALT Indicator e indicates altitude of intended landing field set before takeoff 8 Landing Altitude Selector Rotate to select planned landing field altitude e large diameter control sets 1000 foot increments and negative elevations e Small diameter control sets 10 foot increments www captainsim com 43 DO NOT USE FOR FLIGHT 9 Cabin Rate Selector e DECR cabin altitude rate of change equals 50 ft min e INCR cabin altitude rate of change equals 2000 ft min e Index cabin altitude rate of change equals 300 ft min 10 Outflow VALVE Position Indicator e indicates position of outflow valve e operates in all modes Note Indicator moves to the ful
43. D INDICATORS FLIGHT RECORDER MACH AIRSPEED WARNING AND STALL WARNING TEST SWITCHES 2012 Captain Sim www captainsim com 17 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT FORWARD ELECTRONIC PANEL P01 P06 AUTOMATIC DIRECTION FINDING ADF CONTROL P02 WEATHER RADAR CONTROL PANEL P03 PDCS CONTROL DISPLAY UNIT CDU P04 ALTITUDE ALERT CONTROLLER 05 WEATHER RADAR PANEL P07 IRANSPONDER PANEL P08 HF COMMUNICATION PANEL P09 SELCAL PANEL 2012 Captain Sim www captainsim com PIERIT TEST 2350 5 1 EDF P TAE 6 AL e 09 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT AFT ELECTRONIC PANEL 5 NEAR Hh 1 war m Lilian rra 000 000 um TAJM NET LA ET P11 OVERHEAT FIRE PROTECTION PANEL SWITCHES LIGHTS P12 P13 VHF NAVIGATION CONTROL VHF COMMUNICATION PANEL P14 P15 AUDIO SELECTOR PANEL ASP P16 CABIN DOOR 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 20 DO NOT USE FOR FLIGHT CONTROL STAND 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT AUXILIARY PANELS S01 MAP LIGHT CONTROLS 2
44. DO NOT USE FOR FLIGHT 4 Captain FLIGHT MANUAL PART II Aircraft Systems DO NOT USE FOR FLIGHT VERSION 05 MAY 2012 WARNING THIS MANUAL IS DESIGNED FOR MICROSOFT FSX USE ONLY DO NOT USE FOR FLIGHT The 737 Captain FLIGHT MANUAL is organized into four Parts Each Part is provided as a separate Acrobat PDF document e Part I User s Manual o The User s Manual describes the 737 Captain Sim product as a software title e Part II Aircraft Systems this document e Part III Normal Procedures e Part IV Flight Crew Training Manual Adobe Acrobat Reader Required FOR GENERAL INFORMATION ON THE 737 CAPTAIN PRODUCT PLEASE USE WWW CAPTAINSIM COM THIS MANUAL PROVIDES ADDITIONAL INFORMATION ONLY WHICH IS NOT AVAILABLE ON THE WEB SITE DO NOT USE FOR FLIGHT 737 Captain FLIGHT MANUAL 3 SYSTEM DESCRIPTION 9 CONTROLS ANIMATION SWITCHES BUTTONS KNOBS LAMPS 10 AIRPLANE GENERAL 10 11 11 12 13 14 15 16 17 18 19 20 21 PRINCIPAL DIMENSIONS INSTRUMENT PANELS PANEL ARRANGEMENT AFT FLIGHT DECK OVERVIEW CAPTAIN S INSTRUMENT PANEL FIRST OFFICER S INSTRUMENT PANEL CENTER INSTRUMENT PANEL AND LIGHTSHIELD FORWARD OVERHEAD PANEL AFT OVERHEAD PANEL FORWARD ELECTRONIC PANEL AFT ELECTRONIC PANEL CONTROL STAND AUXILIARY PANELS 22 JLIGHTING 22 23 23 23 24 24 24 25 25 26 EXTERIOR LIGHTING FLIGHT DECK LIGHTING S01 MAP LIGHT CONTROLS
45. EM 28 volt DC power is supplied by three TR units which are energized from the AC transfer busses and main bus 2 The battery provides 28 V DC power to loads required to be operative when no other source is available TRANSFORMER RECTIFIER UNITS The TRs convert 115 volt AC to 28 volt DC and are identified as TR1 TR2 and TR3 TR1 and TR2 receive AC power from transfer bus 1 and transfer bus 2 respectively TR3 receives AC power from main bus 2 Under normal conditions TR1 and TR2 are each powering DC bus 1 and DC bus 2 TR3 powers the battery bus and serves as a backup power source for TR1 and TR2 with the Bus Transfer Switch in the AUTO position e Maximum TR Load with cooling 65 amps e Maximum TR Load without cooling 50 amps e TR voltage range 24 30V 2012 Captain Sim www captainsim com gt 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT 64 BATTERY POWER A 24 volt nickel cadmium battery is located in the electronics compartment The battery can supply part of the DC system Battery charging is automatically controlled A fully charged battery has sufficient capacity to provide standby power for a minimum of 30 minutes Battery voltage range is 22 30 volts DC busses powered from the battery following a loss of both generators are e battery bus e DC standby bus e hot battery bus The hot battery bus is always connected to the battery There is no switch in this
46. ERNATE FLAPS 14 Mach Test switch oF 15 Mach Trim Failure Light ot ag DOWN 9 PRESS amp ET YAW DAMPER MACH TRIM 12 15 13 O TEST na L Er STABILIZER P10 STABILIZER CONTROLS 13 Stabilizer Trim Indicator Indicates units of airplane trim on the adjacent scale 14 Stabilizer Trim Green Band Range Corresponds to allowable range of trim settings for takeoff 2012 Captain Sim www captainsim com 12 Stabilizer Trim Wheel 13 Stabilizer Trim Indicator 14 Stabilizer Trim Green Band Range 15 Stabilizer Trim Light 16 Stabilizer Trim Main Electric Cutout Switch 17 Stabilizer Trim Autopilot Cutout Switch 12 Stabilizer Trim Wheel e provides for manual operation of stabilizer e overrides any other stabilizer trim inputs e rotates when stabilizer is in motion Note handle should be folded inside stabilizer trim wheel for normal operation 737 Captain FLIGHT MANUAL Part II Aircraft Systems 87 DO NOT USE FOR FLIGHT 15 Stabilizer Trim Light Illuminated amber indicates main electric trim motor is operating 16 Stabilizer Trim Main Electric MAIN ELECT Cutout Switch NORMAL normal operating position CUTOUT INOP 17 Stabilizer Trim AUTOPILOT Cutout Switch NORMAL normal operating position CUTOUT INOP WO01 W02 CONTROL WHEEL 2 3 Stabilizer Trim Switches Push both electrically commands stabilizer trim in desir
47. G GEAR IASI ow GEH IM BE ND b GEAR LITEIT 118532 SEA TI kah KETENG Ee 7 LANDING GEAR Lever UP landing gear retract 1 3 4 Landing Gear Indicator Lights top 2 5 6 Landing Gear Indicator Lights bottom 7 Landing Gear Lever 8 Override Trigger 9 Landing Gear Limit Speed Placard 1 3 4 Landing Gear Indicator Lights top Illuminated red e landing gear is not down and either thrust lever is retarded to idle e related landing gear is in disagreement with LANDING lever position in transit or unsafe e gear is down and locked and lever is not in the down detent Extinguished e landing gear is up and locked with landing gear lever UP or OFF e landing gear is down and locked with landing gear lever DN 2 5 6 Landing Gear Indicator Lights bottom Illuminated green related gear down and locked Note Landing gear warning horn is deactivated with all gear down and locked Extinguished landing gear is not down and locked OFF hydraulic pressure is removed from landing gear system DN landing gear extend 8 Override Trigger Allows LANDING GEAR lever to be raised bypassing lever lock 9 LANDING GEAR LIMIT Speed Placard Indicates maximum speed while operating landing gear and after gear extension 737 Captain FLIGHT MANUAL Part II Aircraft Systems 131 DO NOT USE FOR FLIGHT 614 AUTOBRAKE AND ANTISKID CONTROLS 1 2 Antiskid Inoper
48. GHT CONTROLS AND INDICATORS O27 BLEED AIR CONTROLS AND INDICATORS 1 Dual Bleed Light 2 4 RAM Door Full Open Light lt 3 4_ 3 Out Flow Closed Light 5 Bleed Air Duct Pressure Indicator 7 16 Air Conditioning Pack Switch pan MAL PIN 6 Isolation Valve Switch 8 17 Pack Trip Off Light 9 18 Wing Body Overheat Light 10 19 Bleed Trip Off Light 12 Trip Reset Switch 11 20 Engine Bleed Air Switches 13 APU Bleed Air Switch 14 Gasper Fan Switch 15 Wing Body Overheat Test Switch 1 DUAL BLEED Light te Illuminated amber e Either APU bleed air valve open and engine No 1 BLEED air valve open or e APU bleed air valve open engine No 2 BLEED air valve open and ISOLATION VALVE open 2 4 RAM DOOR FULL OPEN Light Illuminated blue indicates ram door in full open position 5 Bleed Air DUCT PRESSURE Indicator Indicates pressure in L and R left and right bleed air ducts 6 ISOLATION VALVE Switch CLOSE closes isolation valve AUTO e closes isolation valve if all engine BLEED air and air conditioning PACK switches ON e opens isolation valve automatically if either engine BLEED air or air conditioning PACK switch positioned OFF OPEN opens isolation valve 7 16 Air Conditioning PACK Switch OFF pack signalled OFF ON opens pack valve to allow bleed air to enter pack Valve is electrically controlled pneumatically operated 8 17 PACK TRIP OFF Light Illumina
49. GPWS CONTROLS AND INDICATORS L01 RO1 PULL UP WARNING LIGHT BELOW GLIDE SLOPE ALERT LIGHT 1 Pull Up Warning Light PULL UP 2 Below Glide Slope G S Alert Light Ep BELOW 6 5 P INHIBIT 1 PULL UP Warning Light Illuminated red indicates one or more of the following exist e excessive descent rate e excessive terrain closure rate e altitude loss after takeoff or go around e unsafe terrain clearance when not in the landing configuration 2 BELOW Glide Slope G S Alert Light Illuminated amber airplane is more than 1 3 dots below glide slope Push inhibits or cancels below glide slope alerting if pushed while in alerting area 2012 Captain Sim www captainsim com 138 DO NOT USE FOR FLIGHT R16 GPWS PANEL 1 GPWS Inoperative Light 2 Ground Proximity System Test Switch 3 Ground Proximity Flap Gear Inhibit Switch GROUND PROXIMITY FLAP GEAR INHIBIT sis TEST NORMAL 1 GPWS Inoperative INOP Light Illuminated amber GPWS computer malfunction or power loss e invalid inputs are being received from the VHF NAV receiver ADC or radio altimeter 2 Ground Proximity System SYS TEST Switch Push momentarily on ground with landing gear not in landing configuration or above 1 000 feet radio altitude in flight with gear up and flaps in any configuration e iluminates BELOW G S PULL UP and INOP lights and causes the GLIDE SLOPE and WHOOP WHOOP PULL UP
50. ITCH FUEL CONTROL PANEL LANDING RUNWAY TURNOFF AND TAXI LIGHTS AC AND DC METERING PANEL GENERATOR DRIVE AND STANDBY POWER PANEL GROUND POWER AND GEN AMMETERS PANEL BUS SWITCHING APU OVERHEAD CIRCUIT BREAKER PANEL LIGHT CONTROLS EQUIPMENT COOLING PANEL FLIGHT DECK EMERGENCY LIGHTING AND PASSENGER SIGNS O15 CALL SYSTEM 2012 Captain Sim www captainsim com po weh ds G S G Pri gre r Hy 18 O16 O18 O19 O20 O21 O22 O23 O24 O25 O26 O27 O28 O29 O31 a YR RUMPL lt WINDSHIELD WIPER PANEL ENGINE START SWITCHES WINDOW HEAT PANEL PITOT STATIC HEAT PANEL WINGS ENGINE ANTI ICE PANEL HYDRAULIC PANEL EXTERIOR DOOR ANNUNCIATOR LIGHTS COCKPIT VOICE RECORDER CABIN ALTITUDE PANEL AIR CONDITIONING CONTROLS AND INDICATORS BLEED AIR CONTROLS AND INDICATORS CABIN PRESSURIZATION PANEL MISCELLANEOUS EXTERIOR LIGHTS STANDBY MAGNETIC COMPASS 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT AFT OVERHEAD PANEL 01 02 A04 A05 A07 08 A09 A10 A11 oco OO OO Oo O Ch D Q G Q Qh gt mf sas 1555 OO Ch GQ Ch O Q Ca oOo OOOO ooo ALTITUDE ALERT SPEAKER LEADING EDGE DEVICES LE DEVICES ANNUNCIATOR PANEL SPEAKER THRUST REVERSER OVERRIDE SWITCHES DOME LIGHT CONTROL AUDIO SELECTOR PANEL ASP OXYGEN CONTROLS AN
51. Ice Switch 11 Wing Anti Ice Switch L VALVE VALVE OPEN 1 2 Wing Anti Ice OPEN Lights Illuminated blue e bright related wing anti ice control valve is in transit or related wing anti ice control valve position disagrees with WING ANTI ICE switch position dim related wing anti ice control valve is open switch ON Extinguished related wing anti ice control valve is closed switch OFF 3 8 VALVE OPEN Lights Illuminated blue e bright related control valve is in transit or the valve position disagrees with related ENGINE ANTI ICE switch position dim related control valve is open switch ON Extinguished related control valve is closed switch OFF 9 10 ENGINE ANTI ICE Switch ON related engine anti ice valve opens OFF related engine anti ice valve closes 11 WING ANTI ICE Switch OFF wing anti ice control valves close ON in flight wing anti ice control valves open 2012 Captain Sim www captainsim com te 49 DO NOT USE FOR FLIGHT AUTOMATIC FLIGHT SYSTEM DESCRIPTION The autopilot is made of two independent channels roll and pitch and may be used with or without the yaw damper engaged The two channels may be engaged simultaneously or independently and only in the MANUAL mode AUTOPILOT MODES The following modes are available and will be described in detail later in this section e MANUAL e e AUTO APPROACH e MANUAL GLIDE SLOPE I
52. K SWITCH 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 12 DO NOT USE FOR FLIGHT AFT FLIGHT DECK OVERVIEW WHITE DOME WHITE DOME EMERGENCY LIGHT LIGHT EXIT HANDLE VIEVER ee OBSERVER S TAS STOWAGE OXYGEN MASK CAPTAIN S OXYGEN FIRST E OFFICER S OXYGEN PANEL C _ STOWAGE ELECTRONIC MASTER SWITCHES y L CO FIRE EXTINGUISHER BOOK STOVAGE 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT CAPTAIN S INSTRUMENT PANEL L01 R01 PULL UP WARNING LIGHT BELOW GLIDE SLOPE ALERT LIGHT L02 ELECTRIC MACH AIRSPEED INDICATOR L03 RADIO MAGNETIC INDICATOR RMI L04 R04 WINDSHIELD FOOT AIR CONTROLS L05 R05 INSTRUMENT COMPARATOR L06 R06 ATTITUDE DIRECTOR INDICATOR L07 R07 HORIZONTAL SITUATION INDICATOR HSI L09 LIGHTS CONTROL PANEL L10 R10 AUTOPILOT DISENGAGE LIGHT RED L11 R11 MINIMUM DESCENT ALTITUDE MDA LIGHT L12 R12 APPROACH PROGRESS DISPLAY L13 ELECTRIC ALTIMETER L14 R14 VERTICAL SPEED INDICATOR L15 R15 DIGITAL DME INDICATOR L16 GPS NAV SWITCH L17 R17 MARKER BEACON LIGHTS L18 R18 ALTITUDE ALERT LIGHT L19 R19 RADIO ALTIMETER L20 R20 CLOCK 2012 Captain Sim www captainsim com J O N 13 737 Captain FLIGHT MANUAL Part II Aircraft Systems 14 DO NOT U
53. OCATION AND CAPACITIES USABLE FUEL 122 O04 FUEL CONTROL PANEL 123 C07 FUEL QUANTITY INDICATIONS 124 C06 TOTAL FUEL AND VREF INDICATOR 125 JHYDRAULICS 126 022 HYDRAULIC PANEL 127 R22 R23 R25 HYDRAULIC INDICATIONS 128 LANDING GEAR 128 LANDING GEAR OPERATION 128 NOSE WHEEL STEERING 129 BRAKE SYSTEM 130 C15 LANDING GEAR PANEL 131 C14 AUTOBRAKE AND ANTISKID CONTROLS 131 P10 22 23 PARKING BRAKE 131 R21 HYDRAULIC BRAKE PRESSURE INDICATOR 132 RUDDER BRAKE PEDALS 132 NOSE WHEEL STEERING WHEEL 133 WARNING SYSTEMS 134 INTERMITTENT CABIN ALTITUDE CONFIGURATION WARNING 134 LANDING GEAR CONFIGURATION WARNINGS 135 135 136 137 137 DO NOT USE FOR FLIGHT MACH AIRSPEED WARNING SYSTEM GROUND PROXIMITY WARNING SYSTEM GPWS G01 G05 FIRE WARNING AND MASTER CAUTION SYSTEM A11 MACH AIRSPEED WARNING AND STALL WARNING TEST SWITCHES GPWS CONTROLS AND INDICATORS 139 CUSTOMER CARE 139 SPECIAL THANKS TO DO NOT USE FOR FLIGHT SYSTEM DESCRIPTION The 737 Captain is one of the most advanced complete and accurate airliner expansions for MSFS But the 737 Captain same as MSFS itself and any MSFS expansion is a flight simulation software game Therefore this product should not be used as flight training device FTD and or simulator for flight training purposes All items should work as described in this manual If something is not described as functional therefore it does not work or does not exist
