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Aircraft Systems

1. 14 Cabin Altitude Knob Selects the maximum cabin altitude for the automatic cabin pressure control 15 Cabin Rate of Climb Indicator A rate of climb indicator shows rate of cabin pressure altitude change and is used as a reference in operating the cabin pressurization system www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 83 DO NOT USE FOR FLIGHT FLIGHT ENGINEER LOWER PANEL WO1 Fuel System Panel WO2 Clocks WO03 Hydraulic Brake Panel W04 Engine Oil Panel WO05 S O Panel Lighting Controls WO6 Service Interphone Switch W07 Door Annunciator Panel W08 Audio Selector Panel WO9 Fuel Heat Panel W10 Hydraulic Panel W11 Oxygen Panel W12 Oil Cooler Panel 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 84 DO NOT USE FOR FLIGHT WO1 FUEL SYSTEM PANEL 1 2 34 3 5 8 3 10 11 12 13 141516 17 21 22 2324 25 326 27 2H 29 30 31 32 33 1 5 7 8 10 11 13 17 Fuel Boost Pump Switch 2 4 6 12 14 16 23 29 Fuel Boost Pump Low Pressure Light Amber 3 9 15 Tank Quantity Indicator 18 26 30 Fuel Tank Quantity Indicators Test Switch 19 24 34 Fuel Crossfeed Manifold Valve in Transit Light Blue 20 25 31 Fuel Crossfeed Manifold Valve Switch 21 27 32 Engine Fuel Shutoff Valve Switch 22 28 33 Engine Fuel Shutoff Valve in Transit Light Blue 1 5 7 8 10 11 13 17 Fuel Boost Pump Switch ON for fuel boost pump operation 2
2. 2 With the function switch in TST or SBY 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 ON The indicator will automatically display in the Wx mode and 80 nm range Weather targets will be displayed in green yellow red or magenta Note A 60 second warm up time period is required before the system will transmit 4 Press the range down button to display 40 nm as the maximum range 5 Press the WxA button and observe that magenta areas if any flash 6 Repeat the manual tilt adjustment this time between the 0 and down 15 degrees positions www captainsim com 58 DO NOT USE FOR FLIGHT 7 Return the function switch to TST or SBY before taxiing 8 When you are ready for weather detection after takeoff or just before place the function switch to ON 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 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 use
3. 8 Navigation Lights Switch White tip mounted tail lights are installed on the trailing edges of the wing tips to provide a horizontal white beam aft These lights are controlled by the navigation light switch on the overhead panel marked NAVIGATION with ON OFF ON BAT positions Navigation lights red left and green right are provided in the outboard edge of each wing The lights are controlled by a switch marked NAVIGATION with ON OFF ON BAT positions on the overhead panel In the ON position the lights are powered by 28V AC and in the ON BAT position by 28V DC On some aircraft the ON position of the nav light switch activates the oscillating position lights The stationary position lights are on whenever the aircraft is powered Note The ON position will be used for all flight operations The ON BAT position induces unacceptable compass error and therefore will only be used for maintenance ground towing 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 39 DO NOT USE FOR FLIGHT 9 Beacon Anti Collision Lights The beacon lights on the top and bottom of the fuselage provide high intensity red flashes as a proximity warning of the aircraft Each beacon light consists of two partly silvered lamps covered with a red glass lens The lights are controlled by a switch marked Brc coN with ON OFF positions on the overhead panel 10 Wing Illumination Lights Two wing illuminati
4. PITOT and the right switch is marked PITOT STATIC AUX PITOT ELEV PITOT Each switch has OFF ON positions The left switch controls the heating of the left static ports left pitot temperature probe and left elevator pitot The right switch controls the heating of the right static ports right pitot auxiliary pitot and right elevator pitot Current for the left pitot heater and the three left static port heaters is supplied from the essential AC bus to ensure that power is available from any generator 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 50 DO NOT USE FOR FLIGHT 5 Heater OFF Light Amber Illuminated Pitot static heat switch OFF Pitot static heat switch ON and left or right pitot probe heater inoperative 021 STANDBY MAGNETIC COMPASS 1 Compas Correction Card T H du 3 TT GOL 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 51I DO NOT USE FOR FLIGHT AISLE STAND 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 32 DO NOT USE FOR FLIGHT Panels duplicated in 2D are listed in bold font PO1 PO7 ADF Control Panel PO2 POS Flight Director Controls P04 Radar Control Panel PO5 Windshear Failure Light PO6 Flap Position Switch P09 Control Stand P10 P11 VHF NAV COMM Control Panel P12 Autopilot Panel P13 Transponder TCAS Contro
5. Aircraft and Systems 38 DO NOT USE FOR FLIGHT 006 EXTERIOR LIGHTING PANEL TERIOR LOHTING LAK DIO RAW AT WHEEL MIRA in NAVIGATION BEACON wing WELL etn pn tmd n t m n LM om BAT OFF rl T at am n i g gt mn 8 1 4 Landing Lights Switch 5 Taxi Light Switch 6 7 Runway Turnoff Lights Switch 8 Navigation Lights Switch 9 Beacon Anti Collision Lights 10 Wing Illumination Lights 11 Main Wheel Well Lights Switch 1 4 Landing Lights Switch Landing lights in the fixed inboard wring L E and another in each outboard Krueger flap provides high intensity lighting for takeoff and landing Illumination of these lights is controlled by four switches on the lower edge of the overhead panel marked LANDING INBOARD L and R and LANDING OUTBOARD L and R 5 Taxi Light Switch A taxi light is mounted on the nose wheel strut The light is controlled by a switch on the lower edge of the overhead panel marked TAXI with ON OFF positions 6 7 Runway Turnoff Lights Switch A RUNWAY TURNOFF light is adjacent to and inboard of the inboard fixed landing light The lights provide ground roll illumination and are controlled by two switches on the lower edge of the overhead panel marked RUNWAY TURNOFF L and R with ON OFF positions Note Do not illuminate LANDING and or RUNWAY TURNOFF lights for more than 5 minutes while stationary on the ground Allow a 5 minute cooling period before re illuminating
6. The light will illuminate when the standby system is pressurized 15 System A Pressure Gauge This electrical gauge on the S O lower panel indicates hydraulic system pressure or accumulator preload depending on whether or not system A is pressurized The gauge will read ZERO if accumulator preload is lost regardless of actual hydraulic pressure A C 32724 and following have no accumulator thus when system is unpressurized the gauge will read ZERO 16 System A Overheat Light The light will illuminate 104 C when system A return fluid temperature is excessive extinguishes at 74 C 17 System A Quantity Indicators The system A quantity indicating system consists of a float type level transmitter with a direct reading gauge at the reservoir and two remote indicators located as follows One is on the S O lower panel and one at the hydraulic servicing station Normal reading is 4 4 gallons F on the ground The direct reading gauge and the indicator at the service station have a refill RF mark at the 3 gallon level Extension of the leading edge flaps and slats will decrease the indicated quantity by approximately 8 gallons Additionally cold soak caused by long periods of cruise at low outside are temperatures will cause a gradual reduction in indicated quantity of approximately 1 0 gallon This indicated loss will be regained when the fluid temperature increases www captainsim com 727 Captain FLIGHT MANUAL Part II
7. 1 APU Master Switch This switch with OFF ON START positions is on the APU control panel With this switch in the OFF position the APU stops as a result of the following automatic actions the pneumatic solenoid actuates the 110 speed switch which opens power to the APU fuel solenoid valve and the bleed air solenoid valve The generator breaker is tripped When the APU engine slows down the low oil pressure switch closes the APU fuel valve With the APU master switch in the OFF position the APU fire warning and extinguishing system remain energized from the battery bus With the master switch in the ON position if the battery switch is in the ON position the APU fuel valve opens and if power is on the Nol 1 DC bus the APU light illuminates With the master switch in the START position and the battery switch in the ON position the following actions will take place and the APU will start the APU starter motor is energized the APU begins cranking and the APU crank light illuminates 2010 Captain Sim www captainsim com 98 DO NOT USE FOR FLIGHT When oil pressure builds up the ignition is energized the fuel solenoid valve opens fuel is injected and ignited At approximately 35 of governed speed the start motor is de energized and the APU crank lights goes out 2 APU Generator Breaker Light This amber light marked GENERATOR is adjacent to the APU generator breaker switch When the light illuminates it indicates that
8. 2 100 Foot Pointer Displays altitude in 100 foot increments One full rotation of pointer equals 1000 feet 3 Altitude Numerical Counter Displays altitude in thousands and hundreds of feet 4 Failure Warning Flag In view indicating loss of signals power or altitude error 5 6 Altimeter Setting Windows Can be set in Millibars or inches Hg 7 Barometric Setting Control Rotation of the control adjusts the barometric setting on the inches of mercury in hg indicator NJ 10 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 18 DO NOT USE FOR FLIGHT 8 Reference Altitude Bug Selector Turn clockwise for higher reference altitude L15 DME INDICATOR AND WINDSHEAR AHEAD LIGHTS 1 DME indicator 2 3 Windshear Ahead Lights Amber 1 DME indicator Provides slant range in nautical miles to station tuned 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 19 CENTER FORWARD PANEL C01 Lights Test Marker C02 Altitude Alerting Panel C03 Marker Lights C04 Standby Artificial Horizon C05 Annunciators C06 Controls Trimmer Position Indicators C07 Engine Instrument Panel C08 Flaps Indicators Master Warning C09 Low Oil Pressure Oil Filter Bypass Caution Lights C10 Landing Gear Control Panel 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 20
9. 2 8 Control Cabin and Passenger Cabin Temperature Selectors The control cabin and passenger cabin temperature selectors are on the Second Officer s upper panel These selectors electrically control the air mix valves through individual cabin temperature regulators The scale on each selector has an automatic range which allows a choice of cabin temperatures The position of the air mix valves can be manually controlled with the selector knob in the appropriate manual position cool or warm The knob is spring loaded to OFF from the MANUAL COOL or MANUAL WARM positions 3 7 Control Cabin and Passenger Cabin Air Mix Valve Indicators The indicators marked CONTROL CABIN AIR MIX VALVE and PASSENGER CABIN AIR MIX VALVE with a range from COLD to HOT are on the Second Officer s upper panel Their function is to display the position of their respective air mix valves 4 Air Temperature Indicator A temperature indicator on the Second Officer s upper panel is calibrated from 0 1009C It indicates temperature in the duct or cabin area selected with the air temperature selector 5 Duct Overheat Reset Switch The duct overheat reset switch marked RESET is on the Second Officer s upper panel This switch is used whenever an overheat condition is indicated by illumination of passenger or control cabin duct overheat lights Illumination of either of these lights occurs when the overheat condition in the main supply duct causes the air mix valves to drive to th
10. DO NOT USE FOR FLIGHT CO1 LIGHTS TEST MARKER 1 Marker Beacon Sensitivity Switch 2 Master Test and Dimming Switch 1 3 1 Altitude Alert System OFF Flag 2 Altitude Set Indicator 3 Altitude Set Control 2 Altitude Set Indicator Indicated selected altitude in 100 foot increments 3 Altitude Set Control Used to set selected altitude in altitude indicator An altitude alerting system gives audible and visual indication of approaching an altitude acquisition or departing from an altitude deviation In the acquisition mode an aural signal tone will sound momentarily and the alert lights will come on when passing through a point approximately 900 feet above or below the selected altitude The light will remain on until approximately 300 feet from the selected altitude In the deviation mode when departing the selected altitude the aural signal will sound momentarily and the alert lights will come on when passing through a point approximately 300 feet above or below the selected altitude The alert light will remain on until reset by pressing the alert light 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 21 DO NOT USE FOR FLIGHT C03 MARKER LIGHTS 1 Airways Light Clear 1 2 Middle Marker Light Amber 2 3 Outer Marker Light Blue 3 1 Airways Light Clear Illuminates steady when over airways beacon or flashing when over airway fan marker beacon
11. Generator Drive Low Pressure Light Amber 10 11 Galley Power Switch 12 13 14 Generator Drive Temperature Switch 15 External Power Switch 16 External Power Connected Light Clear 2 5 8 Generator Drive Disconnect Switches Disconnect drive from engine and trip generator breaker 3 6 9 Generator Drive Low Pressure Lights Amber Indicate oil pressure in the constant speed drive is below operating limits 10 11 Galley Power Switch ON Galley power available to galleys as selected 12 13 14 Generator Drive Temperature Switch RISE Indicate oil temperature increase through generator drive IN Indicate temperature of oil at in put 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 7 DO NOT USE FOR FLIGHT 15 External Power Switch ON External power on the bus tie When external power is connected the generator breakers and APU generator breaker automatically trips for overvoltage or phase unbalance faults OFF If external power connected external power DC bus battery transfer bus and external power 115V AC bus powered GND SERVICE 115V AC transfer bus also powered 16 External Power Connected Light Clear ON Ground power available at external power connection UO3 ELECTRICAL POWER PANEL 1 10 19 Generator Drive Oil Temperature 10 Indicator fa wa 1 irum 2 11 21 Bus Tie Breaker Light Amber 1 our ES Lo 19 ili ght GEN DRIVE GIN DRI
12. VOR LOC Annunciator 3 9 Glide Slope Annunciator 6 HDG Annunciator 7 ALT Annunciator 45 6 7 1 1 MDA light amber The MDA light illuminate when you pass the altitude you have set on the radio alt bug for the MDA Minimum Descent Altitude for the approach Approach Progress Display Annunciators labeled ALT SEL ALT HDG VOR LOC and GLIDESLOPE are located on each pilot s forward instrument panel ALT SEL VOR LOC and GLIDESLOPE may illuminate amber or green ALT and HDG will only illuminate green 2 8 VOR LOC Annunciator AMBER System armed in NAV LOC or AUTO G S modes prior to intercept of VOR radial or localizer beam GREEN Radial or localizer captured 3 9 Glide Slope Annunciator AMBER System armed in AUTO G S prior to intercept of glide slope GREEN A Glide slope captured Green when MAN G S selected 6 HDG Annunciator Paralleles green ENG annunciator of HDG SEL switch on autopilot control panel GREEN Autopilot heading select is active 7 ALT Annunciator GREEN Autopilot is operating in altitude hold 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 15 DO NOT USE FOR FLIGHT L10 STANDBY ALTIMETER An absolute pressure measuring altimeter is provided as a standby altimeter The indicator has a range of 1 000 to 50 000 feet indicated by a drum and pointer 1 1 Digital Display NW 2 100 Foot Pointer P Oi 4 5 Altimeter Setting Win
13. the other switched to standby 6 7 9 10 Code Selector Knobs Rotate to set code on ATC Display Window 8 Ident Pushbutton Initiates ident feature for ATC 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 68 DO NOT USE FOR FLIGHT P14 AFT PEDESTAL PANEL 1 Radio Panels and Autopilot Lights Control 2 Rudder Trim Wheel and Indicator 3 Horn Cutout Lever 4 Aileron Trim Wheel and Indicator 5 Stabilizer Brake Release Knob 1 Radio Panels and Autopilot Lights Control Controls intensity for the dial lights on the electronic control panels 2 Rudder Trim Wheel and Indicator A rudder trim wheel on the control stand moves the rudder feel and centering cam in the vertical fin to produce rudder trim Linkage is through a separate rudder trim cable system The amount of rudder trim is indicated by a pointer moving over a scale marked RUDDER TRIM which is adjacent to the rudder trim wheel 4 Aileron Trim Wheel and Indicator Positions the aileron feel and centering spring through a gear and cable system A pointer on the control stand indicates TRIM position Trim is ineffective in the manual reversion mode 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 69 DO NOT USE FOR FLIGHT FLIGHT ENGINEER UPPER PANEL U01 DC Electrical Power Panel U02 U03 U04 Electrical Power Panel U05 Oxygen System Panel UO6 Air
14. 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 ANTENNA GAIN vs SIDELOBS ANGLE CHARACTERISTIC Ew b 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 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 Green level 1 Yellow level 2 Red level 3 and Magenta level 4 PREFLIGHT PROCEDURES The system never transmits in the OFF SBY or TST modes Accomplish the following procedures completely and exactly 1 Place the radar controls in the following positions e Function switch to TST e Tilt to UP 7 will be shown on the indicator display upper right corner The test pattern will appear
15. 10 Slip Indicator 2 Glide Slope Pointer In parallel with pointer on HSI OUT OF VIEW Until localozer frequency selected and the GS signal malfunction IN VIEW GS receiver power off or fails GS receiver fails GS signal belowusable level In parallel with pointer on HSI 4 Bank Indicator Airplane bank angle is displayed by an indicator read against a scale at the top of the instrument The bank angle scale is marked at 10 20 309 45 and 60 left and right 5 Symbolic Airplane Fixed symbol of airplane Attitude reference when related to horizon 6 Gyro Warning Flag IN VIEW Vertical gyro power is lost Giro in fast erection cycle Instrument amplifier power is lost 7 Course Deviation Scale The course deviation scale which is always perpendicular to the course bar indicates the amount the airplane is displaced from the desired course Each dot on the scale represents 5 of displacement on VOR and 1 1 4 of displacement on a localizer The point at which the bar aligns with the course arrow indicates no displacement from the selected course 9 LOC Warning Flag Covers runway symbol appears with navigation LOC warning flag on HSI for failure indication 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 12 DO NOT USE FOR FLIGHT 10 Slip Indicator A slip indicator located on the bottom of the flight director indicator is provided to monitor s
16. B when illuminated When system A or B hydraulic pressure to the aileron power unit is low or the system A or B aileron switch is in the OFF position the aileron system A or B low pressure annunciator will illuminate 2 5 Rudder Low Pressure Annunciators Two amber annunciators on the First Officer s panel are marked RUDDER SYSTEM A and RUDDER SYSTEM B The annunciator marked RUDDER SYSTEM B will illuminate when hydraulic system B power to the upper rudder is low or switched off rendering the upper rudder inoperative The annunciator marked RUDDER SYSTEM A will illuminate when hydraulic system A power to the lower rudder is low or switched off 3 6 Elevator Low Pressure Annunciators Two amber annunciators on the First Officer s panel display ELEVATOR SYSTEM A and ELEVATOR SYSTEM B when illuminated When system A or B hydraulic pressure to the elevator power unit is low or the system A or system B elevator switch is in the OFF position the corresponding elevator low pressure annunciator will illuminate 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 29 DO NOT USE FOR FLIGHT R12 BRAKE PRESSURE INDICATORS 1 Pneumatic Brake Pressure Indicator 2 Hydraulic Brake Pressure Indicator 1 Pneumatic Brake Pressure Indicator Normal reading is 1200 PSI nominal 2 Hydraulic Brake Pressure Indicator This indicator indicates pressure on the air side of the brake accumulator
17. Conditioning System Panel U07 Engine Start Valve Indicators U08 Smoke Detection System Panel U09 Wing Anti Ice Auto Trip Off and Fire Warning Panel U10 Pneumatic System Panel U11 Pressurization System Panel UO1 DC ELECTRICAL POWER PANEL 1 DC Voltmeter 2 DC Ammeter 3 DC Meters Selector 4 Switch Guard 5 Battery Switch 1 DC Voltmeter Indicates DC voltage of selected source 2 DC Ammeter Indicates DC voltage of selected source 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 70 DO NOT USE FOR FLIGHT 3 DC Meters Selector TR Positions Indicate transformer rectifier current and TR bus voltage BAT Position Indicates battery current and voltage when no AC power on airplane Battery charging shows positive amps 5 Battery Switch ON Battery serves as a back up for battery busses OFF Battery isolated from loads except those on hot batter busses but continues to charge Trips the APU if running U02 ELECTRICAL POWER PANEL 1 2 3 4 J 6 7 8 g 10 11 C GENERATOR ORIVE RALIMG GE J MV ORME CAN BE X Fj el U j PE CHMNECTES px eng che AR i m d Nel Low Lowe Loe T pisconuecr SESE JITILLIT Blot pisconwect EPS rm T2331 1141 1 gt DRIVE TEMPFSATURE gt re RIA ul D dl i li E SERVICE a M d 12 13 14 15 16 1 4 7 Switch Guard 2 5 8 Generator Drive Disconnect Switch 3 6 9
18. J 6 7 8 5 CONTRPL CABIN TT PASSENIER cape AIR MIK VALVE Lip Mik VALVE ik Ic m x Pg F us gt CLIMB l5 lt UP IMO FT PER MI Z DOWN FRE SUH E MFFERALHTIAL Lisit EL FE TARLDTE AMD LANDIHG 113 n f HORN IC uTOGUT 10 11 12 13 14 15 16 17 18 1 9 Control Cabin and Passenger Cabin Duct Overheat Lights 2 8 Control Cabin and Passenger Cabin Temperature Selectors 3 7 Control Cabin and Passenger Cabin Air Mix Valve Indicators 4 Air Temperature Indicator 5 Duct Overheat Reset Switch 6 Air Temperature Selector Switch 10 11 12 13 14 15 16 17 18 Altimeter and Differential Pressure Gauge Rate Decrease Increase Knob Cabin Pressure Control Indicator Barometric Correction Setting Knob Cabin Altitude Knob Cabin Rate of Climb Indicator Altitude Horn Cutout Switch Cabin Pressure Control Mode Selector Knob and Indicator Cargo Door Light amber 1 9 Control Cabin and Passenger Cabin Duct Overheat Lights Amber lights for each air conditioning distribution duct marked DUCT OVERHEAT are on the Second Officer s upper panel These lights will illuminate if the duct temperature exceeds 86 C Simultaneously the respective air mix valve will be driven to the full cold position This trip condition may be reset with the duct overheat reset switch provided the duct temperature has dropped below 88 C 2010 Captain Sim www captainsim com 81 DO NOT USE FOR FLIGHT
19. LOOP Determination of bearing to station is made by manual rotation of the loop antenna until aural null or loss of signal occurs Determined by listening to the signal or observing the tuning meter for minimum needle deflection Best position for audio reception during severe precipitation static P02 P08 FLIGHT DIRECTOR CONTROLS i 2 3 1 Pitch Command Control 2 Autopilot Mode Selector 3 Altitude Hold 3 Altitude Hold Autopilot holds constant airplane altitude if elevator switch engaged Pitch controller is ineffective On APPR AUTO switch trips OFF when glide slope engages 2010 Captain Sim www captainsim com gt 727 Captain FLIGHT MANUAL Part II Aircraft and Sy 54 un ct D Un P04 RADAR CONTROL PANEL RADAR OPERATIONAL CONTROLS 1 2 3 4 3 6 Pd MAK l TILT STAB ie 1 BRT Controls brightness of the indicator display CW rotation for max brightness 2 Wx Selects the Wx weather mode of operation Wx will appear in the lower left of the display Wx colors are Black for no returns Green for weak returns Yellow for moderate returns Red for heavy returns and Magenta for intense returns 3 WxA Selects the WxA weather alert mode of operation WxA will appear in the lower left of the display WxA 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
20. TCAS CONTROL PANEL AFT PEDESTAL PANEL 069 FLIGHT ENGINEER UPPER PANEL 69 UO1 70 U02 71 UO3 73 U04 74 UO5 75 UO6 76 UO7 76 U08 77 UO9 78 U10 80 Uti DC ELECTRICAL POWER PANEL ELECTRICAL POWER PANEL ELECTRICAL POWER PANEL ELECTRICAL POWER PANEL OXYGEN PRESSURE PANEL AFT CABIN ZONE TEMPERATURE CONTROL PANEL START VALVE OPEN LIGHTS SMOKE DETECTION SYSTEM PANEL WING ANTI ICE AUTO TRIP OFF AND FIRE WARNING PANEL PNEUMATIC SYSTEM PANEL PRESSURIZATION SYSTEM PANEL 82 FLIGHT ENGINEER LOWER PANEL 83 WOL 85 W02 86 Wo3 87 Wo4 88 Wo5 88 W07 89 Wo8 90 Wo9 91 W10 93 Wili 94 W12 FUEL SYSTEM PANEL CLOCKS HYDRAULIC BRAKE PANEL ENGINE OIL PANEL S O PANEL LIGHTING CONTROLS DOOR ANNUNCIATOR PANEL AUDIO SELECTOR PANEL FUEL HEAT PANEL HYDRAULIC PANEL OXYGEN PANEL OIL COOLER PANEL 95 SECOND OFFICER S AUXILIARY PANEL 96 P601 97 P602 97 P603 99 P604 100 P605 FUEL DUMP PANEL E L T EMERGENCY LOCATOR TRANSMITTER APU CONTROL PANEL LEADING EDGE DEVICES ANNUNCIATOR PANEL ELECTRICAL SYSTEM FAULT ANNUNCIATOR PANEL 101 CUSTOMER SUPPORT www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 5 DO NOT USE FOR FLIGHT PANELS LAYOUT GLARESHIELD RIGHT FORWARD FLIGHT ENGINEER LEFT FORWARD OVERHEAD CENTER FORWARD 4 SIDE PANEL 2 UPPER PANEL R 3 FLIGHT ENGINEER FORWARD AFT AISLE STAND NW AISLE STAND J LOWER PANEL CONTROL S