54. ONS The landing gear indication lights are activated by signals from each gear the LANDING GEAR lever and the forward thrust lever position as follows Green light illuminated landing gear is down and locked Red light illuminated e landing gear is in disagreement with LANDING GEAR lever position in transit or unsafe e landing gear is not down and locked with either or both forward thrust levers retarded to idle All lights extinguished landing gear is up and locked with the LANDING GEAR lever UP or OFF AURAL INDICATIONS A steady warning horn is provided to alert the flight crew whenever the airplane is in a landing configuration and any gear is not down and locked The landing gear warning horn is activated by forward thrust lever and flap position as follows Flaps 1 through 10 e with either or both forward thrust levers between idle and approximately 10 degrees thrust lever angle the landing gear warning horn can be silenced reset with the landing gear warning HORN CUTOUT switch Flaps 15 or 25 with either but not both forward thrust lever retarded to idle the landing gear warning horn can be silenced reset with the landing gear warning HORN CUTOUT switch with both forward thrust levers set below approximately 30 degrees the landing gear warning horn cannot be silenced with the landing gear warning HORN CUTOUT switch Flaps greater than 25 e regardless of forward thrust lever position the landing gear
55. P Mode In the auto approach AUTO APP mode the VOR LOC light provides the same annunciations as in the VOR LOC mode The GLIDE SLOPE light Illuminates amber at AUTO APP mode selection Illuminates green at glide slope capture 1 3 dot 737 Captain FLIGHT MANUAL Part II Aircraft Systems 50 DO NOT USE FOR FLIGHT AUTOPILOT SCHEMATIC ENGAGEMENT INTERLOCKS The autopilot engage switches will be mechanically locked in the disengage position until the following conditions are satisfied ROLL AIL CHANNEL Autopilot roll computer is valid ADC airspeed signal is valid Vertical and directional gyros are valid B flight control switch is ON No force on control wheel Standby power switch is in AUTO position PITCH ELEV CHANNEL Autopilot pitch computer is valid ADC airspeed signal is valid Vertical gyro is valid Flight control switch is ON Electric trim is not operating A P trim cutout switch is NORMAL No force on control column Standby power switch is in AUTO position AUTOMATIC DISENGAGEMENTS ROLL AND PITCH Automatic disengagement of both channels occurs when e Either autopilot disengage switch is pushed The vertical gyro signal is lost or transferred The airspeed signal from the ADC is lost The B flight control switch is positioned to OFF The autopilot system select switch is repositioned The standby power switch is positioned to BAT ROLL ONLY Automatic disengagement of the roll ch
56. Power on e upto 2500 feet pointer reads true altitude above ground level e above 2500 feet pointer is behind the mask 6 Minimum Descent Altitude MDA Cursor Control Rotate sets the MDA cursor L11 R11 MINIMUM DESCENT ALTITUDE MDA LIGHT 1 Minimum Descent Altitude MDA Light Illuminated amber altitude pointer is at or below MDA cursor setting L03 RADIO MAGNETIC INDICATOR RMI 1 Synchronizing Annunciator 2 ADF VOR Bearing Pointers 3 Compass Warning Flag 4 6 ADF VOR Bearing Pointer Switches 5 Synchronizing Control 7 Scale 1 Synchronizing Annunciator Indicates the compass is out of synchronization if arrow is pointed toward dot or cross 2 ADF VOR Bearing Pointers e narrow pointer uses signals from selected ADF or VOR receiver No 1 e wide pointer uses signals from selected ADF or VOR receiver No 2 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 103 DO NOT USE FOR FLIGHT 3 Compass Warning Flag In view electrical power failure to compass system 4 6 ADF VOR Bearing Pointer Switches Rotate selects ADF or VOR bearing Note Instrument transfer switching table provides VHF NAV signal sources to pointer 5 Synchronizing Control Rotate e synchronizes RMI with compass system e direction of rotation determined by synchronizing annunciator L14 R14 VERTICAL SPEED INDICATOR Two pneumatic vertical speed
57. Remember that hail may fall several miles from the cloud and hazardous turbulence may extend as much as 20 nautical miles therefore echoes should be separated by at least 40 nautical miles before you fly between them As echoes diminish in intensity you can reduce the distance by which you avoid them PATH PLANNING CONSIDERATIONS Avoid cells containing magenta and red areas by at least 20 nautical miles Do not deviate downwind unless absolute necessary Your chances of encountering severe turbulence and damaging hail are greatly reduced by selecting the upwind side of the storm If looking for a corridor remember corridors between two cells containing magenta and or red areas should be at least 40 nautical miles wide from the outer fringes of the radar echo The magenta displays areas of very heavy rainfall and statistically indicates a high probability of hail Note Do not approach a storm cell containing magenta and red any closer than 20 nautical miles Echoes should be separated by at least 40 nautical miles before attempting to fly between them Cells beyond 75 nautical miles are areas of substantial rainfall do not wait for red or magenta to appear Plan and execute evasive action quickly to minimize doglegging E J j Me rod A geal E a ma i ba 20 NM Ba k n 4 CORRIDOR CT in A
58. S TYPICAL 81 O11 APU 83 FIRE PROTECTION 83 P11 OVERHEAT FIRE PROTECTION PANEL SWITCHES LIGHTS 84 JFLIGHT CONTROLS 84 PILOT CONTROLS 85 FLIGHT CONTROL SURFACES 86 O01 FLIGHT CONTROL PANEL 86 STABILIZER 87 RUDDER 88 AILERON ELEVATOR FLIGHT SPOILERS 89 SPEED BRAKES 90 TRAILING EDGE FLAPS 91 P10 FLAP LEVER FLAP GATES 91 LEADING EDGE DEVICES 93 FLIGHT INSTRUMENTS DISPLAYS 93 AIR DATA SYSTEM 93 ANGLE OF ATTACK 94 COMPASS SYSTEMS 94 L06 RO6 ATTITUDE DIRECTOR INDICATOR ADI 96 L07 RO7 HORIZONTAL SITUATION INDICATOR HSI 97 MACH AIRSPEED INDICATOR 97 LO2 ELECTRIC MACH AIRSPEED INDICATOR 99 R13 PNEUMATIC MACH AIRSPEED INDICATOR 100 ALTIMETER 100 L13 ELECTRIC ALTIMETER 100 R24 PNEUMATIC ALTIMETER 101 MARKER BEACON 101 L19 R19 RADIO ALTIMETER 102 LO3 RADIO MAGNETIC INDICATOR RMI 103 L14 R14 VERTICAL SPEED INDICATOR 104 TCAS 106 TOTAL AIR TEMPERATURE 107 L20 R20 CLOCK 108 STANDBY FLIGHT INSTRUMENTS 108 C02 STANDBY HORIZON 109 031 STANDBY MAGNETIC COMPASS 7 DO NOT USE FOR FLIGHT 109 FLIGHT MANAGMENT NAVIGATION 109 RADIO NAVIGATION SYSTEMS 110 SECONDARY NAVIGATION SYSTEMS 111 RADIO NAVIGATION SYSTEMS 112 SECONDARY NAVIGATION SYSTEMS 114 RADAR 114 THEORY OF OPERATION 115 CONTROLS AND INDICATORS 117 PREFLIGHT PROCEDURES 118 OPERATION IN FLIGHT GENERAL 120 FUEL 120 FUEL FEED 120 FUEL SHUTOFF VALVES 120 FUEL TANK L
59. SE FOR FLIGHT FIRST OFFICER S INSTRUMENT PANEL R09 PANEL LIGHT CONTROL R13 PNEUMATIC MACH AIRSPEED INDICATOR R21 HYDRAULIC BRAKE PRESSURE INDICATOR R22 R23 R25 HYDRAULIC INDICATIONS R24 PNEUMATIC ALTIMETER 2012 Captain Sim www captainsim com AL Part II Aircraft Systems 15 DO NOT USE FOR FLIGHT CENTER INSTRUMENT PANEL AND LIGHTSHIELD G01 G02 G03 C01 C02 C03 C04 C05 C06 C07 C08 G05 FIRE WARNING AND MASTER CAUTION SYSTEM G04 FLIGHT DIRECTOR AUTOPILOT PANEL MASTER LIGHTS TEST STANDBY HORIZON STABILIZER OUT OF TRIM LIGHT AMBER FLAPS LIMIT PLACARD SPEED BRAKE LIGHTS TOTAL FUEL AND VREF INDICATOR FUEL QUANTITY INDICATIONS SPEED BRAKE TEST SWITCHES 12 Captain Sim www captainsim com C09 C10 C11 C12 C13 C14 C15 ANXTISKID iNBb OuTBb H ID ih ar ENGINE INSTRUMENTS PRIMARY PANEL ENGINE INSTRUMENTS SECONDARY PANEL ENGINE OIL QUANTITY TEST SWITCH FLAP POSITION INDICATOR LEADING EDGE FLAPS LIGHTS AUTOBRAKE AND ANTISKID CONTROLS LANDING GEAR PANEL O01 O02 O03 O04 O06 O07 O08 O09 O10 O11 O12 O13 O14 737 Captain FLIGHT MANUAL Part II Aircraft Systems 16 DO NOT USE FOR FLIGHT FORWARD OVERHEAD PANEL ALTERNATE FLAP aa 6 TIE c G O0 2 PURI 1 FLIGHT CONTROL PANEL VHF NAV TRANSFER SWITCH VERTICAL GYRO TRANSFER SW
60. Switch is pushed eEither manual disengage switch aileron or elevator is moved to DISENGAGED ePushing the light resets the system after automatic disengagement ILLUMINATED STEADY The self test switch in the E E compartment is on EXTINGUISHED The Autopilot Disengage Switch is released Autopilot Disengage Light is reset PUSH TO RESET STABILIZER OUT OF TRIM LIGHT AMBER Functions only with the Autopilot Elevator Engage STAB OUT Switch ENGAGED OF TRIM ILLUMINATED The stabilizer is out of trim for the condition required by the autopilot 2012 Captain Sim www captainsim com 7 Car art rcraft System 55 DO NOT USE FOR FLIGHT AUTOPILOT PANEL Autopilot Mode Selector Spring Loaded to Man Autopilot System Select Switch Autopilot Heading Switch Autopilot Aileron Roll Engage Switch Autopilot Elevator Pitch Engage Switch Autopilot Pitch Mode Selector CON OUR 1 Autopilot Mode Selector spring loaded to MAN MAN Manual Mode CWS low detent is used to maneuver the airplane with either or both channels engaged e ALT HOLD or TURB is selectable e SEL or HDG OFF is selectable VOR LOC VOR LOC Mode Used to automatically intercept the selected radio course e SEL or CWS is used to achieve the intercept heading e Captain s HSI is used to select heading and course e Course capture occurs at 2 5 dot VOR 2 dots LOC the HDG Switch centers a
61. TION SYSTEM SCHEMATIC VHF VHF NAV 1 2 SECONDARY NAVIGATION SYSTEMS ATC TRANSPONDER Two ATC transponders are installed and controlled by a single control panel The ATC transponder system transmits a coded radio signal when interrogated by ATC ground radar Altitude reporting capability is provided allowing altitude information from the air data computer to be transmitted to an ATC radar facility 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 111 DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS RADIO NAVIGATION SYSTEMS P01 P06 AUTOMATIC DIRECTION FINDING ADF CONTROL 1 Frequency Indicator FREQUENCY _ 2 Frequency Selector 3 ADF Mode Selector 4 Test Switch 5 Tone Switch 1 FREQUENCY Indicator Indicates the frequency selected with the related frequency selector 2 Frequency Selector Rotate outer knob sets the hundreds number middle knob sets the tens number inner knob sets the tenths and ones number 3 ADF Mode Selector OFF removes power from selected receiver ANT only station audio received ADF ADF bearing and station audio received GAIN adjusts receiver gain 4 TEST Switch Push ADF bearing pointer indicates 45 degrees left of lubber line 5 TONE Switch TONE adds tone to receiver audio DISTANCE MEASURING EQUIPMENT DME L15 R15 DIGITAL DME INDICATOR displays slant range to DME station bl
62. Window Heat ON Lights Illuminated green window heat is being applied to selected window Extinguished e switch is OFF or e anoverheat is detected or e a System failure has occurred 9 10 12 13 WINDOW HEAT Switches ON window heat is applied to selected window OFF window heat not in use OVHT simulates an overheat condition PWR TEST provides a confidence test 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 47 DO NOT USE FOR FLIGHT L04 RO4 WINDSHIELD FOOT AIR CONTROLS 1 Windshield Air Controls 2 Foot Air Controls O16 WINDSHIELD WIPER PANEL 1 2 Repellent Switches RAIN REPELLENT Push applies measured amount of repellent on related window 1 3 Windshield WIPER Selector PARK turns off wiper motors and stows wiper blades OFF turns off wiper motors LOW low speed operation HIGH high speed operation 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 48 DO NOT USE FOR FLIGHT O20 PITOT STATIC HEAT PANEL 1 4 7 9 PROBE HEATER Lights CAPT PIS FITOT STATIC ee ee sia Illuminated amber related probe not heated Fig STATIE CAPT STATIC p a 5 6 PITOT STATIC Switches ON power is supplied to heat related system OFF power Off O21 WINGS ENGINE ANTI ICE PANEL 1 2 Wing Anti Ice Valve Open Lights 3 8 Valve Open Lights 9 10 Engine Anti
63. adar transmissions occur until the warm up period is complete TEST The multicolored arc display test pattern is displayed in this mode of operation The test pattern is initialized and sized to fit the 80 nm range and can also be scaled with the range select buttons No radar transmissions occur while TST is selected TEST will appear in the lower left of the display 038 0 ncm STBY Fully energizes the system circuitry but no radar transmissions occur in the SBY mode of operation The antenna is parked at O degrees azimuth and 30 degrees tilt down with the antenna drive motors locked SBY will appear in the lower left of the display 12 Captain Sim www captainsim com 17 DO NOT USE FOR FLIGHT WX CTR selects the WxA weather alert mode of operation WxA will appear in the lower left of the display WXxA colors are Black for no returns Green for weak returns Yellow for moderate returns Red for heavy returns and Magenta for intense returns When the WxA mode is selected magenta areas of storms flash between magenta and black at a 1 HZ rate OFF Removes primary power from the radar indicator but the radar still has power applied The radar will remain active with no radar transmissions occurring for up to a maximum time of 30 seconds This time delay allows time to park the antenna at 0 degrees azimuth and 30 degrees tilt down 2 Antenna Tilt Control Permits manual adjustment of antenna tilt 159 up right click
64. afe to fly between the storms and maintain visual sighting of them RADAR BEAM ILLUMINATION Probably the most important aspect of a weather radar is the antenna beam illumination characteristic To make a proper interpretation of what you are seeing on the display you must have an understanding of what the radar beam is seeing The following figure is a side view of the radar beam characteristic with a storm depicted at a distance that causes the size of the storm to just fill the 3 dB beamwidth This would be the typical situation for a storm at approximately 40 nautical miles with a 12 inch diameter antenna It s important to understand and visualize this situation to enhance your understanding of the rest of this manual 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 115 DO NOT USE FOR FLIGHT ANTENNA GAIN vs ANGLE CHARACTERISTIC S SIDELOBS 3db BEAMWIDTH RADAR REFLECTIVITY What target will reflect the radar s pulses and thus be displayed on the indicator Only precipitation will be detected by an X band weather radar Therefore weather radar does not detect clouds thunderstorms or turbulence directly Instead it detects precipitation which may be associated with dangerous thunderstorms and turbulence The best radar reflectors are raindrops and wet snow or hail The larger the raindrop the better it reflects Because large drops in a small concentrated area are