21. The indicator will display precharge pressure when the brake hydraulic system is depressurized and will display zero if the precharge pressure is lost When the brake system hydraulic pressure exceeds precharge pressure the indicator will display brake system hydraulic pressure Normal Precharge 1000 PSI Normal Pressure 3000 PSI Maximum Pressure 3500 PSI 2010 Captain Sim www captainsim com 30 DO NOT USE FOR FLIGHT GLARESHIELD PANEL i EJ b o EC r 1 2 3435 6 7 8 91011 12 13 14 15 1 Engine Failure Light 2 Wheel Well Fire Warning Light 3 9 Freon Bottle Discharge Light 4 7 10 Fire Handles 5 8 11 Bottle Discharge Switches 6 Bottle Transfer Selector Switch 12 Fire Test Switch 13 Switch Guard 14 Fire Alarm Bell Cutout Switch 15 Detector Test Button 2 Wheel Well Fire Warning Light A red fire warning light marked WHEEL WELL on the fire control panel will illuminate and the fire alarm bell will sound continuously when a fire or overheat condition exists in either main wheel The same light and bell will also be energized if an overheat condition in the nose wheel well exists When the temperature in the area drops below the alarm level the light and bell will be de energized The bell may also be de energized immediately following a fire or overheat signal by operating the fire alarm bell cutout switch remote control APU fire warning horn cutout switch or APU fire warning TEST RESET switc
22. a chord chime will sound 3 Cabin Attendant Call Switch When an attendant call button is depressed a two stroke chime will sound 4 Cabin Attendant Call Light blue Illuminates and single tone chime sounds in cockpit while captain call switch is pressed at either attendant s panel 5 Ground Crew Call Switch When the ground crew call switch is depressed the horn will sound to alert the ground crew O15 VOICE TAPE RECORDER UNIT 1 2 1 Voice Recorder Monitor Jack 2 Voice Recorder Indicator 3 Voice Recorder Area Microphone 4 Voice Recorder Test Switch 5 Voice Recorder Bulk Erase Switch 017 WINDOW HEAT PANEL 1 2 11 13 Window Heat Switches 1 2 3 5 7 9 Window Power On Lights C E 5 4 6 8 10 Window Overheat Lights az Lj 3 i B 12 Window Heat Test Switch rj 9 B8 10 EN uu rn L 11 12 13 1 2 11 13 Window Heat Switches Four window heat switches on the overhead panel are marked WINDOW HEAT L1 and L2 R1 and R2 Each has ON OFF RESET positions 2010 Captain Sim www captainsim com 46 DO NOT USE FOR FLIGHT In the ON position the following occurs Power is available to the respective window s proportional heat control unit which provides modulated power in building up to and maintaining a window operating temperature power is directed to heat the eyebrow windows No 4 and No 5 on the corresponding side left or right and the overheat monitoring relay unit is energized
23. apply to second windshield until residue is washed off and repellency is established on first windshield Rain repellent may be used any time rain intensity requires the use of windshield wipers When applied in light rain a gel or foam may form when the repellent mixes with water 3 Windshield Wipers Switch Each pilot s No 1 window is provided with an 28V DC DC2 for LI DC1 for RI electric 4 speed windshield wiper The two wipers are separate independent systems with a single 6 position PARK OFF LOW 1 2 3 4 HIGH control switch located on the pilot s overhead panel The PARK position stows the wipers at the bottom of the windshield and is spring loaded to the OFF position The LOW through HIGH positions select the speed of the wipers 4 Emergency Exit Lights Unarmed Light An amber light marked EMERGENCY EXIT LIGHTS UNARMED on the overhead panel will be on when the emergency exit lights switch is either in the ON or OFF positions provided the battery switch is on 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 43 DO NOT USE FOR FLIGHT O12 ENGINE START PANEL 1 Continuous Ignition Switch 2 4 6 8 Switch Guards 3 Engine Access Door Light 5 7 9 Engine Start Switches 4 J3 6 7 8 9 1 Continuous Ignition Switch Provides low energy ignition for conditions requiring continuous ignition such as icing conditions or periods of moderate or greater turbulence 5 7 9 En
24. can be lifted over the 0 detent Friction holds the speedbrake lever in any other position on the scale 2010 Captain Sim www captainsim com 63 DO NOT USE FOR FLIGHT The speedbrake lever positions the spoiler mixer ratio changer and ground spoiler control valve through a rod and cable arrangement The spoiler mixer positions the flight spoilers according to inputs received from the speedbrake lever and the roll control system 2 4 7 Thrust Levers Control engine forward thrust The thrust levers can only be advanced if the reverse thrust levers are down 3 5 7 Reverse Thrust Levers Each throttle has an additional handle which is used to actuate the thrust reversers The reverse thrust lever pivots about a point near the top of the throttle If reverse thrust is required the throttle must be retarded to IDLE and then the reverse thrust lever must be pulled up Further aft movement of the lever will increase reverse thrust 8 Flap Lever The lever controls both inboard and outboard flap hydraulic drive units Detents are provided at the flap up 09 2 5 15 25 30 and 40 positions on the flap quadrant adjacent to the lever Gates which interrupt flap lever travel are at the 29 and 25 positions 10 23 Stabilizer Trim Indicators A stabilizer trim indicator and pointer adjacent to each manual trim wheel is calibrated to indicate full stabilizer travel from 2 5 units airplane nose down to 12 5 units airplane
25. engaged the aircraft will turn to the heading selected by the heading cursor on the Captain s course indicator If the turn and pitch controller is turned the heading select switch will automatically switch to off With the mode selector in NAV LOC AUTO G S or MAN G S and the heading select switch engaged HDG SEL the autopilot will turn to or retain the heading selected by the heading selector on the Captain s CI until either the VOR radial or the localizer course selected on the Captain s CI is captured At that time the heading select switch will automatically switch to off In the NAV LOC position the autopilot will maneuver the airplane to capture and track correcting for wind a localizer course or a VOR radial as selected on the course arrow of the Captain s course indicator In the AUTO GS position the autopilot will track a localizer until the glideslope is intercepted whereupon the glideslope will be captured and both the localizer and glideslope will be tracked for a COUPLED ILS approach Altitude hold will function in this mode until the glideslope is captured If MAN G s is selected some distance from the glideslope the airplane will pitch down to establish the 700 feet minute rate of descent then if the glideslope is above the airplane will pitch up the maximum amount to capture the glideslope from below 2 Autopilot Turn and Pitch Controller The autopilot turn and pitch controller is on the aft electronic control panel
26. 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 transmitting 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
27. mode is selected magenta areas of storms flash between magenta and black at a 1 HZ rate 4 9 RANGE Clears the display and advances the indicator to the next range The upper button increases range the lower button decreases it The radar display ranges are 5 10 20 40 80 160 240 320 The selected range is displayed in the upper right corner of the display with the range ring distance displayed along the right edge 2010 Captain Sim www captainsim com 5 STAB DO NOT USE FOR FLIGHT 55 The On position provides normal stabilization The Off position disables and the stabilization antenna tilt angle is controlled by the tilt control only 6 GAIN The gain knob adjusts the radar gain from 0 to 20 dB CCW rotation reduces gain 7 Radar Mode Selector 2010 Captain Sim www captainsim com Note To select mode click the corresponding inscription shown as outlined red on the Weather Radar panel screenshot above ON 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 d
28. proper functioning 4 AC Voltmeter Indicates voltage as selected 5 Frequency Indicator Indicates frequency as selected 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 74 DO NOT USE FOR FLIGHT 6 KVARS Switch Changes U03 ELECTRICAL SYSTEM PANEL Power Meters indication from real KW to reactive KVAR load display 7 8 Synchronizing Lights Clear Connected between the bus tie and the position of the AC meters selector Blink rate is proportional to frequency differences 9 AC Meters Selector Selects source of AC power to be monitored on AC voltmeter and frequency indicator UO5 OXYGEN PRESSURE PANEL 1 Flight Crew Oxygen Pressure Indicator 2 Passenger Oxygen Pressure Indicator 3 Passenger Oxygen Switch 4 Oxygen Pressure Indicating Light NS mme 2 p PASSENGER TER KG NOR 7 Y TL ry i ae 1 Flight Crew Oxygen Pressure Indicator This indicator marked OXYGEN SYSTEM CREW is on the Second Officer s upper panel The indicator is scaled 0 20 0 2000 PSI and indicates pressure in the cylinder and or line The pressure transmitter for this indicator is located downstream of the oxygen cylinder shutoff valve and is common to the indicator on the external charging panel Electrical power is necessary for proper indication 2 Passenger Oxygen Pressure Indicator This indicator marked OXYGEN SYSTEM PASSENGER is on the Second Offic
29. short of a skidding wheel An electronically controlled anti skid control valve for each main wheel continuously varies individual brake pressure in response to wheel action Maximum braking is produced under any variety of runway condition The anti skid system consists of individual wheel speed sensors an antiskid control shield and two dual anti skid control valves The system also includes a test circuit and indicators which allow the system to be checked for proper operation in flight or on the ground 1 Anti Skid Test Switch This switch on the overhead panel marked ANTI SKID TEST can be used to test the anti skid system with or without the parking brake on The switch has momentary INBD amp NOSE and OUTBD amp NOSE positions and is spring loaded to the neutral position INBOARD amp NOSE Inb and nose indicators blank Outboard indicators rel OUTBOARD amp NOSE Outb amp nose indicators blank Inboard indicators rel An AC signal similar to the signal generated by a rotating wheel can be introduced by the test switch into the anti skid control module When the wheels are not rotating and the anti skid system is armed this simulated rotation of the wheels selected by the anti skid test switch will make brakes available on those wheels The corresponding brake released indicators will show blanks The remaining wheels not selected by the test switch position will give a wheel not rotating signal to the control mod
30. the middle when both zone control valves are closed When the aft zone is selected warmer the aft zone control valve opens and the pointer will be to the right 3 Aft Cabin Zone Temperature Switch This spring loaded to neutral switch on the Second Officer s upper panel has momentary COOLER and WARMER positions The switch is used to balance the aft cabin temperature With the switch in the COOLER position the forward zone heat valve will open With the switch in the WARMER position the aft zone heat valve will open 4 Aft Cabin Zone Overheat Light This amber light will illuminate when the temperature in either forward or aft conditioned air supply duct becomes excessive 190 C driving the appropriate zone control valve closed 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 76 DO NOT USE FOR FLIGHT U07 START VALVE OPEN LIGHTS 1 3 Start Valve Open Lights amber 1 3 Start Valve Open Lights amber An engine START VALVE OPEN light is on the Second Officer s lower panel directly above the door annunciator panel The purpose of the light is to provide the flight crew with indication of start valve position The three 3 lights are connected individually to each start valve The appropriate light will be illuminated when the start valve is open A placard under each light states START VALVE OPEN U08 SMOKE DETECTION SYSTEM PANEL 1 7 Smoke Detection System 1
31. 2 3 4 5 amp 7 IL dL HET es es 8 9 Secondary Main Landing Gear Position SMIOKIE OIE DIE GEN GL Indicator Lights green on OFF Az Ah Ah 9 89 10 v A 5 a PUSH To TEST SECONDARY MAIN LANDING GEAR POSITION T L4 INDICATOR e EFT DOWN AND LOCKED proper B8 9 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems T1 DO NOT USE FOR FLIGHT 1 3 Strut and Lower Aft Body Overheat Lights 4 Wing Anti Ice Auto Trip Off Switch 5 Wing Anti Ice Auto Trip Off Light Amber 6 Overheat Test Switch 1 3 Strut and Lower Aft Body Overheat Lights Three amber lights will illuminate when overheat conditions exceeding approximately 204 C in the strut or 124 C in a keel beams area and lower aft section aft cargo and rear entry stairs are detected 4 Wing Anti Ice Auto Trip Off Switch Since a portion of the wing anti ice ducting is located in the pressurized area of the aircraft a rupture in that area would cause a rapid increase in cabin pressure This procedure rise would cause the Wing Anti Ice Auto Trip Off system to close the wing anti ice valves halting the pressure rise Pressurization air could then enter the ruptured duct and flow overboard through the wing ducting causing a proportional decrease in cabin pressure After a trip off or system test the system can only be reset on the ground This system can be tested on the ground by the S O by p