65. ank with electrical loss dashes when not receiving DME station brightness controlled by center knob located on pilot s light control panel 2012 Captain Sim www captainsim com 112 DO NOT USE FOR FLIGHT P12 P13 VHF NAVIGATION CONTROL 1 Frequency Indicator 2 DME Mode Selector 3 Frequency Selector 4 Volume Selector 5 Navigation Test Switch 6 VOR Test Switch 1 Frequency Indicator Indicates the frequency selected by the frequency selector 2 DME Mode Selector OVRD DME searches to 390 nm DME DME searches to 200 nm Search limited to 50 nm for TVOR TEST Digital DME indicator is blank for one second dashes for one second zeros for as long as held in test position 3 Frequency Selector Rotate manually selects the desired frequency 4 Volume VOL Selector Rotate controls volume of selected station 5 Navigation Test NAV TEST Switch With an ILS frequency selected Rotate Knob Left the glideslope indicates one dot up localizer indicates one dot left Rotate Knob Right the glideslope indicates one dot down localizer indicates one dot right 6 VOR TEST Switch With a VOR frequency tuned and a course of 000 selected Push course deviation bar centers VOR bearing pointer indicates 180 degrees TO FROM ambiguity indicator show a FROM indication O02 VHF NAV TRANSFER SWITCH e BOTH ON 1 switches the VHF navigation source to NAV VHF N
66. annel only occurs when e Autopilot roll channel power is lost e compass signal is lost or transferred PITCH ONLY Automatic disengagement of the pitch channel only occurs when e Autopilot pitch channel power is lost e The control wheel stabilizer trim switches are used e stabilizer trim autopilot cutout switch is positioned to CUTOUT AUTOPILOT REVERT TO MAN CONDITIONS The autopilot will revert to MANUAL if the following conditions exist e high detent CWS force applied while in VOR LOC AUTO APP or MAN G S modes after VOR or LOC on course loss of altitude input from the ADC while in AUTO APP or MAN G S 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 51 DO NOT USE FOR FLIGHT CONTROL WHEEL STEERING CWS The airplane may be maneuvered in pitch and roll after autopilot engagement using the control wheel and column Manual inputs by the pilots using CWS are the same as required for manual flight LOW DETENT LEVEL After autopilot engagement a low level manual input is required to move the control wheel out of the center detent position This input is comparable to the input required during manual flight HIGH DETENT LEVEL High detent level manual input is provided to prevent inadvertent disengagement of various submodes The input required to move the control wheel or column out of the detent position is increased If reversion to CWS inputs only no automatic heading
67. ations ground speed range fuel temperature reference speed trip altitude and wind Performance functions are displayed on the CDU only and cannot drive the airspeed or EPR bugs Most flight modes and performance functions have too much data available to be displayed at one time The data is therefore divided into separate displays called pages Each page of data is selected individually for display The mode annunciator indicates when a flight mode is engaged To allow the crew to look ahead in the flight a performance function or another flight mode may be selected for display on the CDU without disengaging the original mode Captain Sim www captainsim com 73 DO NOT USE FOR FLIGHT COMPUTER INPUTS Some inputs from other airplane systems are required for system operation and performance computations Temperature The PDCS receives a total air temperature input for use in temperature dependent computations Altitude and Airspeed Pressure altitude and airspeed are obtained from the Air Data Computer Fuel Weight The total weight of fuel aboard the airplane is provided by a fuel summation unit which receives inputs from each of the airplane s fuel tank transmitters Bleed Logic The PDCS receives switch position logic to adjust limit EPR for engine anti ice bleed wing anti ice bleed except when PDCS is in takeoff mode gravel protection on some airplanes and engine bleed air configurations EPR The existing EPR for each e
68. ative Light 3 4 Antiskid Control Switch 5 Auto Brake Select Switch ANTISKID 6 Auto Brake Disarm Light INBD OUTBD DN on 1 2 Antiskid Inoperative ANTISKID INOP Light 4 Illuminated amber a system fault is detected by antiskid monitoring system Extinguished antiskid system operating normally 3 4 ANTISKID Control Switch AUTO BRAKE ON guarded position 5 AUTO BRAKE Select Switch Used to select the level of desired braking The switch must be pulled out to select MAX deceleration 6 AUTO BRAKE DISARM Light Illuminated amber a malfunction exists in the automatic braking system P10 22 23 PARKING BRAKE 22 PARKING BRAKE Lever Forward parking brake is released Aft sets parking brakes when either Captain s or First Officer s brake pedals are fully depressed 23 Parking Brake Warning Light Illuminated red parking brake is set lights operate from battery power Extinguished parking brake is released R21 HYDRAULIC BRAKE PRESSURE INDICATOR Indicates system A and B brake system pressure normal pressure 3000 psi normal precharge 1000 psi 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 132 DO NOT USE FOR FLIGHT RUDDER BRAKE PEDALS 1 3 Rudder Brake Pedals Push full pedal turns nose wheel up to 7 degrees in either direction Push top of pedal only activates wheel brakes Refer to Chapter 9 F
69. bility to quickly identify significant weather follow these steps 1 Select the NORM mode of operation Adjust Brightness control as desired 2 Select the 50 or 150 nm range 3 Adjust the antenna tilt to watch the strongest returns seen on the display TARGET RESOLUTION The ability of a weather avoidance radar system to resolve and display two or more closely spaced targets is limited in range by the transmitted pulse width and display range and in azimuth by the antenna beam width RANGE RESOLUTION The transmitter pulse width in the radar is 4 micro seconds yielding a receiver range resolution of approximately 1 3 nautical mile AZIMUTH RESOLUTION The ability of the radar to resolve adjacent targets in azimuth is a function of the beam width of the antenna and the range to the target The diameter of this radiated beam increases as it gets further away from the aircraft Targets separated by a distance less than the beam diameter at the target distance will merge and appear on the indicator as one 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 119 DO NOT USE FOR FLIGHT PATH PLANNING Remember to plan a deviation path early Simply skirting the red or magenta portion of a cell is not enough Plan an avoidance path for all weather echoes which appear beyond 100 nautical miles since this indicates they are quite intense The most intense echoes are severe thunderstorms
70. c Displayed when traffic selected on the VSI or Weather Radar Indicator and W outlined position Relative altitude With traffic selected on the VSI or Weather Radar Indicator displays RA W relative traffic altitude in hundreds of feet Vertical motion Displayed when traffic vertical speed is greater than 500 feet per minute arrow RA W and traffic selected on the VSI or Weather Radar Indicator TOTAL AIR TEMPERATURE R02 TOTAL AIR TEMPERATURE INDICATOR Displays TAT from 70 degrees C to 50 degrees C Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 107 DO NOT USE FOR FLIGHT L20 R20 CLOCK Two spring powered eight day clocks are installed Each clock displays time in a 24 hour format and has a stop watch timer Sweep Second Hand Winding And Setting Control Hour Hand Minute Hand Push Control Ul WN P 1 Sweep Second Hand e controlled by push button e rotates once each minute 3 4 Hour and Minute Hands Twenty four hour format 5 PUSH Control Controls sweep hand With sweep second hand at zero 60 e Push starts sweep hand timing e Push again stops sweep hand timing e Push again resets sweep second hand to zero 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 108 DO NOT USE FOR FLIGHT STANDBY FLIGHT INSTRUMENTS C02 STANDBY HORIZON The standby horizon indicator provi
71. circuit The battery must be above minimum voltage to operate units supplied by this bus DC POWER SYSTEM SCHEMATIC 115v Ac MAIM GWE 2 115 AL GR UND SCRVICE DUS 115 Y Ac TRAHSEER BUS 115 V AC TRANSEER BUS 2j 3 DISCUMMLLT RELEF TY BATTERY EU BATTERY pmi NORMAL Dus d CONTROL GATT OFF AUTO P ETANDOY POWER SWITCH GFE OH e TO APU l firplane Configuration EETEBHAL rh 1 Pl Le r Battery Switch QN 5 Standby Power Switch AUTO Bus Transfer Switch AUTO IHE Genermtar Buzzez POWERED STANDBY POWER SYSTEM NORMAL OPERATION The standby system is used to supply power to essential AC and DC systems During normal operation the guarded standby power switch is in AUTO and the battery switch is ON Under normal conditions the AC standby bus is energized from the 115 V AC transfer bus no 1 and the DC standby bus is energized from DC bus no 1 N CU et CU 5 2 C www captainsim com 7 2 MANUAL Part II Aircraft Systems 65 DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS ELECTRICAL PANEL AC AND DC METERING PANEL GENERATOR DRIVE AND STANDBY POWER PANEL GROUND POWER AND GEN AMMETERS PANEL BUS SWITCHING PANEL 2012 Captain Sim www captainsim com J O N 737 Captain FLIGHT MANUAL Part II Aircra
72. course radio or pitch commands is desired this may be accomplished by exerting an input greater than high detent level CWS OPERATION CWS operates in low or high detent level depending on which modes or submodes are active MAN Mode CWS pitch and roll are low detent unless various submodes are active see below VOR LOC Mode CWS pitch and roll are low detent until VOR or localizer ON COURSE CWS roll then becomes high detent and CWS pitch remains low detent unless ALT HOLD is active CWS roll may be used to override during the capture phase until ON COURSE Exceeding high detent in roll reverts the autopilot to MAN AUTO APP or MAN G S Modes Same as VOR LOC mode until G S engaged Pitch and roll CWS are then high detent Exceeding high detent reverts the autopilot to MAN ALT HOLD Submode CWS pitch is high detent Exceeding high detent will revert the Pitch Mode Selector Switch to OFF HOLD HDG OFF Submodes CWS roll is low detent HDG SEL Submode CWS roll is high detent Exceeding high detent causes the heading switch to move to the center HEADING HOLD position FLIGHT DIRECTOR The flight director computers receive constant inputs from various airplane systems Loss of one of these inputs will adversely affect the flight director The command bars are dependent upon the position of the Flight Director Mode Selector Altitude Hold Switch and Pitch Command Control The following is a condensed description of th
73. de energizes blocking valve in pump to allow pump pressure to enter system Note Should remain ON at shutdown to prolong solenoid life OFF energizes blocking valve to block pump output 10 11 Electric Hydraulic Pump Switches ON provides power to corresponding electric motor driven pump OFF electrical power removed from pump 12 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 127 DO NOT USE FOR FLIGHT R22 R23 R25 HYDRAULIC INDICATIONS R22 Hydraulic System Pressure Indications Indicates system A and B pressures e Normal pressure 3000 psi e Maximum pressure 3500 psi Note When both pumps for a system are OFF respective pointer reads zero R23 System A Hydraulic quantity Indicator e Full 3 5 U S gallons e Refill 2 4 U S gallons Hydraulic System B LOW QUANTITY Light 1 4 HYD QTY us GAL Illuminated amber indicates reservoir fluid level is low B LOW QUANTITY 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 128 DO NOT USE FOR FLIGHT LANDING GEAR SYSTEM DESCRIPTION The airplane has two main landing gear and a single nose gear Each main gear is a conventional two wheel landing gear The nose gear is a conventional steerable two wheel unit Hydraulic power for retraction extension and nose wheel steering is normally supplied by hydraulic system A Normally brakes
74. des and performance functions with multiple pages e After the last page is reached the system cycles back to the first page 737 Captain FLIGHT MANUAL Part II Aircraft Systems 80 DO NOT USE FOR FLIGHT PDCS DISPLAYS TYPICAL Page Title Target Airspeed Target Mach Wind Component No 1 Engine Target Limit EPR Indicating Arrow Page 1 of 4 No 2 Engine Target Limit EPR Q NO 4 Wind Component Unless a wind is entered the component reads zero 6 Indicating Arrow IN VIEW e Optimum altitude is still more than 2000 feet above or below if down arrow is showing e Arrow disappears when within 2000 feet of optimum altitude Performance Function Distance Nautical Miles Reserve c Alternate Fuel Over Distance Wind Component Total Fuel Quantity Remaining Page Title Page 1 Of 4 FUEL ECON 1 DIST NM 700 RSVtALT 9 9 FOD 10 4 WIND FUEL WT l OA Ui N PERFORMANCE FUNCTION FUEL 2 DIST NM Distance Nautical Miles Distance to go as entered May be to a checkpoint or over destination 3 RSV ALT Reserve Alternate Reserve and alternate fuel quantity LBS X 1000 4 FOD Fuel over distance Fuel remaining over destination or waypoint at the CRZ ECON speed for the present altitude and entered distance to go LBS X 1000 5 Wind Component Wind component entered into computer based on 10 kts headwind 20
75. des attitude information that is independent of the primary attitude displays The indicator is powered by the battery bus and remains powered after the loss of all normal AC power as long as battery power is available 1 1 Bank Angle Scale 2 Bank Angle Indicator 3 Horizon Drum 4 Symbolic Airplane 5 Warning Flag 6 6 Horizon Bar 7 Pitch Trim and Gyro Caging Control 8 Pitch Trim Scale 1 Bank Angle Scale Measures bank angles up to 60 in 10 increments freedom of roll 3609 2 Bank Angle Indicator Indicates airplane bank angle against bank angle scale 3 Horizon Drum Provides indication of airplane pitch attitude freedom of pitch 905 4 Symbolic Airplane Provides an adjustable attitude reference 5 Warning Flag In view loss of power 7 Pitch Trim and Gyro Caging Control In rotate to adjust symbolic airplane pitch presentation Pull momentary provides fast erection caging of gyro Release control retracts Note Airplane should be level during procedure 8 Pitch Trim Scale Provides a reference for adjusting the symbolic airplane pitch presentation Marked in 1 degree increments e C climb D dive 2012 Captain Sim www captainsim com GHT MANUAL Part II Nircraft Systems 109 DO NOT USE FOR FLIGHT O31 STANDBY MAGNETIC COMPASS A standard liquid damped magnetic standby compass is provided A card located near the compass provides heading correction factors
76. e altitude is below 10 000 feet e flag appears in the two left hand windows when altitude below zero feet is displayed 2 Altitude Pointer Makes one revolution each one thousand feet 3 Barometric BARO Setting Control Rotate adjusts barometric settings 4 Barometric Setting Window Displays barometric correction in millibars and inches of mercury as set by the barometric setting control R24 PNEUMATIC ALTIMETER A pneumatic altimeter is installed on the first officer s instrument panel It utilizes the first officer s pitot static source 1 Barometric Setting Window 2 Altitude Pointer 3 Barometric Setting Control 4 Digital Altitude Counter 1 Barometric Setting Window Displays barometric correction in millibars of mercury as set by the barometric setting control 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 101 DO NOT USE FOR FLIGHT 2 Altitude Pointer Makes one revolution each one thousand feet 3 Barometric Setting Control Rotate adjusts barometric settings MARKER BEACON Each pilot has a set of marker beacon lights that show airways middle and outer beacon passage Both sets are operated by one marker beacon receiver L17 R17 MARKER BEACON LIGHTS AIRWAYS 1 3 Marker Beacon Lights AIRWAYS white illuminates over an inner or airways marker beacon MIDDLE amber illuminates over a middle marker
77. e inputs to the computers and the commands to the indicator Air data computer a pitch command to hold altitude if the Altitude Hold Switch is ON Radio altimeter and marker beacon receiver at 1500 feet gain for pitch commands to maintain glide slope is reduced Gain is further reduced at 200 feet or the middle marker whichever is first N 2012 Captain Sim www captainsim com 52 DO NOT USE FOR FLIGHT GA Go Around a pitch up command and a wings level roll command Vertical gyro pitch and roll commands for stabilization of the indicator Navigation unit pitch and roll signals for capturing and tracking VOR radials localizer courses and glide slope beams Preset course roll commands to remain on selected course Preset heading roll commands to remain on selected heading FLIGHT DIRECTOR SCHEMATIC AIR DATA COMPUTER RADIO ALTIMETER MARKER RECEIVER GA THRUST VERTICAL GYRO DIRECTOR RAW UNIT PRESET COURSE PRESET HEADING FLIGHT COMPUTER 737 Captain FLIGHT MANUAL Part II Aircraft Systems 53 DO NOT USE FOR FLIGHT ALTITUDE ALERT SYSTEM The altitude alert system provides visual and aural reminders when approaching a pre selected altitude The system uses the Captain s altimeter to compare actual altitude to the alerting altitude set in the Altitude Alert Controller ACQUISITION MODE When approaching the selected altitude a two second tone sounds and the ALTITUDE ALERT lig
78. ed direction RUDDER RUDDER PEDALS 1 2 Rudder Brake Pedals Push e controls rudder position e permits limited nose gear steering up to 7 degrees each side of center 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 88 DO NOT USE FOR FLIGHT P16 RUDDER AILERON TRIM WHEELS 4 Rudder Trim Wheel Rotate repositions the rudder neutral control position 6 AILERON TRIM Wheel Rotate repositions the aileron neutral control position AILERON ELEVATOR FLIGHT SPOILERS W01 W02 CONTROL WHEEL 4 Control Wheel Rotate operates ailerons and flight spoilers in desired direction 5 Control Column Push Pull operates elevators in the desired direction Movement opposing stabilizer trim stops electric trimming 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 89 DO NOT USE FOR FLIGHT SPEED BRAKES P10 SPEED BRAKE LEVER 18 Speed Brake Lever DOWN detent all flight and ground spoiler panels in faired position ARMED INFLIGHT ONLY e automatic speed brake system armed upon touchdown the SPEED BRAKE lever moves to the UP position and all flight and ground spoilers extend throttle movement or key will retract the spoiles FLIGHT DETENT all flight spoilers are extended to their maximum position for inflight use UP all flight and ground spoilers are extended to the
79. ed will then be faster thus reducing flying time at the expense of fuel The flight index is programmed into the computer by the airline but may be changed for any flight if desired from the CDU keyboard Engaging the Output Whenever the display can be engaged the engage key is illuminated Pressing the key causes the ENGAGE light to extinguish and the EPR bugs to drive to the displayed values Engaging any PDC mode causes the EPR bugs to drive to the displayed values The PDC drives the airspeed cursors only when PDC SPEED is selected Automatic Page Selection Whenever a page of flight mode data has been engaged pressing one of the performance function keys causes the PDCS to compute and display the data for the corresponding page of the performance function For example if CRZ LRC has been engaged and the RNG key is pressed the display immediately shows RNG LRC Display of Speeds When a Mach airspeed schedule is displayed on the manual page of the CDU the controlling value is underlined For example if climbing at a speed schedule of 320 72 at low altitudes the 320 is underlined and at high altitudes the 72 underlined 737 Captain FLIGHT MANUAL Part II Aircraft Systems 74 DO NOT USE FOR FLIGHT When accelerating Mach numbers less than 65 are not displayed when decelerating Mach numbers are not displayed after the speed falls below Mach 60 SYSTEMS SAFEGUARDS The PDCS has been integrated into the airplane in such a wa
80. ered by a warning flag when the display is unreliable 10 Airspeed Digital Counter e digital display of indicated airspeed in knots e warning flag covers the counter when the airspeed pointer and airspeed digital counter are unreliable DO NOT USE FOR FLIGHT R13 PNEUMATIC MACH AIRSPEED INDICATOR 1 Mach Airspeed Pointer Indicates Mach and airspeed in knots 2 Airspeed Cursor Control Rotate manually positions the airspeed cursor 3 MACH Dial Rotates Mach number read under Mach Airspeed pointer 4 Airspeed Reference Markers Bugs Positioned manually to the desired airspeed reference 5 Airspeed Cursor 99 1 Mach Airspeed Pointer 2 Airspeed Cursor Control 3 Mach Dial 4 Airspeed Reference Markers Bugs 5 Airspeed Cursor Indicates target airspeed positioned manually by the airspeed cursor control 737 Captain FLIGHT MANUAL Part II Aircraft Systems 100 DO NOT USE FOR FLIGHT ALTIMETER L13 ELECTRIC ALTIMETER An electric altimeter is installed on the captain s instrument panel Altitude is derived from the air data computer 1 Digital Altitude Counter 2 Altitude Pointer 3 Barometric Setting Control 4 Barometric Setting Window 1 Digital Altitude Counter Indicates current altitude in increments of thousands hundreds and twenty feet e warning flag appears whenever the ADC signal is lost or a malfunction exists e blue flag appears in the left window when th
81. ft Systems 66 DO NOT USE FOR FLIGHT O07 AC AND DC METERING PANEL DC Ammeter DC Voltmeter DC Meter Selector Battery Switch AC Frequency Meter AC Voltmeter AC Meter Selector Galley Power Switch Residual Volts Switch N 1 DC Ammeter Indicates current of source selected by DC meter selector 2 DC Voltmeter Indicates voltage of source selected by DC meter selector 3 DC Meter Selector Selects the DC source for the DC voltmeter and DC ammeter indications TEST used by maintenance 4 Battery BAT Switch OFF e removes power from the battery bus ON guarded position e provides power to the battery bus from TR3 when main bus No 2 is energized e provides power to the battery bus from the hot battery bus when main bus No 2 is not energized 5 AC Frequency Meter Indicates frequency of source selected by AC meter selector 6 AC Voltmeter 130 V scale indicates voltage of source selected on the AC meter selector 30V scale indicates residual voltage of generator selected when RESID VOLTS switch is pressed 7 AC Meter Selector Selects the AC source for the AC frequency meter and AC voltmeter TEST used by maintenance 8 GALLEY Power Switch OFF removes electrical power from galleys ON electrical power is supplied to galleys when both AC generator busses are powered 9 Residual Volts RESID VOLTS Switch PRESS 30V scale of AC voltmete
82. ght pack are mixed in a common manifold The mixed air is then distributed by the sidewall risers to the passenger cabin PRESSURIZATION SYSTEM DESCRIPTION Cabin pressurization is controlled during all phases of airplane operation by the cabin pressure control system CPCS The CPCS includes one automatic controller and one standby controller available by selecting AUTO or STBY and two manual MAN pilot controlled modes The system uses bleed air supplied to and distributed by the air conditioning system Pressurization and ventilation are controlled by modulating the outflow valves 737 Captain FLIGHT MANUAL Part II Aircraft Systems 37 DO NOT USE FOR FLIGHT FLIGHT PATH EVENTS AUTO MODE WHEN AIRCRAFT HOLDS 1 d ISOBARIC PROPORTIONAL ISOBARIU MAX P VET PROPORTIONAL CONTROL CONTROL CONTROL CONTROL CONSTANT FLT ALT SETTING I I p DESCENT RELAY MIN CRUISE RELAY TRIPS TP TRIP I I l l I LAND RNU i I amp I SET ERD CTAXIING CLIMB CRUISE OFF ALTITUDE DESCENT IN CABIN ALTITUDE WS AIRPLANE ALTITUDE The controller senses only pzi Feferences to altitudes sre spnroximstionsz end wary according ta density altitude As the density of the mir decresses the greater the change in altitude for a given psi 2012 Captain Sim www captainsim com JAL Part II Aircraft Systems 38 DO NOT USE FOR FLI
83. ghts are installed on the fuselage and illuminate the leading edge of the wing WHEEL WELL LIGHTS Lights are installed in the wheel well of the nose gear and each main gear 737 Captain FLIGHT MANUAL Part II Aircraft Systems 23 DO NOT USE FOR FLIGHT EXTERIOR LIGHTING LOCATIONS TAXI LIGHT white LEFT AND RIGHT RUNWAY TURNOFF LIGHTS white WING ILLUMINATION LIGHTS white LEFT AND RIGHT INBOARD LANDING LIGHTS white LEFT AND RIGHT OUTBOARDL AND ING LIGHTS white UPPER AND LOWER ANTI COLLISION LIGHT red ztrobe Light LEFT AND RIGHT NAVIGATION LIGHTS red and white Left green and white right FLIGHT DECK LIGHTING White dome lights provide general flight deck flood lighting The Captain s and First Officer s instruments are illuminated by white flood lights under the light shield and by integral white lights in the panels Overhead map and circuit breaker panel lights and standby magnetic compass controls compass are controlled by individual switches CONTROLS AND INDICATORS S01 LIGHT CONTROLS 1 Map Light Control 2 Map Light Switch PANEL AND BACKGROUND LIGHTING 09 LIGHTS CONTROL PANEL 1 Captain and Center panels instruments backlight Control 2 Shift L Light Control Aux 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 24 DO NOT USE FOR FLIGHT RO9 PANEL LIGHT CONTROL 1 First
84. has two passenger entry doors one cabin door the flight deck passenger cabin entry and two cargo doors It also has one center electrical and electronic E E equipment access door on the bottom of the airplane The flight deck number two windows one on the left and one on the right can be opened by the flight crew 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT 28 FLIGHT DECK NUMBER TWO WINDOWS The flight deck number two windows can be opened on the ground or in flight and can be used for emergency evacuation To open the window turn the handle back and inboard After the window moves inboard move it back until it locks in the open position To close the window move the window forward until the handle can be turned forward and outboard HANDLE WITH TRIGGER LATCH MECHANISM CLOTHES GUARD FLIGHT COMPARTMENT WINDOW NO 2 RIGHT SIDE SHOWN PILOT SEAT ADJUSTMENT Adjust the seat position with the appropriate controls to obtain the optimum eye reference position Use the handhold above the forward window to assist The correct eye reference position is established when e The topmost flight mode annunciators or approach progress displays are just in view below the glareshield A slight amount of the aircraft nose structure is visible above the forward lower window sill EYE REFERENCE POSITION e FLIGHT MODE A ANNUNCIATOR OR APPROACH PROGRESS DISPL
85. hts illuminate 1000 feet above or below the selected altitude The lights extinguish 375 feet above or below the selected altitude ALTITUDE ALERT SYSTEM CAPTAIN S ALTIMETER ALTITUDE ALERT CONTROLLER J ALTITUDE ALERT AUTOPILOT CONTROLS T01 GO AROUND SWITCH 1 2 Go Around Switch Armed with flight director Mode Selector in the AUTO APP or MAN GS positions PRESS either or both switches Provides flight director commands for wings level with a pitch up of 14 degrees 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 54 DO NOT USE FOR FLIGHT W01 W02 CONTROL WHEEL 1 Autopilot Disengage Switch e Disengages the autopilot e A P disengage light illuminates e Resets the Autopilot Disengage Light after automatic disengagement Note Each time the autopilot is disengaged the pilot should guard the controls for an undetected out of trim condition AUTOPILOT INDICATORS L16 GPS NAV SWITCH 1 GPS NAV Switch GPS NAV switch to select an additional FSX flight plan tracking autopilot Nav 1 GPS toggle should be assigned via FSX Menu Controls Assignments L10 R10 AUTOPILOT DISENGAGE LIGHT RED AUTO PRESS Resets the Autopilot Disengage Light after automatic disengagement PILOT ILLUMINATED FLASHING The autopilot is automatically disengaged e The light is pressed to test e Autopilot Disengage