32. 3000 Hz signal 2 Middle Marker Light Amber Illuminates flashing when over ILS middle marker beacon 1300 Hz signal 3 Outer Marker Light Blue Illuminates flashing when over ILS outer marker beacon 400 Hz signal C04 STANDBY ARTIFICIAL HORIZON 1 Bank Indicator 2 Symbolic Airplane 3 Pitch Trim and Gyro Caging Control 1 Bank Indicator Indicates airplane bank angle in degrees 2 Symbolic Airplane Reference bars provide attitude reference 3 Pitch Trim and Gyro Caging Control CONTROL IN Rotate to adjust airplane symbol CONTROL OUT Momentary Erects horizon 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 22 DO NOT USE FOR FLIGHT CO5 ANNUNCIATORS 1 Stabilizer Out of Trim Light 2 Elevator Low Pressure Annunciators 1 Stabilizer Out of Trim Light A light on the center panel will illuminate when autopilot inputs to the elevator are not trimmed out by the stabilizer 2 Elevator Low Pressure Annunciator Illuminates when system A or B hydraulic pressure to the elevator power unit is low or the system A or system B elevator switch is in the OFF position C06 CONTROLS POSITION INDICATORS 1 2 3 Controls Position Indicator Show positions of left 2 and right 3 elevators and upper and lower 1 rudders when airplane power is on the bus LIER Ny 2 s Ao nz 3 LER MJQ 2010 Captain Sim www captain
33. 4 6 12 14 16 23 29 Fuel Boost Pump Low Pressure Light Amber Indicates low boost pump discharge pressure from respective pump 3 9 15 Tank Quantity Indicator Individual indicators for each tank are on the S O panel Individual indicator s are installed at the fueling station These indicators are calibrated to depict pounds of usable fuel in tanks The indicators on the S O panel operate on airplane external or APU power The fuel quantity indicators at the refueling panel operate on external or APU power only and require the POWER switch be in the ON position 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 85 DO NOT USE FOR FLIGHT 18 26 30 Fuel Tank Quantity Indicators Test Switch Respective quantity indicator drives toward zero Drives fueling station indicator pointer up the scale Pointer returns to original position after switch released 19 24 34 Fuel Crossfeed Manifold Valve in Transit Light Blue ON during respective valve transit OUT after valve attains new position 20 25 31 Fuel Crossfeed Manifold Valve Switch Switch shown closed Bar align with fuel flow line when open OPEN opens valve to crossfeed manifold to supply fuel to other engines from respective tank 21 27 32 Engine Fuel Shutoff Valve Switch Operates respective engine fuel shutoff valve Must be open for engine operation valve overrides closed when respective engine fire switch pulled or e
34. 8 12 14 19 21 26 29 Amber Leading Edge Flap Slat Light 15 Leading Edge Devices Annunciator Switch This panel contains 14 amber lights one for each leading edge flap or slat 14 green lights and a switch The switch has POSITION TEST OFF LIGHT TEST positions and is spring loaded to the OFF position All lights should illuminate when the switch is in the LIGHT TEST position When the switch is in the POSITION TEST position a green light indicates that the corresponding leading edge device is extended An amber light indicates the IN TRANSIT position and no light indicates the retracted position of the corresponding leading edge flap or slat When the switch is in the OFF position all lights are out 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 10 DO NOT USE FOR FLIGHT P605 ELECTRICAL SYSTEM FAULT ANNUNCIATOR PANEL 1 26 Annunciator Lights 1 9 10 18 19 27 27 APU Crank Annunciator Circuit Breaker m 28 Reset Switch LIN MAN 29 Test Switch Wim wg em ar vililla IBN 2H 29 1 27 Annunciator Lights APU Crank Light During APU starts illumination of this light indicates starter operation This light illuminates when a start is initiated and goes out when the starter motor is de energized At approximately 35 of governed speed 28 Reset Switch Used to extinguish an annunciator light and reset annunciator system after a fault has b
35. Aircraft and Systems 93 DO NOT USE FOR FLIGHT 19 System B Pressure Gauge This electrical gauge on the S O lower panel indicates hydraulic system pressure or accumulator preload depending on whether or not system B is pressurized The gauge will read ZERO if accumulator preload is lost regardless of actual hydraulic p assure 20 System B Overheat Light The light will illuminate 1049C when system A return fluid temperature is excessive extinguishes at 749C 21 System B Quantity Indicator System B quantity indicator is on the S O lower panel Normal reading is 1 8 gallons F No quantity indication is provided for the hydraulic fluid in the auxiliary reservoir The system B main and auxiliary reservoirs will be maintained at the full level when the system A hydraulic quantity indicator indicates above 2 5 gallons The essential DC bus supplies electric power for quantity gauges 22 Standby Hydraulic System Quantity Indicator 1 0 52 US gal full 2 0 2 8 US gal minimum dispatch quantity 1 Oxygen Emergency Lever 2 Oxygen Diluter Lever 3 Oxygen Flow Indicator 4 Oxygen Supply Lever 5 Oxygen Mask MIC Switch 6 Switch Guard 7 MIC Oxygen Switch 2 6 7 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 94 DO NOT USE FOR FLIGHT W12 OIL COOLER PANEL 1 Oil Cooler Selector Switch CSD 2 3 No Equipment Cooling Light Amber 4 Rudder Load Limiter Li
36. Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 42 DO NOT USE FOR FLIGHT 011 WINDSHIELD WIPERS AND RAIN REPELLENT PANEL RAIN E 1 2 Rain Repellent Switches REPELLENT aen 3 Windshield Wipers Switch um EX om den LEFT I 4 Emergency Exit Lights Unarmed Light WINDSHIELD W FER Nn T FAF 5 Switch Guard 2 E 6 Emergency Exit Lights Switch ET HI EMERGENCY EXIE LIGHTS DHARM O 1 2 Rain Repellent Switches A rain repellent system is provided to be used in conjunction with the windshield wiper system to improve visibility during heavy rain When actuated the system sprays a predetermined amount of repellent solution on the Captain s or First Officer s No 1 window as selected The solution is spread on the windows by rain water flowing over the solution and action of the wiper blades This provides the windows with a water repellent coating Two push button type switches marked RAIN REPELLENT LEFT RIGHT are on the overhead panel Each switch actuates a solenoid valve controlled by a time delay circuit which controls the flow of repellent fluid to the spray nozzles at the base of each windshield wiper The switch must be depressed momentarily for the full measured flow of repellent fluid to be applied The switch then must be released to allow the time delay circuit to reset before another application can be obtained Note Apply to one windshield at a time Do not
37. DO NOT USE FOR FLIGHT 727 Captain FLIGHT MANUAL PART II Aircraft and Systems DO NOT USE FOR FLIGHT ABOUT THIS MANUAL VERSION 23 FEBRUARY 2010 WARNING THIS MANUAL IS DESIGNED FOR MICROSOFT FSX USE ONLY DO NOT USE FOR FLIGHT The 727 Captain FLIGHT MANUAL is organized into three Parts Each Part is provided as a separate Acrobat PDF document e Part I User s Manual e Part II Aircraft and Systems this document e Part III Operations Adobe Acrobat Reader Required FOR GENERAL INFORMATION ON THE 727 CAPTAIN PRODUCT PLEASE USE WWW CAPTAINSIM COM THIS MANUAL PROVIDES ADDITIONAL INFORMATION ONLY WHICH IS NOT AVAILABLE ON THE WEB SITE www captainsim com DO NOT USE FOR FLIGHT 727 100 PRO PACK FLIGHT MANUAL Page S PANELS LAYOUT 6 LEFT FORWARD PANEL 7 LO1 MACHMETER INDICATOR 7 L02 CLOCKS 8 L03 AUTOPILOT DISENGAGED WARNING LIGHT 9 L04 AIRSPEED INDICATOR 9 LO5 RADIO MAGNETIC INDICATOR RMI 10 LO6 ANNUNCIATORS 11 LO7 ATTITUDE DIRECTOR INDICATOR ADI 12 LO8 HORIZON SITUATION INDICATOR HSI 14 LO9 ANNUNCIATORS 15 L10 STANDBY ALTIMETER 15 L11 VERTICAL SPEED INDICATOR 16 L12 PNEUMATIC BRAKE LEVER 16 L13 RA HEIGHT INDICATOR 17 L14 ELECTRIC ALTIMETER 18 L15 DME INDICATOR AND WINDSHEAR AHEAD LIGHTS P19 CENTER FORWARD PANEL S 20 C01 LIGHTS TEST MARKER 20 C02 ALTITUDE ALERTING PANEL 21 C03 MARKER LIGHTS 21 C04 STANDBY ARTIFICIAL HORIZON 22 C05 ANN
38. NBD and OUTBD have UP OFF DN positions and are spring loaded from the DN position to the OFF position When either alternate flap switch is in the DN position the corresponding trailing edge flaps extend electrically and the leading edge flaps standby drive shutoff valve will open causing all leading edge flaps and slats to extend When the alternate flap switches move from the DN position to the OFF position the leading edge flaps and slats will continue to extend or remain extended as long as the alternate flaps master switch is in the ON position The trailing edge flaps will stop When the alternate flap switches are in the UP position with the leading edge flaps and slats extended and the alternate flaps master switch in the ON position the leading edge flaps and slats will remain extended and the corresponding trailing edge flaps will retract The leading edge flaps and slats cannot be retracted using the alternate flap system 014 CABIN CALL PANEL 1 2 4 1 No Smoking Switch 2 Fasten Seat Belts Switch 3 Cabin Attendant Call Switch 4 Cabin Attendant Call Light blue 5 Ground Crew Call Switch 1 No Smoking Switch A switch marked NO SMOKING with ON OFF positions 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 45 DO NOT USE FOR FLIGHT 2 Fasten Seat Belts Switch A switch marked FASTEN SEAT BELTS with ON OFF positions With this switch in the ON position
39. NG 2 ENG 3 are on the Second Officer s lower panel When the fuel heat switch is placed in the ON position the light will illuminate bright while the valve is in transit then dim when the valve is fully open When the fuel heat switch is placed to the OFF position the light illuminates bright while the valve is in transit then extinguishes when the valve is fully closed On some aircraft a green light illuminates when the fuel heat valve is open There is no transit function On some aircraft a blue light illuminates when the fuel heat valve is in transit The light is extinguished when the valve position agrees with the selected switch position 2 4 6 Fuel Icing Caution Light These amber lights marked FUEL HEAT ICING ENQ 1 ENQ 2 ENQ 3 are on the Second Officer s lower panel The light is controlled by a differential pressure switch located by the fuel filter The switch closes at a differential pressure of 5 PSI illuminating the light and opens at 3 PSI extinguishing the light 7 8 9 Fuel Heat Switch These switches marked FUEL HEAT ENG I ENG 2 ENG 3 with ON OFF positions are on the Second Officer s lower panel With the switch in the ON position the hot air valve of the fuel heater is opened permitting the flow of the 13th stage bleed air through the fuel heater Positive indicators of fuel heat application will be a drop in EPR of approximately 03 and a rise in engine oil temperature 10 Z1 Tank Fuel Temperature Indicator
40. Power is also applied to the perimeter heat circuit on the No 1 and No 2 windows In the OFF RESET position the heat control system is de energized or in the event of an overheat condition the overheat light is turned out and the system is reset for operation Perimeter heat is applied to the L and R windshields to prevent delamination and is activated by the L 1 and R 1 window heat switches To deactivate the perimeter heaters pull the associated L or R 4 and 5 eyebrow circuit breakers on the P6 1 panel Perimeter heat is currently being incorporated for both the L 2 and R 2 sliding windows It will be controlled by the L 2 and R 2 window heat switches 3 5 7 9 Window Power On Lights Four lights green marked on are adjacent to the window heat switches Each light will illuminate when power is available to the respective heat control unit and its output exceed 5 watts 4 6 8 10 Window Overheat Lights Four overheat indicating lights amber marked OVERHEAT are directly below each power on light The overheat light will illuminate when the heat control unit is directing power to its respective window and the window temperature is excessive All lights are push to test type 12 Window Heat Test Switch A switch on the overheat panel has momentary POWER ON TEST OVERHEAT TEST and center OFF positions Both test positions require the window heat switches to be on In POWER ON TEST the temperature controller s power output is verif
41. S rest TUS RECORDER unc este vi S 2 Flight Recorder Test Switch The purpose of the flight recorder is to provide continuous recording of airspeed acceleration altitude time and heading It also receives data from which the time of each radio transmission from aircraft to ground station can be determined The recorder is operating any time electrical power is being supplied by the ship s generators An underwater beacon is installed to assist in locating the flight recorder under water 1 Flight Recorder Light An amber colored light marked OFF is on the overhead panel When illuminated the light indicates power failure to the recorder or that the recording tape is broken Extinguished recorder it operating either automatically or during test 2 Flight Recorder Test Switch With this switch marked TEST on the overhead panel actuated the flight recorder can be operated on external or APU power as evidenced by an extinguished flight recorder light while the test switch is closed If the flight recorder light does not illuminate after the flight recorder test switch has been depressed it indicates that the flight recorder tape is satisfactory 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 4 DO NOT USE FOR FLIGHT 009 COMPASS MODE PANEL 1 3 Switch Guard 2 4 Compass System Switch 010 FLOOD LIGHT Flood Light 1 Red 2 White 2010
42. SSURE or FILTER BYPASS are on the pilot s center panel These lights provide an indication at the pilot s station to supplement the oil pressure indicators at the S O s panel Normally the light should extinguish during engine start When this light is illuminated and oil pressure indication normal a clogging main oil filter should be suspected The incident should be reported as an engine discrepancy This light illuminates at 35 1 PSI when pressure is decreasing and goes out at 36 5 1 PSI when pressure is increasing 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 26 DO NOT USE FOR FLIGHT C10 LANDING GEAR CONTROL PANEL 1 7 Landing Gear Lights 8 Landing Gear Lever Le oca FT aes IB ISL 1ft deum ILE ipw ILLI AL ne marg DIT fa sj sekk u e FT 1 7 Landing Gear Lights Three red lights marked L GEAR N GEAR and R GEAR will illuminate when the corresponding gear is not locked in the position as selected by the landing gear lever or when any engine thrust lever is retarded with the landing gear Three green lights marked L GEAR N GEAR and R GEAR illuminate when the corresponding gear is down and locked A red warning light will illuminate when any of the main gear doors or forward nose gear doors are not up and locked 8 Landing Gear Lever The landing gear lever is on the pilot s center panel and has UP OFF DN positions A placard below the lever indi
43. TAND Po PANEL arm mmn ed arr ee Lg L a m gt dg RE er E ur ms um pru d acm mew s re 2m Spe Bos Rd rome Burman ee oo m L i EL w anis CD NES ET TE n tonne E s Wa de en 2010 Captain Sim 727 Captain FLIGHT MANUAL Part II Aircraft and Systems DO NOT USE FOR FLIGHT LEFT FORWARD PANEL LO1 Machmeter Indicator LO2 Clocks LO3 Autopilot Disengaged Warning Light LO4 Airspeed Indicator L05 Radio Magnetic Indicator RMI LO3 06 09 Annunciators LO7 Attitude Director Indicator ADI LO8 Horizontal Situation Indicator HSI L10 Standby Altimeter L11 Vertical Speed Indicator L12 Pneumatic Brake Lever L13 Height Indicator L14 Electric Altimeter L15 DME Indicator and Windshear Ahead Lights 2010 Captain Sim www captainsim com 0000000000000 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 7 DO NOT USE FOR FLIGHT LO1 MACHMETER INDICATOR 1 1 Mach Pointer 2 Mach Limitation Mark The airspeed indicator and the mach meter are separate indicators and they are pitot static operated pneumatic There is no standby mach airspeed indicator installed when only pneumatic instruments are installed LO2 CLOCKS 1 Elapsed Time Hours Minutes Hands 2 4 Hours And Minute Hands 3 Elapsed Time Switch 5 Winding amp Setting Control 6 Lower Minute Register Hand 7 Sweep Second Hand 8 Push Button 1 Elapsed Time Hours Minutes Hands C
44. TION 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 www captainsim com 59 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 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 e Avoid cells c
45. The time delay between the illumination of the wheel wells fire warning light and the 4 engine fire warning lights is determined by the time necessary to heat the sensor responder to the warning temperature Caution When testing the engine or engine firewall fire detection system minimize duration of fire test switch operation The test should be stopped when all engine fire warning lights illuminate Test time should not exceed 60 seconds per each test position On some aircraft the response is immediate when tested A fault in the system will be indicated by illumination of the amber fault light on the S O auxiliary panel A fault on the B side of the system will be indicated at any time A fault on the A side is only indicated immediately after a test of the system 14 Fire Alarm Bell Cutout Switch Will silence the bell and horn and will change the flashing red light on the APU remote control panel to a steady light The lights will remain illuminated as long as the fire condition exists 15 Detector Test Button When pressed performs a continuity test of the firewall engine and the wheel wall fire detectors and the detector circuit ground lights www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems OVERHEAD PANEL O01 O02 O03 O04 O05 O06 O07 O08 O09 O10 LENER ZEEN PPG Pa eri Ge Sp gt grt Hydraulic Power System Yaw Damper Switches Flight Control Warning Test Switc
46. The controller will rotate to right or left for right or left bank control and is provided with forward and aft movement for nose down or nose up pitch control The controller provides for turn control when the autopilot is in the MAN position only Pitch control is provided when the mode selector is in any position except AUTO G s or MAN G s after glideslope capture 2010 Captain Sim www captainsim com 66 DO NOT USE FOR FLIGHT When the autopilot altitude hold switch is in the ALT HOLD position the pitch controller is de energized 3 Autopilot Aileron Switch This switch marked AIL with ENGAGED DISENGAGED The switch is spring loaded to the DISENGAGED position and will be magnetically held in the ENGAGED position only when the roll axis interlock circuits are satisfied When this switch is in the ENGAGED position the autopilot will control the airplane about its roll axis from signals received from the vertical gyro the autopilot turn and pitch controller or from navigational facilities as selected by the autopilot mode selector Note To engage the aileron switch at least one yaw damper switch must be engaged 4 Autopilot Elevator Switch A switch marked ELEV with ENGAGED DISENGAGED positions This switch like the autopilot aileron switch is spring loaded to the DISENGAGED position and will be magnetically held in the ENGAGED position only when the pitch axis interlock circuits are satisfied When these circuits are comp
47. The fuel temperature in 1 tank is displayed on an indicator installed on the Second Officer s panel The indicator dial has a scale range of 56 C to 56 C 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 91 DO NOT USE FOR FLIGHT W10 HYDRAULIC PANEL 1 2 3 4 3 5 7 8 9 10 11 12 13 14 A LI JID SHUTOFF V PEH hese d F a r 15 16 17 18 19 20 21 22 1 3 System A Pump Switches 15 System A Pressure Gauge 2 4 System A Pump Low Pressure Lights 16 System A Overheat Light 5 7 System A Fluid Shutoff Switch 17 System A Quantity Indicators 6 8 Switch Guard 18 Ground Interconnect Switch 9 11 System B Pump Switches 19 System B Pressure Gauge 10 12 System B Pump Low Pressure Lights 20 System B Overheat Light 13 Standby System Overheat Light 21 System B Quantity Indicator 14 Standby System Light 22 Standby Hydraulic System Quantity Indicator 1 3 System A Pump Switches Two switches on the S O lower panel have ON OFF positions In the OFF position a solenoid will be energized to block the pump output and depressurize the pump 2 4 System A Pump Low Pressure Lights Two amber lights marked ENG 1 PUMP ENG 2 PUMP LOW PRESS are on the S O lower panel A pressure switch in each pump output line operates the lights The light will illuminate when the corresponding pump output pressure is insufficient or when the applicable pump is off 5 7 System A Flu
48. UNCIATORS 22 C06 CONTROLS POSITION INDICATORS 23 C07 ENGINE INSTRUMENT PANEL 24 C08 FLAPS INDICATORS MASTER WARNING 25 C09 LOW OIL PRESSURE OIL FILTER BYPASS CAUTION LIGHT 26 C10 LANDING GEAR CONTROL PANEL 28 RO1 LOW PRESSURE ANNUNCIATORS 29 RO6 BRAKE PRESSURE INDICATORS KE TK GLARESHIELD PANEL EK OVERHEAD PANEL 33 O01 HYDRAULIC POWER SYSTEM 34 O02 YAW DAMPER SWITCHES 34 O03 FLIGHT CONTROL WARNING TEST SWITCH 35 004 ANTI SKID CONTROL PANEL 36 005 INTERIOR LIGHTING PANEL 38 O06 EXTERIOR LIGHTING PANEL 39 O07 STALL WARNING SYSTEM 40 008 FLIGHT RECORDER 41 009 COMPASS MODE PANEL 41 010 FLOOD LIGHT 42 011 WINDSHIELD WIPERS AND RAIN REPELLENT PANEL 43 012 ENGINE START PANEL 44 013 ALTERNATE FLAPS PANEL www captainsim com 44 O14 45 O15 45 O17 47 O18 48 O19 49 O20 50 O21 DO NOT USE FOR FLIGHT CABIN CALL PANEL VOICE TAPE RECORDER UNIT WINDOW HEAT PANEL ANTI ICE PANEL WING ENGINE AND COWL ANTI ICING PANEL PITOT STATIC HEAT PANEL STANDBY MAGNETIC COMPASS ENTE AISLE STAND 52 PO1 P07 ADF CONTROL PANEL 53 P02 P08 FLIGHT DIRECTOR CONTROLS 54 P04 RADAR CONTROL PANEL 54 RADAR OPERATIONAL CONTROLS 56 THEORY OF OPERATION 57 PREFLIGHT PROCEDURES 58 OPERATION IN FLIGHT GENERAL 61 P0O5 WINDSHEAR FAILURE LIGHT 61 P0O6 FLAP POSITION SWITCH 62 P0O9 CONTROL STAND 64 P10 P11 VHF NAV COMM CONTROL PANEL 65 P12 AUTOPILOT PANEL 67 P135 68 P14 TRANSPONDER
49. VE bort 3 12 20 Bus Tie Breaker Switch fe 4 13 23 Generator Breaker Light Amber 2 an 5 14 22 Generator Breaker Switch 21 E 13 6 15 25 Generator Field Light Amber 14 4 7 16 24 Generator Field Switch 22 5 xu 8 17 26 Power Meter 16 9 18 27 Frequency Control Knob 6 24 ou 7 17 26 18 5 of 2 11 21 Bus Tie Breaker Lights Amber ON Bus tie breaker open and generator operating isolated 3 12 20 Bus Tie Breaker Switches Open circuit between respective A C bus and bus tie Automatically trips due to excitation faults or overload if respective generator breaker is closed A phase unbalance on the bus tie will trip all bus tie breakers 4 13 23 Generator Breaker Lights Amber ON Generator breaker open and generator disconnected from load bus 2010 Captain Sim www captainsim com 12 DO NOT USE FOR FLIGHT 5 14 22 Generator Breaker Switches Open circuit between respective generator and A C bus Automatically trips due to generator drive speed faults if the drive is disconnected or if the generator field is off Trips on engine shutdown Closing a generator breaker trips the external power contactor or the APU generator breaker 6 15 25 Generator Field Lights Amber ON Generator field relay open and generator field deenergized Generator electrically inoperative and essential power not available from this source 7 16 24 Generator Field Switches Turn off generator field Automatically trips due to
50. al fuel flow rate during engine starts of approximately 1000 pph and 3200 during cruise C08 FLAPS INDICATORS MASTER WARNING 1 Master Warning Light Flashing Red 2 5 Flap Position Indicators 3 4 Leading Edge Flap Lights 1 Master Warning Light Flashing Red On when essential ac bus not energized Push extinguishes light on center panel Will not extinguish power failure warning light on third Crewman s upper panel 2 5 Flap Position Indicators Two dual flap position indicators on the pilots center panel are marked OUTBD and INBD respectively 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 25 DO NOT USE FOR FLIGHT Two needles in each indicator marked L and R indicate corresponding flap positions White bands indicate maximum allowable needle deviation at each flap position 3 4 Leading Edge Flap Lights AMBER ILLUMINATED Any leading edge device in transit At flap lever position 2 leading edge devices 2 3 6 or 7 not extended GREEN ILLUMINATED At flap lever position 2 slats 2 amp 3 6 amp 7 fully extended At any other flap lever position all leading edge Haps and slats fully extended No Lights All leading edge flaps and slats retracted C09 LOW OIL PRESSURE OIL FILTER BYPASS CAUTION LIGHT 1 2 3 Low Oil Pressure Oil Filter Bypass Caution Lights Eri cut PEELA Cor FILTER BYPASS Three amber lights labeled LOW OIL PRE