86. ic Mach Airspeed indicator displays information derived from the air data computer The pneumatic Mach Airspeed indicators derives information from the respective captain s or first officer s pitot static system 02 ELECTRIC MACH AIRSPEED INDICATOR PJ 4 Airspeed Pointer 5 Airspeed Cursor Control y I m s 6 1 Airspeed Cursor Mode Annunciator 1 aW B In 2 Vmo Pointer FI 3 Vmo Flag 100 D Dok 1 L qm 6 Airspeed Cursor 285 297 7 Airspeed Reference Markers Bugs 2 ih gt 42 8 Mach Digital Counter Ur NDS 9 Airspeed Cursor Flag OR 10 Airspeed Digital Counter 1 Airspeed Cursor Mode Annunciator Manual mode in view 2 Vmo Pointer Indicates the maximum operating indicated airspeed in knots 2012 Captain Sim www captainsim com 98 DO NOT USE FOR FLIGHT 3 Vmo Flag In view indicates the Vmo pointer is inoperative 4 Airspeed Pointer Indicates airspeed in knots 5 Airspeed Cursor Control Airspeed cursor is positioned by rotating the control 6 Airspeed Cursor Indicates target airspeed positioned manually as selected by the airspeed cursor control 7 Airspeed Reference Markers Bugs Positioned manually to the desired airspeed reference 8 MACH Digital Counter e shows Mach number from 40 to 99 Mach in digital form e masked below 40 Mach e digits are cov
87. if force is being exerted on the control column 8 Autopilot Pitch Mode Selector ALT HOLD Altitude Hold Pitch reference is to pressure altitude TURB Turbulence INOP 737 Captain FLIGHT MANUAL Part II Aircraft Systems 37 DO NOT USE FOR FLIGHT L12 R12 APPROACH PROGRESS DISPLAY 1 2 Photoelectric Cells 3 4 VOR LOC 5 6 Glide Slope Sait GLIDE GLIDE 1 2 Photoelectric Cells e Overridden by positioning the Master Lights Test Switch to BRT E LL wv AMBER Radio mode selected e Prior to VOR or localizer capture GREEN Radio mode selected e Capture initiated 5 6 GLIDE SLOPE AMBER AUTO APP selected Prior to glide slope capture GREEN AUTO APP selected and glide slope captured 9 GO AROUND GREEN Captured G02 G04 FLIGHT DIRECTOR 1 Mode Selector Em 2 Altitude Hold Switch 3 Pitch Command Control X MEDE TEL 1 Mode Selector MODE SEL Rotate selects flight director computer reference signals provided to command bars GA Go Around e GAlight illuminated green e command bars provide commands for wings level and a pitch attitude of 14 degrees until the Mode Selector is changed to another position e mode Selector in AUTO APP or MAN GS go around is initiated by pushing the Go Around switches on the thrust levers e manual selection to GA can be initiated anytime by positioning the Mode Selector to GA OFF removes command bars HDG command
88. in FLIGHT MANUAL Part II Aircraft Systems 71 DO NOT USE FOR FLIGHT OIL SYSTEM Oil from the individual engine tank is circulated under pressure through the engine to lubricate the engine bearings and accessory gearbox Oil quantity is displayed on the oil quantity indicator located on the center instrument panel ENGINE START SYSTEM Low pressure air a pneumatic starter and electrical power are required for starter operation The engines may be started with air from the APU from a ground source or by using engine crossbleed Engine bleed air valves must be open to allow air from any source to reach the selected engine starter ENGINE IGNITION SYSTEM 4 POSITION START SWITCH Two systems are provided A high energy system is energized with the engine start switch in either the GRD or FLT position when the engine start lever is placed to the IDLE position The high energy system furnishes pulsating power to plugs in both No 4 and No 7 burner cans The high energy system is used for all engine starts THRUST REVERSER Reverse thrust is accomplished by two doors which block engine exhaust and deflect the exhaust flow forward The doors operate by system A hydraulic pressure through the gear down hydraulic line Alternate operation at a reduced rate is available with the standby hydraulic system the reverser may not stow A REVERSER UNLOCKED light located on the center instrument panel will illuminate when either thrust reverse door is
89. in the model it is not a system bug but a reasonable simplification 3D CONTROLS ANIMATION SWITCHES BUTTONS KNOBS LAMPS 1 Two positions left click 2 Multi position Counterclockwise decrease left click or mouse wheel outwards oneself Clockwise increase right click or mouse wheel towards oneself 3 Three position with middle spring back position Down left left click Up right right click 4 Levers and some wheels like trim and pitch trim wheels Decrease left click drag Increase right click drag DO NOT USE FOR FLIGHT AIRPLANE GENERAL marta 5 23M 37 P gt er 11 23M a1 Oo xt 13 ae 37 A 5 96 11 37M ggg ge 29 5zM 1 gt Cardo airplanets only 737 Captain FLIGHT MANUAL Part II Aircraft Systems 11 DO NOT USE FOR FLIGHT INSTRUMENT PANELS PANEL ARRANGEMENT AFT OVERHEAD PANEL SPEAKER Q La ESCAPE STRAP FORWARD Wr STOWAGE OVERHEAD QU 5 P ANEL MAP LIGHT STANDBY LIGHTSHIELD MAGNETIC CAPTAIN INSTRUMENT PANEL CENTER INSTRUMENT P ANEL FORWARD ELECTRONIC FIRST PANEL OFFICER INSTRUMENT FANEL AFT ae ELECTRONIC AND PANEL AUTOPILOT DISENGAGE SWITCH STABILIZER TRIM SWITCH aes MEMORY DEVICE WRITING PAD HOLDER CLIP WITH CHECKLIST PUSH TO TAL
90. in transit or valve position and fuel HEAT switch disagree e dim fuel heat valve is open Extinguished fuel heat valve is closed 5 Crossfeed VALVE OPEN Light Illuminated blue e bright crossfeed valve is in transit or valve position and CROSSFEED selector disagree e dim crossfeed valve is open Extinguished crossfeed valve is closed 6 23 Fuel HEAT Switch ON The solenoid switch opens the respective engine fuel heat valve allowing bleed air to heat the fuel and de ice the fuel filter The switch automatically moves to OFF after one minute 7 CROSSFEED Selector Controls fuel crossfeed valve Closed isolates engine No 1 and No 2 fuel feed lines Open connects engine No 1 and No 2 fuel feed lines gt 3 737 Captain FLIGHT MANUAL Part II Aircraft Systems 123 DO NOT USE FOR FLIGHT 8 9 Center Tank Fuel Pump LOW PRESSURE Light Illuminated amber fuel pump output pressure is low and FUEL PUMP switch is ON Note With both Center CTR tank FUEL PUMP switches ON illumination of both LOW PRESSURE lights illuminates MASTER CAUTION and FUEL system annunciator lights Illumination of one LOW PRESSURE light illuminates MASTER CAUTION and FUEL system annunciator lights on MASTER CAUTION light recall Note With one CTR tank FUEL PUMP switch OFF illumination of opposite CTR tank LOW PRESSURE light illuminates the MASTER CAUTION and FUEL system annunciator lights Extinguished fuel pump output pressure
91. indicators display vertical speed derived from the respective pilots static system or alternate static if selected On some airplanes vertical speed information is displayed by two electric vertical speed indicators that receive information derived from their respective air data computer On some airplanes a TCAS VSI display shows air traffic information detected by the TCAS system 1 Light Sensor 2 TA Select Push button 3 Brightness Control 4 Vertical Speed Pointer 1 Light Sensor Automatically adjusts display contrast for ambient light conditions 2 TA Select Push button Push changes display between modes e full time mode traffic information is displayed full time e popup mode traffic information is displayed only when a or RA is generated Display remains for the duration of the alert 3 Brightness Control Rotate adjusts brightness of the VSI display 4 Vertical Speed Pointer Displays rate of climb or descent from 0 to 6 000 feet per minute 012 Captain Sim www captainsim com C J N 737 Captain FLIGHT MANUAL Part II Aircraft Systems 104 DO NOT USE FOR FLIGHT TCAS TCAS RESOLUTION ADVISORY COMMANDS 1 RA Pitch Command green UP Advisory Indicates vertical speed range to ensure traffic separation 2 Command Arc red Indicates vertical speed range to avoid 3 RA Pitch Command green DOWN Advisory Indicates vertical speed range to ensure traffic separation
92. ir maximum position for ground use CO5 SPEED BRAKE LIGHTS 1 Speed Brake Do Not Arm Light 2 Speed Brake Armed Light SPEED BRAKE DO MOT ARM SPEED BRAKE P ARMED 1 SPEED BRAKE DO NOT ARM Light Light deactivated when SPEED BRAKE lever is in the DOWN position Illuminated amber indicates abnormal condition or test inputs to the automatic speed brake system 2 SPEED BRAKE ARMED Light Light deactivated when SPEED BRAKE lever is in the DOWN position 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 90 DO NOT USE FOR FLIGHT 608 SPEED BRAKE TEST SWITCHES 1 3 Speed Brake Test Switches SPEED BRAKE TEST W 2 Tests fault detection circuits of the automatic speed brake system C12 FLAP POSITION INDICATOR Used for maintenance purposes only TRAILING EDGE FLAPS Indicates position of left and right trailing edge flaps provides trailing edge flaps asymmetry protection circuit C04 FLAPS LIMIT PLACARD Indicates maximum speed for each flap setting FLAPS LIMIT CIAS 1 250 15 195K 2e 30K 25 190K a 225K 30 1856 1 210K 40 170K 210K ALT FLAP EXT 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 91 DO NOT USE FOR FLIGHT P10 FLAP LEVER FLAP GATES 19 Flap Lever Selects position of flap control valve directing hydraulic pressure for flap drive unit positi
93. l left position when no AC power is available 11 Cabin Altitude CAB ALT Indicator e Indicates selected cabin altitude e Set before takeoff 12 Outflow Valve Switch spring loaded to center CLOSE closes main cabin outflow valve electrically with pressurization mode selector in MAN position OPEN opens main cabin outflow valve electrically with pressurization mode selector in MAN position 13 Cabin Altitude Selector Rotate to select desired cabin altitude e large diameter control sets 1000 foot increments and negative elevations e small diameter control sets 10 foot increments 14 Flight Ground Switch AUTO mode e GND on the ground drives the pressurization outflow valve full open at a controlled rate and depressurizes the airplane After takeoff inhibited functions the same as FLT position e FLT on the ground pressurizes the cabin to approximately 200ft below airport elevation After takeoff cabin pressure is automatically controlled in climb and descent as a function of airplane altitude In cruise cabin pressure is held constant STANDBY mode e GND on the ground drives the main outflow valve full open After takeoff inhibited functions the same as FLT position e FLT pressurizes the airplane by driving the main outflow valve to attempt to pressurize the cabin to the selected CAB ALT normally set 200ft below takeoff field elevation 15 Pressurization Mode Selector AUTO pressurization
94. l locks and airplane cabin pressure The hatches can be opened from the inside or from outside of the airplane by a spring loaded handle at the top of the hatch A seat back blocking an exit may be pushed forward by applying force to the top of the seat back For safety reasons hatches should not be removed in flight EXTERIOR PLACARD EMERGENCY EXIT HATCHES PUSH PANEL PRESS TO UNLATCH TO OPEN HATCH PUSH HATCH INWARD AND LIFT UP 1 Push in panel 2 Push hatch inward and Lift up EMERGENCY EXIT INTERIOR HANDLE TO OPEN HATCH 1 Pull down and inward HANDHOLD To operate the OVERWING ESCAPE HATCHES use Animation Control Panel WARNING Do not remove hatches in flight in preparation for passenger evacuation For emergency evacuation on the ground or in water remove hatch and place so as not to obstruct egress The hatch may be thrown out onto the wing GALLEYS Galleys are located in the passenger cabin to provide convenient and rapid service to the passengers Generally they are installed in the cabin adjacent to the forward and aft galley service doors In general the equipment of the galley unit consists of the following main items e High speed ovens e Hot beverage containers e Hot cup receptacles e Refrigeration and main storage compartments 2012 Captain Sim www captainsim com 33 DO NOT USE FOR FLIGHT AIRSTAIRS The forward airstair provides the capability of boarding passengers without relying on the a
95. l monitors slip or skid for coordinated flight 8 Flight Director Command Bars yellow Displays computed pitch and or roll commands Biased out of view e flight director switch is positioned OFF e the required signal inputs are unreliable 9 Symbolic Airplane orange Represents airplane attitude relative to the horizon 10 Flight Director COMPUTER Warning Flag In view e vertical gyro information unreliable e electrical power loss e causes flight director command bars to retract 11 Localizer Symbol and Deviation Scale In view e localizer frequency is tuned and localizer signal is valid e scale indicates localizer deviations of one dot or less one dot is one degree displacement 737 Captain FLIGHT MANUAL Part II Aircraft Systems 96 DO NOT USE FOR FLIGHT L07 R07 HORIZONTAL SITUATION INDICATOR 1 DME Miles Window 2 Lubber Line 3 Glideslope Pointer and Scale 4 Airplane Symbol 5 HSI Heading Selector 6 Course Pointer and Course Counter 7 To From Ambiguity Indicator 8 Heading Marker 9 Course Deviation Bar 10 HSI Cource Selector 1 DME MILES Window Inoperative 2 Lubber Line Displays heading on compass card 3 Glideslope Pointer and Scale Indicates displacement above or below glideslope Pointer in view localizer frequency tuned and HSI powered 4 Airplane Symbol e fixed in the center of the instrument e displays position of the airplane in relation to movable portion
96. light Controls for rudder description 2 Rudder Pedal Adjustment Crank AFT counter clockwise adjusts rudder pedals aft FWD clockwise adjusts rudder pedals forward NOSE WHEEL STEERING WHEEL 1 Nose Wheel Steering Wheel Rotate turns nose wheel up to 78 degrees in either direction overrides rudder pedal steering 2 Nose Wheel Steering Indicator LEFT indicates nose wheel steering displacement left of center position CENTER normal straight ahead position RIGHT indicates nose wheel steering displacement right of center position O23 ANNUNCIATOR LIGHTS 1 Tire Screen Light Illuminated amber indication that the tire screens are not secure 2012 Captain Sim www captainsim com 133 DO NOT USE FOR FLIGHT WARNING SYSTEMS SYSTEM DESCRIPTION Aural tactile and visual warning signals alert the flight crew to conditions requiring action or caution in the operation of the airplane The character of the signals varies depending upon the degree of urgency or types of hazards involved Aural tactile and visual signals are used singularly or in combination to simultaneously provide both warnings and information regarding the nature of the condition Mach airspeed warnings landing gear warnings takeoff configuration warnings windshear warnings and ground proximity warnings are discussed in this section Cabin altitude warning is discussed in this section and in the Air Systems chapter
97. lluminated 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 26 DO NOT USE FOR FLIGHT O29 MISCELLANEOUS EXTERIOR LIGHTS 1 Position Light Switch 2 Anti Collision Light Switch 3 Wing Illumination Switch 4 Wheel Well Light Switch WHEEL WELL ANTI POSTERS COLLISION WING on BAT on arr 1 POSITION Light Switch ON BAT illuminates the red and green wingtip position lights the white trailing edge wingtip lights from the battery bus if no other power is available Battery Switch must be positioned to ON OFF position lights extinguished ON illuminates the red and green wingtip position lights and the white trailing edge wingtip lights 2 ANTI COLLISION Light Switch OFF red high intensity strobe lights extinguished ON red high intensity strobe lights on upper and lower fuselage illuminated 3 WING Illumination Switch OFF wing leading edge lights extinguished ON wing leading edge lights on fuselage forward of wing illuminated 4 WHEEL WELL Light Switch OFF three wheel well lights extinguished ON wheel well lights illuminated for checking landing gear down and locked stripes 2012 Captain Sim www captainsim com 27 DO NOT USE FOR FLIGHT DOORS AND WINDOWS SYSTEM DESCRIPTION FWD FWD SERVICE CARGO CARGO SERVICE FWD MAIN EH s_ AIR STAIR EQUIF ENTRY EAs installed The airplane
98. n conjunction with these modes the following submodes are available e CONTROL WHEEL STEERING HEADING OFF HEADING HOLD HEADING SELECT ALTITUDE HOLD AUTOPILOT SYSTEM AUTOPILOT HEADING SWITCH The autopilot heading switch may be used to operate the autopilot in HEADING OFF HEADING HOLD or HEADING SELECT This switch is spring loaded to the center HEADING HOLD position HEADING SELECT may be used in any mode until VOR LOC capture when it trips to the center position automatically When in HEADING SELECT the autopilot uses the Captain s heading marker for reference The autopilot roll channel is in CWS high detent If high detent force is exceeded the heading switch trips to HEADING HOLD Pitch mode such as ALT HOLD may be used independently of the heading mode Bank angles for all modes are limited to 32 degrees AUTOPILOT PITCH MODE SELECTOR The autopilot pitch mode selector is used for altitude hold ALT HOLD mode selection The Altitude Hold mode causes the autopilot to level at the altitude at which the autopilot mode selector is positioned to ALT HOLD APPROACH PROGRESS DISPLAY The approach progress display provides annunciation of autopilot status while in VOR LOC AUTO APP and MAN G S VOR LOC Mode The VOR LOC light Illuminates amber immediately after mode selection Illuminates green when capture occurs 2 5 dot in VOR and 2 dots in LOC The GLIDE SLOPE light is inoperative in the VOR LOC mode AUTO AP
99. ne maximum certified altitude The APU supplies bleed air for one air conditioning pack either on the ground or in flight Both generator busses can be powered on the ground In flight only one generator bus can be powered ELECTRICAL REQUIREMENTS FOR APU OPERATION APU operation requires the following e APU fire switch on the overheat fire panel must be IN e APU fire control handle on the APU ground control panel must be IN e Battery switch must be ON Electrical power to start the APU comes from the airplane battery Moving the battery switch to OFF on the ground shuts down the APU 2 Captain Sim www captainsim com DO NOT USE FOR FLIGHT APU START The automatic start sequence begins by moving the APU switch momentarily to START This initiates opening of the air inlet door When the APU inlet door reaches the full open position the start sequence begins After the APU reaches the proper speed ignition and fuel are provided When the APU is ready to accept a bleed air or electrical load the APU GEN OFF BUS light illuminates Operate the APU for one full minute before using it as a bleed air source This one minute stabilization is recommended to extend the service life of the APU APU SHUTDOWN Operate the APU for one full minute with no bleed air load prior to shutdown This cooling period is recommended to extend the turbine wheel life of the APU Moving the APU switch to OFF shuts down the APU trips the APU generator and closes
100. ngine is furnished to the PDCS for use in computing actual airplane performance Distance The system also uses distance information from the airplane s DME This data is used for automatic computation of wind and airplane ground speed COMPUTER OUTPUTS Speed Schedules For climb cruise and descent the PDCS provides a variety of speed schedules enabling the crew to select that schedule which is best suited to their requirements For climb there is a choice of ECON minimum cost RATE maximum rate of climb or MANUAL the crew manually enters a desired speed ECON is always the first page of data For cruise the crew can select either ECON LRC or MANUAL The LRC mode differs from economy Cruise in that LRC computes speed for 99 best range where economy cruise computes speed for minimum trip cost There is also the TURB turbulence speed schedule available in cruise by pressing the TURB key For descent the PDCS offers ECON or MANUAL schedules The ECON schedule of climb cruise and descent is computed to provide data for minimum trip cost based on the flight index provided to the computer Flight index is a number between zero and 200 which is a measure of the relative cost effects of flight time and fuel An index of zero implies that fuel economy is the exclusive criterion and the PDCS will schedule the ECON speed to minimize fuel consumption A high flight index infers that flying time is of greater value than fuel The ECON spe
101. not in the stowed and locked position 2012 Captain Sim www captainsim com Aircraft Systems 72 DO NOT USE FOR FLIGHT THRUST REVERSER SCHEMATIC THRUST RLWSRSLERE ENS 2 SYSTEM TANDET GEAR DOW SYSTEM REVERSER UNLOCKED OVERRIJUE SWITCH UP gt REVERSER INTERLOCK PRESSUREB jeh SMITCH E AE SELECTOR VALVE z5 pz AIRPLANE RETRACT HIN ON GROUND MUMBEB 4 RCVERSER CONDITION NUMBER 1 REVERSER umm SYSTEM A PRESSURE EXTENDING PDCS SYSTEM DESCRIPTION GENERAL The performance data computer system PDCS provides the crew with flight guidance data to assist in achieving the most efficient and economical operation of the airplane The data is presented in the form of digital displays on the CDU and bug displays on the EPR indicator s The PDCS is controlled by the crew and consists of a computer a control display unit CDU and mode annunciator The primary function of the PDCS is to compute and display target airspeed and EPR settings for each phase of flight takeoff climb cruise descent holding and go around For each of these phases of flight flight modes the PDCS computes and displays optimum EPR and airspeed values on the CDU and drives the EPR bug s to the computed values In addition to the phase of flight data other flight guidance data performance functions are available from the PDCS These functions are altitude intercept flight level calcul
102. ntains any bank attitude within limits e Selectable in MANUAL mode only HDG SEL solenoid held on spring loaded to the center position Establishes preselected heading mode Maintains the heading selected for the Captain s HSI HEADING HOLD center position Autopilot engaged Bank angle lt 5 degrees Airplane rolls wings level and maintains heading Bank angle gt 5 degrees Airplane maintains bank attitude CWS input Bank angle lt 5 degrees When the force is released the airplane rolls wings level Bank angle gt 5 degrees When the force is released the airplane maintains bank attitude 56 DO NOT USE FOR FLIGHT 6 Autopilot Aileron ROLL Engage Switch The aileron roll channel may be operated independently of the pitch channel in the MAN or VOR LOC modes of operation DISENGAGED Mechanically locked until interlock circuitry is satisfied e Spring loaded to DISENGAGED if interlock is broken ENGAGED Solenoid held if interlocks are satisfied e The Mode Selector must be in MAN e Will not engage if force is being applied to the control wheel 7 Autopilot Elevator PITCH Engage Switch The elevator pitch channel may be operated independently of the roll channel in the MAN mode only DISENGAGED Mechanically locked until interlock circuitry is satisfied e Spring loaded to DISENGAGED if interlock is broken ENGAGED Solenoid held if interlocks are satisfied e The Mode Selector must be in MAN e Will not engage
103. nter tank fuel is used before main tank fuel even though all fuel pumps are operating Individual pressure sensors monitor the output pressure of each pump FUEL CROSSFEED The engine fuel manifolds are interconnected by use of the crossfeed valve The valve is DC motor operated from the battery bus The valve provides a means of directing fuel to both engines from any tank FUEL SHUTOFF VALVES Fuel shutoff valves are located at the engine mounting wing stations The valves are DC motor operated from the hot battery bus They close whenever the respective engine fire warning switch is pulled or engine start lever is placed to CUTOFF FUEL TANK LOCATION AND CAPACITIES USABLE FUEL Main tanks No 1 and No 2 are integral with the wing structure The center tank lies between the wing roots within the fuselage area and extends out into the wing structure These figures represent approximate amounts of usable fuel The appropriate weight and balance control and loading manual gives exact figures for all conditions TANK GALLONS POUNDS NO 1 1 430 9 580 NO 2 1 430 9 580 CENTER 737 100 1860 737 100 12462 200 F C 1920 200 F C 12864 ADV 2300 ADV 15410 TOTAL 5 163 34 590 AUXILIARY 810 5 429 TOTAL 5 973 40 019 Usable fuel at level attitude fuel density 6 7 pounds per US gallon 2012 Captain Sim www captainsim com FUEL SCHEMATIC T aaa a ENGINE FUEL SHUT OFF VALVE ee ANAA ee ee Oe
104. omputer PITOT STATIC SYSTEM The pitot static P S system provides pitot and static pressure inputs to pressure sensing instruments and systems which have functions that vary with altitude and or airspeed A separate pitot system with probes mounted on the vertical stabilizer is provided for the elevator feel system A blocked or frozen pitot and or static system may affect the following primary airplane system Mach airspeed indicator Vmo Mmo warning altimeter vertical speed indicator true airspeed static air temperature flap load relief system elevator feel system autopilot ground proximity warning system altitude alert cabin pressure flight recorder transponder altitude reporting flight director altitude hold TAT or TAT EPRL yaw damper Mach trim AIR DATA COMPUTER The ADC receives pitot and static pressure inputs from the respective pilot s P S system or from the alternate static system if selected The ADCs converts these pressure inputs to electrical signals used to operate various flight instruments and airplane systems ANGLE OF ATTACK There is one angle of attack sensor located on the left side of the forward fuselage The vane measures airplane angle of attack relative to the air mass 7 1 2012 Captain Sim www captainsim com 5 4 2 Captain FLIGHT MANUAL Part II Aircraft Systems 94 j y DO NOT USE FOR FLIGHT COMPASS SYSTEMS Two compass systems are ins
105. on of the leading edge devices is determined by selecting trailing edge flap position At flaps position 40 arms the flap load relief system which automatically will cause flap retraction to position 30 in the event of excess airspeed 20 21 Flap Gates Prevents inadvertent flap lever movement beyond e position 1 to check flap position for one engine inoperative go around e position 15 to check flap position for normal go around LEADING EDGE DEVICES Ci3 LEADING EDGE FLAPS LIGHTS 1 Leading Edge Flaps Transit Light 2 Leading Edge Flaps Extended Light 1 Leading Edge Flaps Transit LE FLAPS TRANSIT Light Illuminated amber any leading edge device in transit or not in programmed position with respect to trailing edge flaps 2 Leading Edge Flaps Extended LE FLAPS EXT Light Illuminated green all leading edge flaps extended and all leading edge slats in extended intermediate position trailing edge flap positions 1 2 and 5 OR e all leading edge devices fully extended trailing edge flap positions 10 through 40 2012 Captain Sim www captainsim com 92 DO NOT USE FOR FLIGHT A02 LEADING EDGE DEVICES LE DEVICES ANNUNCIATOR PANEL 1 5 Leading Edge Devices Transit Lights 2 a 2 6 Leading Edge Devices Extended Lights 3 7 Leading Edge Devices Full Extended Lights 3 4 Leading Edge Annunciator Panel Test Switch Leading Edge Devices LE DEVICES Annunciator Panel Indica
106. r Switch 1 4 AC Ammeter Indicates engine generator load in amperes 2 Ground Power GRD POWER AVAILABLE Light Illuminated blue external power bus is powered by ground power supply Remains illuminated as long as an AC ground power source is attached outside the airplane 3 Ground Power GRD PWR Switch Three position switch spring loaded to neutral OFF disconnects ground power from both generator busses ON if momentarily moved to ON position and ground power is available removes previously connected power from AC generator busses connects ground power to both AC generator busses if power quality is correct switches the ground service bus to the generator bus 1 deactivates the ground service switch O10 BUS SWITCHING 1 6 Transfer Bus Off Light eus TRANS 27 Bus Off Light 3 9 Generator Bus Off Light 4 12 Generator Switch 5 Bus Transfer Switch 8 APU Generator Bus Off Light 10 11 APU Generator Switch TRANSFER BUS OFF ay iam GEN GEN OFT OFF BUS Bus 11 1 6 TRANSFER BUS Light Illuminated amber related transfer bus is inactive 2 7 BUS OFF Light Illuminated amber related generator bus is inactive 3 9 Generator Off Bus GEN OFF BUS Light Illuminated blue related generator is not supplying the generator bus 2012 Captain Sim www captainsim com 69 DO NOT USE FOR FLIGHT 4 12 Generator S