51. alve switch in the CLOSE position fuel is stopped from dumping and held under pressure in the fueling dumping manifold Note The fuel dump panel cover is constructed such that it cannot be closed unless all the fuel dump valve and dump nozzle valve switches are in the CLOSE position 10 11 Fuel Dump Nozzle Valve In Transit Light Blue A valve in transit light will illuminate when the corresponding switch is actuated and remains on until the valve reaches the full open or close positions as selected 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 97 DO NOT USE FOR FLIGHT P602 E L T EMERGENCY LOCATOR TRANSMITTER 1 E L T Emergency Locator Transmitter Control Switch 2 LED Light 2 LED Light The red LED will illuminate if the switch is turned to on or if the E L T is triggered from an impact P603 APU CONTROL PANEL CAUTION CLEAR REVERSERS E 2 APU Generator Breaker Light BEFORE STARTING APU TER 3 APU Generator Field Light E MAP a T am EH 4 Fire Switch ee ds 1 APU Master Switch M ota m gt 2 5 APU Generator Breaker Switch y di i OPEM THIF 6 Bottle Discharge Switch FIELD cose rw PN fal 7 APU Generator Field Switch qe M on TE 8 Auto Fire Shutdown Arming Switch 2 5 AEMED i PE 9 Switch Guard fa Tova 10 Fire Warning Test Reset Switch 11 APU Ammeter 12 APU Exhaust Gas Temperature Indicator
52. cates limit speeds for landing gear extending retracting and extended The landing gear lever operates the hydraulic landing gear selector valve through a control cable arrangement In the UP position the landing gear lever in addition to retracting the landing gear also causes retraction of the tailskid and automatically applies all wheel brakes The tailskid will extend when the landing gear lever is in the DN down position 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 21 DO NOT USE FOR FLIGHT RIGHT FORWARD PANEL RO1 Airspeed Machmeter Indicator RO2 06 09 Annunciators R03 Autopilot Disengaged Warning Light R04 Mach Airspeed Indicator RO5 Radio Magnetic Indicator RMI RO7 Attitude Director Indicator ADI RO8 Horizontal Situation Indicator HSI R10 Standby Altimeter R11 Vertical Speed Indicator R12 Brake Pressure Indicators R13 Radio Altimeter R14 Marker Lights R15 DME Windshear 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 28 DO NOT USE FOR FLIGHT R02 LOW PRESSURE ANNUNCIATORS 1 2 Aileron Low Pressure Annunciators a 2 5 Rudder Low Pressure Annunciators 1 0 c 4 MER 3 6 Elevator Low Pressure Annunciators D 5 1 2 Aileron Low Pressure Annunciators Two amber annunciators on the First Officer s panel will read AILERON SYSTEM A and AILERON SYSTEM
53. d EPR value when the knob is pulled out to the manual position The EPR set reference index is automatically set by the PDCS unit when the EPR set knob is pushed into the automatic position 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 24 DO NOT USE FOR FLIGHT 16 18 N1 Tachometers Indicate RPM of the low pressure compressor Small dial is graduated in 1 increments marked from 0 9 1 Large dial is graduated in 2 increments marked every 10 from 0 100 Tachometer systems are self generating 19 21 Engine Exhaust Gas Temperature Indicators Three engine exhaust gas temperature indicators calibrated in degrees centigrade indicate temperature of the exhaust gases of each engine in the turbine exhaust case On most aircraft these indicators are self powered On other aircraft the EGT indicators are of an improved response type and utilize the 115 volt AC standby bus as a power source 22 24 N2 Tachometers Indicate RPM of the high pressure compressor Small dial is graduated in 1 increments marked from 0 9 Large dial is graduated 2 increments marked every 10 from 0 100 Tachometer systems are self generating 25 27 Engine Fuel Flow Indicators The engine fuel flow indicators provide a visual indication of the fuel consumption rate for each engine Power for these indicators is from the 115V AC2 and from the 28V DC2 bus The indicators are very accurate up to 6000 pph with norm
54. d 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 ability to quickly identify significant weather follow these steps 1 Select the Wx weather mode of operation Adjust Brightness control as desired 2 Select the 50 or 80 nm range 3 Adjust the antenna tilt to watch the strongest returns seen on the display TARGET RESOLU
55. dows ALI s JP j Kd s 0900 0990 A f Pa 4 b NY m OO OU 3 Barometric Setting Control 1 Digital Display Shows altitude in increments of 100 ft 2 100 Foot Pointer Displays attitude in 100 foot Increment smallest division equals 20 feet One full rotation of pointer equals 1000 feet 3 Barometric Setting Control Rotation of the control adjusts the barometric setting on the inches of mercury in HG indicator 4 5 Altimeter Setting Windows Can be set in millibars or inches Hg L11 VERTICAL SPEED INDICATOR 1 Vertical Speed Pointer Two vertical speed indicators are used on the airplane one located on the Captain s panel and the other on the First Officer s instrument panel Each indicator operates from the airplane static pressure system and provides instantaneous display of airplane vertical speed in the range of 0 to 6 000 feet per minute up or down These instruments differ from a conventional vertical speed instrument by the addition of two accelerometers which generate pressure differences whenever there is a change in the normal acceleration of the airplane 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 16 DO NOT USE FOR FLIGHT L12 PNEUMATIC BRAKE LEVER 1 Pneumatic Brake Lever The lever has an OFF position and a range marked INCREASE In the OFF position gas pressure is isolated from the transfer tube and the p
56. e full cold position When duct temperature is lowered use of the reset switch will return the system to normal and extinguish the duct overheat lights 6 Air Temperature Selector Switch A selector marked AIR TEMP on the Second Officer s upper panel has FWD SUPPLY AFT SUPPLY MAIN SUPPLY AFT CAB FWD CAB positions The indicator will display temperature of the selected area 10 Altimeter Differential Pressure Gauge An altimeter differential pressure gauge is on the Second Officer s upper panel The dual altimeter and differential pressure gauge registers cabin altitude and pressure difference between cabin and ambient The gauge has two concentric scales and two pointers The short pointer indicates cabin altitude on the inner scale and the longer pointer indicates pressure differential on the outer scale 11 Rate Increase Decrease knob Adjusts the cabin climb or descent rate in automatic cabin pressure control mode 12 Cabin Pressure Control Indicator The combined indicator displays the selected maximum cabin altitude the maximum flight altitude attainable for selected maximum cabin altitude and maximum differential pressure limit and a barometric correction scale www captainsim com 32 DO NOT USE FOR FLIGHT 13 Barometric Correction Setting Knob A knob and indicator on the Second Officer s upper panel are used to introduce the altimeter setting into the controller This setting should be the same as the pilots altimeters
57. ean corrected or de energized Note A differential fault annunciator cannot be reset with the switch 29 Test Switch Used for testing annunciator panel lights When depressed all annunciator lights will illuminate 2010 Captain Sim www captainsim com 10 DO NOT USE FOR FLIGHT CUSTOMER SUPPORT For Customer Support please visit http www captainsim com support Thank you Enjoy your flight Captain Sim Team www captainsim com www captainsim com
58. eld is closed In the TRIP position the field is tripped the generator breaker is then tripped automatically The field of the APU generator normally will remain closed so that the voltage build up is automatic when the APU is being started 8 Auto Fire Shutdown Arming Switch ARMED a fire warning or test will automatically shut down APU OFF automatic shutdown deactivation Note If shutdown is initiated by other fire switch or automatic fire shutdown relay the fuel shutoff valve will close immediately accompanied by other normal shutdown actions www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 99 DO NOT USE FOR FLIGHT 10 Fire Warning Test Reset Switch TEST Heats fire detector to trigger fire warning system CAUTION LIMIT TEST TIME TO 60 SECONDS RESET Will silence fire warning bell and horn and extinguish Master Fire Warning Light When APU Fire Warning Light is extinguished resets automatic fire shutdown to allow starting the APU 11 APU Ammeter The APU ammeter indicates electrical APU or external power load on Phase B 12 APU Exhaust Gas Temperature Indicator This indicator calibrated in degrees centigrade indicates the exhaust gas temperature sensed by the thermocouple on the exhaust flange of the turbine casing P604 LEADING EDGE DEVICES ANNUNCIATOR PANEL 1 4 9 11 16 18 22 25 Green Leading Edge 1 4 9 11 16 18 22 25 Flap Slat Light 5 B 12 14 is 19 21 26 29 5
59. er s upper panel The indicator is scaled 0 20 0 2000 PSI and indicates pressure in the cylinders The pressure transducer for this indicator is common to the indicator on the external charging panel 3 Passenger Oxygen Switch The passenger oxygen switch marked OXYGEN SYSTEM with ON NORMAL positions is on the Second Officer s upper panel and is lockwired to the NORMAL position This switch when placed in the ON position supplies power to the solenoid which operates the electro pneumatic unit and actuates the passenger oxygen system This switch may be used at the discretion of the flight crew or in the event that both automatic valves fail to open during an emergency 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 15 DO NOT USE FOR FLIGHT 4 Oxygen Pressure Indicating Light This light illuminates when the passenger oxygen system low pressure distribution system is pressurized U06 AFT CABIN ZONE TEMPERATURE CONTROL PANEL 1 Auto Pack Trip Cutout Switch 2 Valve Position Indicator 3 Aft Cabin Zone Temperature Switch 4 Aft Cabin Zone Overheat Light 1 Auto Pack Trip Cutout Switch NORMAL auto pack trip system will arm for takeoff CUTOUT auto pack trip system deactivated 2 Valve Position Indicator When the aft zone is selected cooler than the forward zone the pointer will be to the left indicating the forward zone control is open The pointer will be in
60. freon bottle valve to release freon and open the respective engine selector valve to permit freon to enter the engine compartment www captainsim com 31 DO NOT USE FOR FLIGHT 6 Bottle Transfer Selector Switch This switch marked BOTTLE TRANSFER is on the fire control panel The switch controls the routing of the freon extinguishing agent from the two freon bottles RH and LH If it is necessary to discharge the second freon bottle this switch must be selected to the opposite position in which case a new circuit breaker power source is also selected The RH and LH switch positions are associated with the respective RH and LH bottle discharge lights to provide for positive selection of a second freon bottle 12 Fire Test Switch A test switch marked FIRE TEST with FIRE WALLS ENGS amp WHEEL WELLS positions on the fire control panel is provided to test the fire warning system A With the switch in the FIREWALL position the engine fire warning lights will illuminate and tine fire alarm bell will ring normally within 60 seconds After releasing the test switch the lights should extinguish within 15 seconds B With the switch in the ENGS amp WHEEL WELLS position the bell will ring and the wheel well fire warning light will illuminate immediately Normally within 60 seconds all engine fire warning lights will illuminate The fire test switch must be released immediately when all three engine fire warning lights illuminate
61. generator voltage faults generator overload or if engine fire switch pulled 8 17 26 Power Meters Indicates generator real KW or reactive KVAR load Indication is controlled by KVARS switch on U04 ELECTRICAL POWER PANEL 9 18 27 Frequency Control Knobs Permits frequency adjustment of an isolated generator www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 73 DO NOT USE FOR FLIGHT U04 ELECTRICAL POWER PANEL ESSENTIAL 1 POWER orde l 2 Hh E SEM 3 E vae 7 ne EG er 9 STANCE 4 P SOURCE 2 E i 5 6 3 4 9 5 5 7 g 9 1 Essential Power Selector Essential Power Selector Essential Power Failure Warning Light Red Residual Volts Switch AC Voltmeter Frequency Indicator KVARS Switch 7 8 Synchronizing Lights Clear AC Meters Selector Selects power source for essential AC bus If no fault exists a generator can supply essential power with the generator breaker tripped Neither external power nor the APU can supply essential power unless it is on the sync bus and the 3 bus tie breaker is closed In standby position required flight instruments and radios are powered from battery bus and static inverter 2 Essential Power Failure Warning Light Red ON loss of essential power Master warning light also illuminates 3 Residual Volts Switch Changes voltmeter scale from 150 to 30 volts Indicates residual generator voltage to check rotation and