107. r indicates residual voltage of generator selected Associated generator switch must be OFF With associated generator switch ON AC voltmeter drives off scale and residual voltage cannot be read 2012 Captain Sim www captainsim com Aircraft Systems 67 DO NOT USE FOR FLIGHT O08 GENERATOR DRIVE AND STANDBY POWER PANEL 5 1 6 Low Oil Pressure Lights 2 7 High Oil Temperature Lights 3 10 Disconnect Switches Guarded And Safetied 1 E w 4 11 Generator Drive Oil Temperature Indicator E 7 5 Standby Power Light a 8 Standby Power Switch 9 Drive Temperature Switch DISCONNECT OFF DRIVE TEMP 0 10 1 6 LOW OIL PRESSURE Lights IN gt Illuminated amber generator drive oil pressure is DRIVE CAN BE ini i imi See 9 below minimum operating limits UN S A ar 2 7 High Oil Temperature HIGH OIL GE J GE VE Lights uis TEMP JIL TEMP 2 s Illuminated amber generator drive oil temperature exceeds operating limits 3 10 DISCONNECT Switches guarded and safetied Disconnects generator drive Generator drive cannot be re engaged in the air 4 11 Generator Drive Oil Temperature GEN DRIVE OIL TEMP Indicator Displays the temperature of the oil used in the generator drive IN scale inner Displays the temperature of the oil entering the generator drive RISE scale outer Displays the temperature rise within the generator drive Higher than
108. r pedals The SPEED BRAKE lever allows manual or automatic symmetric actuation of the spoilers captainsim Captain Sin 737 Captain FLIGHT MANUAL Part II Aircraft Systems 85 DO NOT USE FOR FLIGHT FLIGHT CONTROL SURFACES Pitch control is provided by e two elevators e movable horizontal stabilizer Roll control is provided by e two ailerons e four flight spoilers Yaw control is provided by a single rudder During takeoff the rudder becomes aerodynamically effective between 40 and 60 knots TE flaps and LE flaps and slats provide high lift for takeoff approach and landing In the air symmetric flight spoilers are used as speed brakes On the ground symmetric flight and ground spoilers destroy lift and increase braking efficiency FLIGHT CONTROL SURFACES LOCATION FLIGHT SPOILERS GROUND SPOILERS LE FLAPS LE SLATS TRAILING EDGE Os FLAPS ELEVATOR AILERONS STABILIZER 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS O01 FLIGHT CONTROL PANEL FLT CONTROL STANDBY HYD w LOW BlANTITY Tar STAY 7 Alternate Flaps Master Switch Guarded To Off 8 Alternate Flaps Position Switch 9 10 Flight Spoiler Switches Guarded To On 11 Feel Differential Pressure Light RUD A ALR y L 12 Yaw Damper Light 2 E ae Tm 13 Yaw Damper Switch ALT
109. ransmitting and receiving When a pulse intercepts a target the energy is reflected as an echo or return signal back to the antenna From the antenna the returned signal is transferred to the receiver and processing circuits located in the receiver transmitter unit The echoes or returned signals are displayed on an indicator Radio waves travel at the speed of 300 million meters per second and thus yield nearly instantaneous information when echoing back Radar ranging is a two way process that requires 12 36 micro seconds for the radio wave to travel out and back for each nautical mile of target range As shown in the distance illustration below it takes 123 6 micro seconds for a transmitted pulse of radar energy to travel out and back from an area of precipitation 10 nautical miles away 20 NM ROUND TRIP IN 123 6 MICROSECONDS 10 NM WEATHER RADAR PRINCIPLES Airborne weather avoidance radar as its name implies is for avoiding severe weather not for penetrating it Whether to fly into an area of radar echoes depends on echo intensity spacing between the echoes aircraft capabilities and pilot experience Remember that weather radar detects only precipitation drops it does not detect minute cloud droplets nor does it detect turbulence Therefore the radar provides no assurance of avoiding instrument weather in clouds and fog The indicator may be clear between intense echoes this clear area does not necessarily mean it is s
110. raulic pressure in the brake accumulator can still provide several braking applications or parking brake application ANTISKID PROTECTION The brake system provides each main gear wheel with individual antiskid protection The ANTISKID control switches control power to the antiskid controllers When the system detects a skid the associated antiskid valve modulates brake pressure until skidding stops The antiskid system also provides locked wheel touchdown and hydroplane protection An ANTISKID INOP light illuminates anytime there is a system malfunction Both ANTISKID INOP lights illuminated indicates there is a disagreement between the PARKING BRAKE lever position and the parking brake shutoff valve position AUTOBRAKE SYSTEM The autobrake system uses hydraulic system B pressure to provide automatic braking at preselected deceleration rates immediately after touchdown The system operates only when the normal brake system is functioning Antiskid system protection is provided during autobrake operation LANDING The digital autobrake system arms for landing when e air ground safety sensor is in the flight mode e ANTISKID control switches are ON e AUTO BRAKE selector switch is positioned to MIN MED or MAX Three levels of deceleration can be selected for landing However on dry runways the maximum autobrake deceleration rate in the landing mode is less than that produced by full pedal braking After landing autobrake application begin
111. rovides low energy ignition to one igniter 1 2 with the Engine Start Lever in IDLE FLT Provides high energy ignition to two igniters when the Engine Start Lever is in IDLE 10 ENGINE CONTROLS 6 7 Forward Thrust Lever 8 9 Reverse Thrust Lever 10 11 Engine Start Lever 6 7 Forward Thrust Lever e Controls engine thrust e Cannot be advanced if the reverse thrust lever is in the reverser deployed position 8 9 Reverse Thrust Lever e Controls engine reverse thrust Reverse thrust cannot be selected unless the forward thrust levers IDLE Note When the reverse thrust levers are moved out of IDLE towards reverse thrust pawls are forced into openings locking the forward thrust levers in the idle position Note The ability of each reverse thrust lever and its corresponding forward thrust lever to move depends on the position of the other lever because each is capable of locking out the other pawl attached to the forward thrust levers 10 11 Engine Start Lever IDLE e Controlled fuel flow is supplied to the engine and ignition circuits are energized CUTOFF e Closes the main fuel shutoff valve and the main engine control shutoff valve e Ignition system is de energized 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 78 DO NOT USE FOR FLIGHT P03 PDCS CONTROL DISPLAY UNIT CDU 1 Cathode Ray Tube CRT Display 2 CRT Display Symbols 3
112. rplane is in landing configuration ALERT CONDITIONS GPWS provides warnings and or alerts if one of the following conditions exists e excessive barometric descent rate excessive terrain closure rate altitude loss after takeoff or go around unsafe terrain clearance when not in the landing configuration excessive deviation below glideslope The GPWS alerts and the condition which causes each alert are presented on the following GPWS annunciation chart 2012 Captain Sim www captainsim com DO NOT USE FOR FLIGHT GPWS ANNUNCIATIONS AURAL ALERT VISUAL ALERT DESCRIPTION MODE 1 MK II PULL UP lights Excessive descent rate SINK RATE MODE 1 MK II PULL UP lights Follows SINK RATE if sink rate becomes cont severe Also follows TERRAIN alert WHOOP WHOOP excessive terrain closure rate continues and PULL UP landing gear and or flaps not in landing configuration MODE 2 MK II PULL UP lights Excessive terrain closure rate TERRAIN MODE 3 MK II PULL UP lights Excessive altitude loss after takeoff or go DON T SINK around MODE 4A MK II PULL UP lights Unsafe clearance during approach with TOO LOW GEAR landing gear up or TOO LOW TERRAIN MODE 4B MK II PULL UP lights Unsafe clearance during approach with flaps TOO LOW FLAPS not in landing configuration or TOO LOW TERRAIN MODE 5 MK II BELOW G S w P Deviation below glideslope The volume and GLIDESLOPE INHIBIT lights repetition rate increa
113. s of the indicator 5 HSI Heading HDG Selector e selects desired flight director heading e captain s selector can set desired heading for autopilot 6 Course Pointer and COURSE Counter Reflects the course set by the HSI course selector 7 To From Ambiguity Indicator Displays direction to a VOR station along the radial selected by the HSI course selector 8 Heading Marker Displays the heading set by the HSI heading selector 9 Course Deviation Bar VOR 1 dot 5 degrees LOC 1 dot 1 degree 10 HSI COURSE Selector e selects VOR radial or LOC course for flight director 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 97 DO NOT USE FOR FLIGHT e captain s selector can set VOR radial or localizer course for autopilot 11 Compass Failure Flag 12 Glideslope Failure Flag Tm 13 VOR LOC Failure Flag 11 COMPASS Failure Flag 12 In view e Selected compass is invalid e electrical power loss to HSI e compass card malfunction 12 Glideslope GS Failure Flag In view only with localizer frequency tuned e glideslope signal below acceptable level e failed glideslope receiver e electrical power loss 13 VOR LOC Failure Flag In view e VORor LOC signal below acceptable level e NAV receiver malfunction e electrical power loss MACH AIRSPEED INDICATORS Two Mach airspeed indicators display indicated airspeed Mach and Vmo The electr
114. s when e both Thrust Levers are retarded to near IDLE and e the main wheels spin up To maintain the selected landing deceleration rate autobrake pressure is reduced as reverser thrust is applied The total deceleration of reverse thrust and braking is equal to the selected deceleration rate The autobrake system brings the airplane to a complete stop unless the braking is terminated by the pilot AUTOBRAKE DISARM The pilots may disarm the autobrake system by moving the selector switch to the OFF position This action does not cause the AUTO BRAKE DISARM light to illuminate After braking has started any of the following pilot actions disarm the system immediately and illuminate the AUTO BRAKE DISARM light e moving the SPEED BRAKE lever to the down detent e advancing the Thrust Levers as for go around or e applying manual brakes PARKING BRAKE The parking brake is set by depressing both brake pedals pulling the PARKING BRAKE lever back then releasing the pedals This mechanically latches the pedals in the depressed position and commands the parking brake valve to close The parking brake is released by depressing the pedals until the PARKING BRAKE lever releases A fault in the parking brake system may cause the ANTISKID INOP lights to illuminate 737 Captain FLIGHT MANUAL Part II Airc ea fF Cue ome diti 5VySLCITIIS 130 DO NOT USE FOR FLIGHT CONTROLS AND INDICATORS C15 LANDING GEAR PANEL LANDIN
115. se as deviation continues CONTROLS AND INDICATORS G01 G05 FIRE WARNING AND MASTER CAUTION SYSTEM CAPTAIN 1 Fire Warn Light 2 Master Caution Light 3 7 System Annunciator Panel FIRE MASTER WARN CAUTION BELL CUTOUT SH RESET Et KP F O 1 5 System Annunciator Lights 6 Master Caution Light 7 Fire Warn Light MASTER FIRE WARN BELL CUTOUT T sv _ OVERHEAD oors fare cowo 737 Captain FLIGHT MANUAL Part II Aircraft Systems 137 DO NOT USE FOR FLIGHT A11 MACH AIRSPEED WARNING AND STALL WARNING TEST SWITCHES 1 2 Mach Airspeed Warning Test Switch 3 Stall Warning Off Light 4 Test Indicator 5 Stall Warning Switch a UU MACH AIRSPEED WARNING TEST STALL WARNING HTA GFF 1 2 MACH AIRSPEED WARNING TEST Switch Push Tests respective Mach Airspeed warning system e cClacker sounds e inhibited while airborne 3 STALL WARNING OFF Light Illuminated amber indicates a failure of the angle airflow sensor heater a system signal failure or a power failure 4 TEST INDICATOR Rotating indicates electrical continuity through the angle airflow sensor and flap position transmitter during TEST 5 STALL WARNING SWITCH Normal heater power for the angle airflow sensor is available only if engine 1 is operating or the air ground safety sensor is in the air mode Test OFF light Test Indicator rotates
116. series N1 and N2 This is a forward fan type engine with a twin spool axial compressor consisting of a low pressure unit N1 and a high pressure unit N2 Each engine has individual flight deck controls Thrust is set by positioning the thrust levers The forward thrust levers control forward thrust from idle to maximum The reverse thrust levers control thrust from reverse idle to maximum reverse POWER PLANT SCHEMATIC FAM AIR ETH STAGE SLEED AIR 13TH STAGE SLEED AIR LOW PRESSURE CONPRESSOR PRESSURE COUMSRESSOR BURNER CANS TURBINES HYDRAULIC BURP 7 M gt r DRIVE FAM THRUST REVERSER BYPASS DEFLECTOR DOOR OIL BUMP FUEL PUAPS ENGINE FROM ENGINE DUE FUEL INDICATING SYSTEMS AIR DRIVEN I COCKPIT CONTROLS STARTER amp INDICATORS FR H ELECTRICAL STSTEM FRON FRON PREUAATIC FUEL SYSTEM ENGINE FUEL SYSTEM Fuel is delivered to the engines at pressures and flow rates required to obtain desired engine thrust Fuel leaves the fuel tank and enters through the engine fuel shutoff valve The engine fuel shutoff valve is controlled by the engine start lever and the engine fire warning switch When the engine fuel shutoff valve is closed the FUEL VALVE CLOSED light located on the forward overhead panel will illuminate dim N 2012 Captain Sim www captainsim com 737 Capta
117. sim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 46 DO NOT USE FOR FLIGHT PROBE AND SENSOR HEAT All pitot static probes the total air temperature probe and angle airflow sensors are electrically heated to prevent the formation of ice Alternate static ports are not heated ENGINE ANTI ICE SYSTEM Engine bleed air thermal anti icing prevents the formation of ice on the engine nose cowl lip compressor area and EPR probe Engine anti ice operation is controlled by individual ENG ANTI ICE switches The engine anti ice system may be operated on the ground and in flight WING ANTI ICE SYSTEM The wing anti ice system provides protection for the leading edge slats by using bleed air The wing anti ice system does not include the leading edge flaps With a valve open bleed air flows to the leading edge slats through a telescoping duct and is then exhausted overboard The wing anti ice system is effective with the slats in any position CONTROLS AND INDICATORS 019 WINDOW HEAT PANEL 1 4 Window Overheat Lights e 5 8 Window Heat On Lights a 9 10 12 13 Window Heat Switches 11 Window Heat Test Switch spring loaded to ES neutral A on L WINDOW HEAT R SIDE FWD pou FWD SIDE Illuminated amber overheat condition is detected OO LUC L 1 4 Window OVERHEAT Lights Note OVERHEAT light also illuminates if electrical power to window is interrupted 5 8