62. ght 1 Oil Cooler Selector Switch CSD FLIGHT ON Turns on cooler ejector in flight for additional CSD oil cooling NORMAL Cooler off in flight ON on ground On causes ejector to pull cooling air across heat exchange GROUND OFF Ejector off Automatically resets to normal on takeoff 2 3 No Equipment Cooling Lights Amber ON indicates no airflow in equipment cooling duct 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 95 DO NOT USE FOR FLIGHT SECOND OFFICER S AUXILIARY PANEL i Tre E T EXMBIT TANK 1258 TANKS TANE 3 OBEN OPER Rede 4 mese f fi 5 TM H TRANSIT R NOZZLE 7 VALVE WX NOZZLE CAUTION CLEAR REVERSERS BEFORE STARTING APU p luem KOK FOWERURITT an C ESRQENERATOR stant LS close ets te ay CRREZBUR DRIT OFEN TEIR BOTTLE AUTO FIRE y IQ OFF DISCHARGE SHUTDOW Er Sa ee NL ME dr mr EE wm Cum hun gg MA er PERS me 0 ir E m P601 Fuel Dump Panel P602 E L T Emergency Locator Transmitter P603 APU Control Panel P604 Leading Edge Devices Annunciator Panel P605 Electrical System Fault Annunciator Panel 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 96 DO NOT USE FOR FLIGHT P601 FUEL DUMP PANEL 1 4 Fuel Dump Valve In Transit Light 5 6 7 8 Fuel Dump Valve Switch 9 12 Fuel Dump Nozzle Valve Switc
63. gine Start Switches Three rotary switches marked ENGINE START with GROUND OFF IGN 1 IGN 2 FLIGHT positions are on the overhead panel With this switch in the GROUND position power BATT BUSS is supplied to open the start valve With this switch in the GROUND or FLIGHT position the 20 joule ignition system is armed This system is energized when the engine start lever is advanced out of the CUTOFF position The starter rotates the engine until engine sustaining speed is reached 35 40 N2 RPM At this speed the pilot releases the start switch which interrupts electrical power to the starter valve causing it to close disengaging the starter A pressure rise is indicated on the duct pressure gauge confirming starter valve closure Low pressure air from the external air source crossbleed air from an operating engine or compressed air from the auxiliary power unit is used for starter operation The access door for the pneumatic ground service connection is on the lower right side of the fuselage adjacent to the tailskid The pneumatic duct pressure indicator used to check pneumatic manifold pressure available for starting and to check starter cutout during starts is on the Second Officer s upper panel On some aircraft the engine start switches on the overhead panel have three positions GROUND OFF FLIGHT They are spring loaded from the GROUND position to the OFF position but will remain in FLIGHT if selected The FLIGHT or GROUND posi
64. h 3 9 Freon Bottle Discharge Light The light will illuminate when the pressure in the respective bottle falls below a pre determined value due to discharge 4 7 10 Fire Handles Three engine fire handles incorporating fire warning lights marked 1 2 amp 3 are on the fire panel Engine fire extinguishing is accomplished by pulling the affected fire handle and depressing the bottle discharge switch for at least one second With the fire handle pulled the following actions occur 1 The extinguisher bottle discharge squib and the engine fire extinguisher selector valve are armed 2 The engine fuel shutoff valve will close 3 The respective wing anti ice valves engine 1 or 3 2 engine cowl valve and the air conditioning bleed valve will close 4 The generator field control relay will trip after 5 to 10 seconds time delay To allow closure of elect powered valves of associated engine 5 The hydraulic fluid supply shutoff valve of engine 1 or engine 2 will close 6 The hydraulic low pressure light circuit for engine 1 or engine 2 are deactivated With the engine fire handle pulled out and the bottle discharge switch depressed the actual fire extinguishing process will commence 5 8 11 Bottle Discharge Switches A push button type bottle discharge switch is located under each engine fire handle When a selector handle is pulled out depressing the respective discharge switch will fire the cartridge in the selected
65. h TANK J TAN TT 10 11 Fuel Dump Nozzle Valve In Transit Light LE Ad Blue ogar 3 f a Gy 7 Y A 4 Ti JA T HE NOzZ 9 10 11 12 is i 1 4 Valve In Transit Lights A valve in transit light will illuminate when the corresponding switch is actuated and remains on until the valve reaches the full OPEN and CLOSE position as selected 5 6 7 8 Fuel Dump Valve Switches Four fuel dump valve switches are marked TANK 1 TANK 2 and TANK 3 and have OPEN CLOSE positions Their respective valve in transit lights adjacent to the switches are marked VALVE IN TRANSIT There is one switch and one light each for tank No 1 and No 3 and two switches and two lights for tank No 2 fuel dump system These switches actuate the fuel tank dump valve to permit or stop the flow of fuel from the fuel tank to the dump system 9 12 Fuel Dump Nozzle Valve Switch Two fuel dump nozzle valve switches and their adjacent lights are marked L NOZZLE R NOZZLE The lights are also marked VALVE IN TRANSIT The switches have OPEN CLOSE positions These switches actuate the fuel dump nozzle valves at the wing tips to open or close the valves With the fuel dump valve switches in the OPEN position fuel under pressure is in the fueling dumping manifold With the fuel dump nozzle valve switch in the OPEN position fuel will be dumped from the airplane as long as automatic shutoff conditions are not encountered With the fuel dump nozzle v
66. h Anti Skid Control Panel Interior Lighting Panel Exterior Lighting Panel Stall Warning System Flight Recorder Compass Mode Panel Flood Light O11 O12 O13 O14 O15 O17 O18 O19 O20 O21 32 CD CIIM E FU LIH Windshield Wipers And Rain Repellent Panel Engine Start Panel Alternate Flaps Panel Cabin Call Panel Voice Tape Recorder Unit Window Heat Panel Anti Ice Panel Wing Engine and Cowl Anti Icing Panel Pitot Static Heat Panel Standby Magnetic Compass 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 33 DO NOT USE FOR FLIGHT 001 HYDRAULIC POWER SYSTEM Fa SRI DRAUDKOROWER y ln 1 3 5 7 9 11 13 15 17 Switch Guard 1 ONSE LI pa A 2 4 10 12 Flight Control Hydraulic Shutoff ae j Switches 2 TE 3 5 6 Spoiler Switch System A 3 4 7H 8 Spoiler Switch System B BERE ELEVATOR EA pet 2 14 16 Lower Rudder Switches Standby and p System A 9 10 18 Upper Rudder Switch System B 11 12 i E E 13 1428 i t 17 18 E cava qe KT 15 16 00 73 2 4 10 12 Flight Control Hydraulic Shutoff Switches Shuts off respective hydraulic system pressure to designated flight controls 6 Spoiler Switch System A OFF Shuts off system A hydraulic pressure to outboard flight spoilers 8 Spoiler Switch System B OFF Shuts off system B hydraulic pressure to inboard flight spoilers Two switches on the overheat panel are ma
67. he MTR OFF position Pulling the switch will bypas the lock HTR OFF Cuts power to the heater for maintenance purposes NORMAL The system including the vane heater is powered when the airplane landing gear safety sensor is in the air position TEST With APU or external power 1 OFF light extinguishes 2 Indicator spins 3 Control columns shake With airplane power 1 OFF light remains extinguished 2 Indicator spins 3 Control columns shake This switch marked STALL WARNING TEST on the overhead panel enables pilots to test the system integrity When the switch is momentarily held in the TEST position a signal is sent into the stall warning computer and makes the pilot s control column shake at the same time if the system is operating on external or APU power the stall warning power failure light will go off thus indicating proper operation of the vane heater Additionally a spinner will rotate to indicate the flap to computer circuitry is intact When the switch is momentarily held in the TEST position a signal is sent into the stall warning computer and makes the pilot s control column shake at the same time if the system is operating on external or APU power the stall warning power failure light will go off thus indicating proper operation of the vane heater Additionally a spinner will rotate to indicate the flap to computer circuitry is intact 008 FLIGHT RECORDER ismer h o AE UN 1 Flight Recorder Light VE
68. he autopilot pitch channel is disengaged and the stabilizer out of trim light will not operate 19 Stabilizer Trim Light An amber light on the control stand will illuminate when the stabilizer main electric trimmotor is operating or when the cruise and autopilot trim motor is operated by the stabilizer cruise trim switch The light will not be on when the autopilot operates the cruise and autopilot trim motor 20 Flap Lever Scale All Indicated flap positions are detented In addition flap positions 2 and 25 are gated to interrupt flap lever travel to cross check airspeed with flap positions P10 P11 VHF NAV COMM CONTROL PANEL i 1 NAV Frequency Indicator Gem El rump 2 COMM Frequency Indicator F DE e um E ESI 3 7 NAV Frequency Selector 4 NAV Volume Control 6 DME Override Button ee I Y Hy F pe og EXIT nM wd 5 9 COMM Frequency Selector 8 COMM Volume Control 1 NAV Frequency Indicator Displays the frequency selected by the NAV Frequency Selector Knob 2 COMM Frequency Indicator Displays the frequency selected by the COMM Frequency Selector Knob 3 5 NAV Frequency Selector Selects frequency as shown in NAV frequency window Rotate outer ring changes the digits to the left of the decimal point Rotate inner knob changes the digits to the right of the decimal point 6 DME Override Button With DME function switch at OVERRIDE position each system will track a DME sig
69. he instrument loss of a return radio signal incorrect altitude tracking and operation above the altitude range of the equipment The flag also appears when the low range radio altimeter test switch is actuated A test switch is installed on the altimeter Operating the test switch will cause the altimeter to indicate 250 10 feet and the warning flag to appear On some aircraft pressing the test switch causes the display to indicate 100 feet or 40 feet as installed 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 17 DO NOT USE FOR FLIGHT L14 ELECTRIC ALTIMETER The pilot s altimeters are electrically operated The Captain operates from the 1 air data computer and furnishes the air data computer with barometer corrections These corrections are applied to the altitude signals sent from the air data computer to the altitude alerting system The First Officer s altimeter operates from the air data sensor This altimeter is the secondary altitude source for the ATC transponder On some aircraft a servo pneumatic altimeter on the Captain s panel is normally driven by the Air Data System and provides corrected altitude signals to the altitude alert system The altimeter reverts to pneumatic operation in the event of power or air data failure A pneumatic altimeter is provided on the F O s panel which operates from the F O s static system An altitude alerting system gives audible and v
70. he three right 8th stage valves Again if each valve position agrees with its control switch the respective position light illuminates 3 The COWL position checks agreement of the three 13th stage valves In addition for engine 2 the 6th stage valve is wired in series with the 13th stage valve thus the 2 light will not illuminate unless both valves agree with the control switch position 4 WING checks the position of the wing anti ice valves in relation to the wing anti ice switch position O20 PITOT STATIC HEAT PANEL 1 3 Pitot Static Ammeters 2 Pitot Static Heat Ammeters Selector rann funne fet bd bw c4 L5 Gab 4 6 Pitot Static Heat Switches fr t r farm a 5 Heater OFF Light Amber i LEFT PITCH POI TATIC STATIK MF PROBI AUX PTOT LEV MIOT TAA BTE TA c TUI Lue Qr DEF d ON 1 3 Pitot Static Ammeters The two AC ammeters marked LEFT and RIGHT The ammeters display current drain for corresponding left and right heating units 2 Pitot Static Heat Ammeters Selector This selector marked PITOT STATIC HEAT with S P T PROBE AUX P ELEV P positions The selector is used in conjunction with the two AC ammeters to compare current drain for corresponding left and right sensor heaters The selector is spring loaded to P PITOT position 4 6 Pitot Static Heat Switches These switches are on the overhead panel The left switch is marked PITOT STATIC TEMP PROBE ELEV
71. id Shutoff Switch These switches marked FLUID SHUTOFF ENG 1 and ENG 2 with OPEN CLOSE positions on the S O lower panel control the fluid shutoff valves in the supply line of each engine driven pump 2010 Captain Sim www captainsim com 92 DO NOT USE FOR FLIGHT The switches are guarded OPEN In the CLOSE position supply to the corresponding system A pump will be shut off With the engine fire switch pulled on engine No 1 or engine No 2 the fluid shutoff valve will be closed regardless of fluid shutoff switch position 9 11 System B Pump Switches Two switches on the S O lower panel with ON OFF positions control operation of the system B electric motor driven hydraulic pumps through a power relay The switches also control power to the respective system B overheat light 10 12 System B Pump Low Pressure Lights Two amber lights marked ELEC PUMP 1 ELEC PUMP 2 LOW PRESS The light will illuminate when the applicable system B hydraulic pump output pressure is below 1100 PSI or when the pump is off The light extinguishes when pressure is above 1500 PSI A pressure switch in each pump output line operates the light Electrical power is DC1 and DC2 respectively 13 Standby System Overheat Light This amber light on the S O lower panel is marked OVERHEAT The light will illuminate when the standby system return fluid temperature is excessive 104 C It extinguishes when temperature drops below 74 C 14 Standby System Light