118. system controlled automatically STBY pressurization system controlled through the standby mode MAN e pressurization system controlled manually by Outflow Valve Switch e outflow valve operates from AC power e DC outflow valve operates from DC power e all auto and standby circuits bypassed CHECK Tests auto failure function of AUTO system 16 Cabin Flight Altitude CAB ALT FLT ALT Placard Used to determine setting for cabin altitude when operating in standby and manual modes 737 Captain FLIGHT MANUAL Part II Aircraft Systems 44 DO NOT USE FOR FLIGHT AIR SYSTEMS SCHEMATIC TO TO FLIGHT PASSENGER DECK CABIN W e F 1 MIXING l DISTRIBUTION MANIFOLD Walk GROUND PRECONDITIONED AIR CONNECTION 5 axes gFACKE VALVE PACK hu VALVE Fi Z ENGINE ISOL ENGINE BLEED ATION BLEED AIR VALVE AIR VALVE VALVE HIGH STAGE HIGH STAGE VALVE VALVE ns uar ATR CONNECTION CONDITION _ ENGINES OPERATING m BLEED AIR amp SUPPLYING AIR amp ICONDITIONED AIR CONDITIONING PACES 1 Cargo airplanes only 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 45 DO NOT USE FOR FLIGHT ANTI ICE RAIN Thermal anti icing TAI electrical anti icing rain repellent and windshield wipers are the systems provided for ice and rain protection
119. t capture if HDG SEL is used Roll commands can be increased or reduced manually during the capture phase prior to ON COURSE When ON COURSE CWS roll is high detent Crosswind compensation occurs after ON COURSE e ALT HOLD is selectable AUTO APP Auto Approach Mode Used to automatically capture ILS Localizer and glide slope e HDG SEL or CWS is used to achieve the intercept heading e LOC CAPTURE is the same as VOR LOC mode e LOC and G S are armed when e ILS frequency is tuned Autopilot Panel e Front Course is selected AUTO APP is selected G S is captured at 1 3 dot ALT HOLD trips OFF at G S capture Gain programming occurs after G S capture at 1500 feet radio altitude or below LOC sensitivity is reduced from 100 to 50 as altitude decreases to 100 feet G S sensitivity is reduced to 0 as altitude decreases to 50 feet e When ON COURSE and on G S CWS roll and pitch are high detent e AUTO APP is not selectable unless ILS frequency is selected e MAN G S Manual Glide Slope Mode Used to capture G S from above or to re capture after autopilot disengagement Note Do not select MAN G S when the airplane is more than 1 2 dot as depicted on the HSI from the glide slope e Operates the same as AUTO APP after G S capture 4 Autopilot System Select Switch Selects the hydraulic system used by the autopilot and yaw damper Transfer of systems will disengage the autopilot and yaw damper 5 Autopilot Heading Switch HDG OFF Autopilot mai
120. talled Directional gyros are connected to the RMI compass cards The RMI compass card is then connected to the HSI compass card CONTROLS AND INDICATORS L06 R06 ATTITUDE DIRECTOR INDICATOR ADI An attitude director indicator ADI on each pilot s panel displays a view of the pitch and roll attitude of the airplane The attitude display is shown on a colored tape with pitch and roll reference provided by vertical gyros Computed steering commands from the flight director computer are presented on the ADI by command bars These commands are viewed with respect to a fixed symbolic airplane When the GYRO warning flag is in view use the Vertical Gyro transfer switch to transfer the associated systems to an operating vertical gyro When the GS flag is in view use the VHF NAV switch to transfer to an operating system The localizer symbol moves left or right to indicate deviation from localizer centerline The localizer signal is covered by a mask until the flight director captures the glideslope After glideslope capture a VOR LOC failure flag on the HSI will cause the mask to cover the localizer symbol The localizer pointer and warning flag remain out of view with VOR frequencies selected The COMPUTER flag monitors the flight director system Switching is not installed for this problem 1 Bank Indicator and Scale 9 2 Attitude Display 3 Glideslope Pointer and Deviation Scale 4 Glideslope Warning Flag 5 Gyro Warning Flag 8 6
121. ted amber e indicates pack temperature has exceeded limits e related pack valve automatically closes and mix valves drive full cold e requires reset 2012 Captain Sim www captainsim com 39 DO NOT USE FOR FLIGHT 9 18 WING BODY OVERHEAT Light Illuminated amber e left light indicates overheat from bleed air duct leak in left inboard wing leading edge left air conditioning bay keel beam or APU bleed air duct e right light indicates overheat from bleed air duct leak in right inboard wing leading edge or right air conditioning bay 10 19 BLEED TRIP OFF Light Illuminated amber indicates excessive engine bleed air temperature rela e ted engine bleed air valve closes automatically e requires reset 12 TRIP RESET Switch PUSH if fault condition is corrected e resets BLEED TRIP OFF PACK TRIP OFF and DUCT OVERHEAT lights e lights remain illuminated until reset 11 20 Engine BLEED Air Switches OFF closes engine bleed air valve ON opens engine bleed air valve 13 APU BLEED Air Switch OFF closes APU bleed air valve ON opens APU bleed air valve when APU is operating 14 GASPER FAN Switch OFF gasper fan signalled off ON increases airflow to individual gasper outlets 15 Wing Body Overheat OVHT TEST Switch PUSH e tests wing body overheat detector circuits e illuminates both WING BODY OVERHEAT lights 737 Captain FLIGHT MANUAL Part II Aircraft Systems 40 DO NOT USE FOR FLIGHT 0
122. tes VREF speed for landing 4 TOTAL FUEL Weight Counter Indicates the total usable fuel remaining in all tanks 5 ZERO FUEL Weight Selector Used to set the ZERO FUEL weight counter to the correct zero fuel weight Maximum Landing Weight VREF MAX LDG WT VREF Placard Airspeeds on this placard depend on the maximum allowable landing gross weight of the airplane 2012 Captain Sim www captainsim com 125 DO NOT USE FOR FLIGHT HYDRAULICS The airplane has three hydraulic systems A B and standby The standby system is used if system A and or B pressure is lost The hydraulic systems power the following airplane systems flight controls leading edge flaps and slats trailing edge flaps spoilers landing gear wheel brakes nose wheel steering thrust reversers yaw damper autopilots cargo door cargo airplanes only Each hydraulic system has a fluid reservoir located in the main wheel well area The reservoirs are pressurized by engine bleed air directed into the system A reservoir Fluid balance lines interconnect all reservoirs Pressurization of all reservoirs ensures positive fluid supply to all hydraulic pumps and controls the fluid level in the reservoirs HYDRAULIC POWER DISTRIBUTION SCHEMATIC GROUND INTERCONNECT yd T MEE EE POTEN EEEE a E Ea Eo INBOARD halo pisi OUTBOARD ES RE F i ug ees FLT SPOILERS
123. tes position of individual leading edge flaps and slats Extinguished corresponding leading edge device retracted 1 5 Leading Edge Devices TRANSIT Lights Illuminated amber corresponding leading edge device in transit 2 6 Leading Edge Devices Extended EXT Lights Illuminated green corresponding leading edge slat in extended intermediate position 3 7 Leading Edge Devices FULL Extended FULL EXT Lights Illuminated green corresponding leading edge device in full extended position 4 Leading Edge Annunciator Panel TEST Switch Press tests all annunciator panel lights 737 Captain FLIGHT MANUAL Part II Aircraft Systems 93 DO NOT USE FOR FLIGHT FLIGHT INSTRUMENTS DISPLAYS SYSTEM DESCRIPTION The flight instruments provide information to aid the pilots in controlling the airplane throughout its flight regime The electric flight instruments receive input from an air data computer The pneumatic flight instruments receive input directly from the pitot static system An alternate static system is also available and may be selected from the flight deck AIR DATA SYSTEM The air data system consists of the pitot static system and one or two air data computers The system provides pitot and or static pressure information to various flight instruments and airplane systems The pressure information is provided in one of two ways either directly from the pitot static system or indirectly from an air data c
124. vailability of airport ground equipment The airstair is electrically operated and may be controlled from either inside or outside the airplane The airstair is stowed in a compartment just below the forward entry door The compartment has a pressure door that automatically opens before the airstair will operate For passenger safety upper handrails are attached to support brackets inside the entry door after the airstair is fully extended REAR VIEW To operate the FORWARD AIR STAIRS use Animation Control Panel Part II Aircraft Systems 34 DO NOT USE FOR FLIGHT OXYGEN SYSTEMS Two independent oxygen systems are provided one for the flight crew and one for the passengers Portable oxygen cylinders are located throughout the airplane for emergency use CONTROLS AND INDICATORS A09 OXYGEN CONTROLS AND INDICATORS 1 Flight Crew Oxygen Pressure Indicator 2 Passenger Oxygen Pressure Indicator 3 Passenger Oxygen On Light 4 Passenger Oxygen Switch 1 2 a Sm c QU E PRESS Oty PRESS x 1 100 3 4 12 Captain Sim www captainsim com 35 DO NOT USE FOR FLIGHT WATER SYSTEM SYSTEM DESCRIPTION The potable airplane water system is supplied from a single tank located behind the aft cargo compartment Fresh water is supplied to the galleys and lavatory sinks GALLEY S WATER QUANTITY INDICATOR WATER DISTRIBUTION LINE LAVATORY S SERVICE PANEL ld WATER TANK lt
125. warning horn cannot be silenced with the e landing gear warning HORN CUTOUT switch The warning indication is cancelled when the configuration error is corrected 2012 Captain Sim www captainsim com 737 Captain FLIGHT MANUAL Part II Aircraft Systems 135 DO NOT USE FOR FLIGHT MACH AIRSPEED WARNING SYSTEM Two independent Mach airspeed warning systems provide a distinct aural warning a clacking sound any time the maximum operating airspeed of Vmo Mmo is exceeded Each system operates from a mechanism internal to the respective pilot s Mach airspeed indicator The warning clacker can be silenced only by reducing airspeed below Vmo Mmo and can be tested at any time with the test switch STALL WARNING SYSTEM Natural stall warning buffet usually occurs at a speed prior to stall In some configurations the margin between stall and natural stall warning is less than desired Therefore an artificial stall warning device a stick shaker is used to provide the required warning GROUND PROXIMITY WARNING SYSTEM GPWS The GPWS provides alerts for potentially hazardous flight conditions GPWS alerts to the extent they are installed are for imminent impact with the ground detected windshear condition excessive angle of bank and glideslope deviation GPWS may also provide radio altitude and decision height callouts Note GPWS does not provide alerts for flight toward vertically sheer terrain or of shallow descents when the ai
126. witch GEN 1 GEN 2 Three position switch spring loaded to neutral OFF disconnects related engine generator from the generator bus ON connects related engine generator to the generator bus if the power quality is correct Disconnects the previous power source 5 Bus Transfer BUS TRANS Switch AUTO guarded position upon failure of one engine generator bus its transfer bus is switched to the active generator bus Allows TR3 to supply DC bus No 1 if TR1 fails OFF Isolates transfer busses by preventing operation of the bus transfer relays and opens TR3 disconnect relay Prevents the battery charger from switching to its alternate source of power main bus 2 Isolates TR3 from DC bus No 1 8 APU Generator Off Bus GEN OFF BUS Light Illuminated blue APU is at its operating speed and not powering a generator bus 10 11 APU Generator GEN Switch Three position switch spring loaded to center position OFF disconnects the APU from the generator bus ON connects the APU generator output to the generator bus if the quality is correct Note In flight if one generator bus is powered by the APU and the other APU GEN switch is moved to ON the second generator bus will not connect to the APU generator 737 Captain FLIGHT MANUAL Part II Aircraft Systems 70 DO NOT USE FOR FLIGHT ENGINES APU SYSTEM DESCRIPTION The airplane is equipped with two Pratt and Whitney JT8D ducted turbofan engines having two rotors in
127. y that it is isolated from each of the primary instruments and sensors This assures that failures within the PDCS do not affect the other systems The performance data computer has a complete built in self test capability which allows a complete checkout of the computer and all inputs and outputs If the PDCS fails the screen becomes blank In addition under some failure conditions the airspeed bug moves to 440 knots the EPR bugs move to 1 0 and the indicator inoperative flags appear If the air data computer fails the CDU displays a CADC fail message Failure of CADC causes the PDCS to be inoperative Under certain mode conditions if the fuel totalizer signal fails the screen displays Use EPR limit Flight crews can initiate self test procedures if desired When either airspeed or EPR validity is questioned or a self detection fault develops in the computation process the computer normally drives the appropriate bugs to 440 knots and 1 0 EPR APU SYSTEM The auxiliary power unit APU is a self contained gas turbine engine installed within a fireproof compartment located in the tail of the airplane The APU supplies bleed air for engine starting or air conditioning An AC electrical generator on the APU provides an auxiliary AC power source ACCESSORY COOLING AIR DUCT AIR DUCT AIR DIFFUSER DUCT EXHAUST DUCT APU FUEL LINE AIR INLET DOOR APU BLEED AIR DUCT APU OPERATION The APU operates up to the airpla

Download Pdf Manuals

Related Search

Related Contents

  Polti C110  Samsung MAX-DC650 Manuel de l'utilisateur  Ferplast Lod120 User's Manual  Vis hermétiques-accessibles compactes    TSSUB18 - Quickstart Guide  Pacemaker temporaneo bicamerale Manuale tecnico  Manual de autorizaciones de endoprótesis  注意 GX デスクパネル対向用 組立説明書 注意 GX - Garage  

Copyright © All rights reserved. Failed to retrieve file