72. ied to each window 4 green lights In OVERHEAT TEST an overheat condition is simulated and the overheat circuit s monitoring reliability is checked 4 amber lights On old type of controllers the power on green lights go out immediately upon illumination of amber overheat lights With a newer type of controller installed on various aircraft the power on green light will remain on for 55 seconds 15 seconds after power is removed This will occur even when the overheat trip is operated In this case both amber and green lights will be on for a short period of time until the power on lamp goes out Apart from this operational differences both units are physically and functionally interchangeable www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 47 DO NOT USE FOR FLIGHT 018 ANTI ICE PANEL 1 2 3 1 Anti Ice Duct Temperature Indicator 2 Anti Ice Duct Overheat Light Amber 3 Anti Ice Duct Temperature Selector DUCI TA 1 Anti Ice Duct Temperature Indicator Temperature indication as determined by duct temperature selector 2 Anti Ice Duct Overheat Light Amber ILLUMINATED e Excessive temperature in left or right wing anti ice supply or duct e Engine 2 cowl duct e Independent of duct temperature selection 3 Anti Ice Duct Temperature Selector Determines source of temperature displayed by duct temp indicator ENG 1 Wing anti ice left supply duct temperature ENG 2 Engine 2 cowl d
73. isplay radar returns No radar 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 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 SBY will appear in the lower left of the display 56 DO NOT USE FOR FLIGHT 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 O degrees azimuth and 30 degrees tilt down 8 ON Light 10 TILT STAB Permits manual adjustment of antenna tilt 159 up or down for best indicator presentation The tilt angle is displayed yellow in the upper right corner of the display D Down U Up THEORY OF OPERATION 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
74. isual indication of approaching an altitude acquisition or departing from an altitude deviation In the acquisition mode an aural signal tone will sound momentarily and the alert lights will come on when passing through a point approximately 900 feet above or below the selected altitude The light will remain on until approximately 300 feet from the selected altitude In the deviation mode when departing the selected altitude the aural signal will sound momentarily and the alert lights will come on at approximately 300 feet above or below the selected altitude The alert light will remain on until reset by pressing the alert light A failure flag will appear in the alert indicator if a failure occurs in the Captain s altimeter or the alert indicator The altitude alerting system may be tested by turning the altitude selector toward the airplane altitude and then up through more than 900 feet above the airplane altitude The aural signal sounds momentarily and the alert light illuminates when the indicator reads 300 feet from the airplane altitude and remains extinguished until 300 feet from the airplane altitude When indicator altitude exceeds airplane altitude by 300 feet the aural signal sounds momentarily and the alert lights illuminate 1 Failure Warning Flag 2 Reference Altitude Bug 3 100 Foot Pointer 4 Altitude Numerical Counter 6 5 6 Altimeter Setting Windows 7 Barometric Setting Control 8 Reference Altitude Bug Selector
75. l remainder blank Parking brake on all blank system deactivated Four brake released indicators are adjacent to the main gear anti skid switch on the overhead panel Two of the indicators are marked LEFT OUTBD and INBD The other two are marked RIGHT INBD and OUTBD These indicators normally show blanks When a brake is released by the anti skid system the corresponding indicator will display REL During anti skid system test the brake released indicators of the brakes selected by the anti skid test switch position will show blanks and the remaining brake released indicators will show REL 005 INTERIOR LIGHTING PANEL 1 2 3 4 3 6 7 B 5 10 11 meg L oat i i T cum d a I T ST j D 1 FA d S n L 1d Lib LES d 12 13 14 1 11 Map Lights Switch 2 Left FWD amp Side Panel Lights 3 Center FWD Panel Lights 4 FWD Panel Background Lights 5 FWD Panel Fluor Lights 6 Overhead Panel Lights 7 Control Stand Red Lights 8 Control Stand White Lights Light Override Switch 10 Right Fwd amp Side Panel Lights 12 Compass Light 13 Dome Red 14 Dome White O 2010 Captain Sim www captainsim com 37 DO NOT USE FOR FLIGHT 2 Left FWD amp Side Panel Lights Control integral Instrument illumination on left forward and tide panels Alto controls panel light for first and second observers 3 Center FWD Panel Lights Control integral instrument illumination on center panel 4 FWD Pane
76. l Background Lights Control lights located under the light shield 5 FWD Panel Fluor Lights Control white fluorescent lights under light shield 6 Overhead Panel Lights Control integral instrument Illumination on overhead panel 7 Control Stand Red Lights Control red flood lights located in overhead panel for illuminating the control stand 8 Control Stand White Lights Control white floodlight located in overhead panel for illuminating the control stand 10 Right Fwd amp Side Panel Lights Control integral instrument illumination on the right forward and side panels 12 Compass Light Controls light in standby compass 13 Dome Red Three pairs of red and white dome lights provide general diffused illumination of the control cabin Two pairs of lights are installed on the left and right supports of the overhead panel and the other pair in the center of the aft control cabin area The variable intensity control for the red lights is by a switch marked DOME RED on the overhead panel 14 Dome White The control for the three white dome lights is by two switches a switch to the right of the control cabin door and the other by a switch marked DOME WHITE on the overhead panel When external AC power is applied to the airplane and the external power switch on the S O upper panel is in the GRD SERVICE position power is available to the white dome lights www captainsim com 727 Captain FLIGHT MANUAL Part II
77. l Panel P14 Aft Pedestal Panel P01 P07 ADF CONTROL PANEL 1 Loop Control 4 2 Beat Frequency Oscillator BFO Switch T ar 3 Frequency Indicator 4 Tuning Meter 5 Volume Control 6 Volume Control Function Selector 7 Frequency Band Selector 8 Frequency Band Selector Tuning Control 1 Loop Control Switch has L R positions fast or slow When moved left or right the phasing in the fixed loop antenna will be shifted providing the effect of rotating the antenna Operates only in LOOP function Used to determine bearing information by rotating the loop antenna right or left while observing the tuning meter for minimum deflection at the aural null position 2 Beat Frequency Oscillator BFO Switch OFF Undistorted voice reception is possible BFO Precise tuning is possible when the function selectoris in the ANT position The BFO provides a tone for unmodulated CW signals 4 Tuning Meter Displays relative strength of signal being received Most desirable reception is achieved by tuning for maximum needle deflection 6 Function Selector OFF Power off ADF Both the sense and loop antennas operate bearing information is displayed on the RMI s 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 53 DO NOT USE FOR FLIGHT ANT Only the sense antenna is used The receiver is used for reception of audio signals no bearing information is displayed
78. l appear with loss of electrical power to the compass system DG not levelling or underspeed or excessive heading error signal 5 6 ADF VOR Pointers Pointers indicate ADF and VOR bearing as selected by the ADF VOR knobs at the bottom of the instrument A narrow pointer marked with a dashed line displays bearings from VOR No 1 or ADF No 1 as selected by the switch in the lower left corner of the instrument A wide pointer marked with two parallel solid lines displays bearings from VOR No 2 or ADF No 2 if installed as selected by the switch in the lower right corner LO6 ANNUNCIATORS 1 Master Comparator Warning Light Amber 2 Pull Up Light GPWS Test Switch Red 3 GC Cancel Light 1 Master Comparator Warning Light Amber An amber COMPARATOR light on each pilot s panel directs the pilot s attention to the annunciator on the center console 2 Pull up Light GPWS Test Switch Red lluminates flashing to provide visual warning Press to test aural and visual warnings System cannot be tested between 50 and 1000 feet Y 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 11 DO NOT USE FOR FLIGHT LO7 ATTITUDE DIRECTOR INDICATOR ADI 1 Flight Director Bar 2 Glide Slope Pointer 1 4 3 Glide Slope Warning Flag 3 4 Bank Indicator amp 5 Symbolic Airplane 6 Gyro Warning Flag T 7 Course Deviation Scale 8 Test Knob 9 Localizer Warning Flag
79. lacing the test switch to the GROUND TEST position and observing the illumination of the TRIP light Moving the switch to the GROUND RESET position will reset the system GROUND TEST Simulate trip condition NORMAL System armed GROUND RESET Resets trip light and wing anti ice valves after trip or test Reset can only be accomplished on the ground 5 Wing Anti Ice Auto Trip Off Light Amber ILLUMINATED Wing anti ice duct rupture All wing anti ice valves close 6 Overheat Test Switch A test button adjacent to the overheat lights is provided to test continuity in the detection elements and associated wiring and satisfactory control unit and lights operation 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 78 DO NOT USE FOR FLIGHT U10 PNEUMATIC SYSTEM PANEL 1 2 3 4 a 6 7 8 9 10 CARGQ HEIT CONTRO CABIN br PA rac CLOM CODLING DOORS Fl AP j x f A olet a gt ELSE A CLOSE LEFT A C PA SIGHT A C PACK 4 Li p AM Lf DI 8 i f TT A P i i du d INE z BE i T es k l E Cound i5 E x e npn 5 LY E X7 Wig v mm INI l G El Y eiat HGH ME Or GLINEE EL INSANE I BLEDA ENGINE z La BLEED INGINE 3 BLEED ai 11 12 13 14 13 16 17 18 19 20 321 22 1 Air Conditioning Pack Reset Switch 2 10 Cooling Doors Switch 3 Cargo Heat Outflow Switch 4 9 Cooling Doors Position Indicators 5 7 Pack Tempera
80. leted and the switch is in the ENGAGED position the autopilot will control the airplane about its pitch axis from signals received from the vertical gyro the autopilot turn and pitch controller or from such navigational facilities as selected by the autopilot mode selector Note To engage the elevator switch the aileron switch must be engaged 5 Altitude Hold Switch The altitude hold switch on the aft electronic control panel has positions marked ALT HOLD OFF and is spring loaded to the OFF position The switch is magnetically held in the ALT HOLD position The magnetic holding circuit will be broken and the switch will revert to the OFF position with the autopilot elevator switch in the DISENGAGED position With the switch in the ALT HOLD position the autopilot controls the airplane about its pitch axis so as to maintain a constant barometric altitude as sensed by the air data computer system The pitch control function of the autopilot turn and pitch controller is inoperative when the autopilot altitude hold switch is in the ALT HOLD position 6 Pitch Channel Selector This selector is on the aft electronic panel and has a A B INOP positions The AB position is deactivated With the selector in the A position the pitch channel controls pitch axis by selecting the left transfer valve thereby selecting hydraulic system A as the source of power to control elevators When the selector is in the B position the above is duplicated u
81. lip or skid in turns 1 DME Indicator 2 Course Cursor 3 Compass Card and Lubber Line 4 Compass Heading Warning Flag 5 Heading Cursor 6 Course Counter 7 Glide Slope Pointer 8 Glide Slope Warning Flag 9 Navigation Warning Flag 11 12 13 14 15 10 Course Bar 11 Heading Selector 12 Course Deviation Scale 13 Symbolic Airplane 14 TO FROM Indicator 15 Course Selector 1 DME Indicator Indicates slant range in nautical miles to station tuned on corresponding VHF NAV radio 2 Course Cursor Indicates course correspond ing to digital readout on course counter Rotates with card 3 Compass Card and Lubber Line Rotating card driven by compass system indicates airplane magnetic heading under lubber line 4 Compass Heading Warning Flag IN VIEW Compass system power fails Signal is unreliable Compass display is in error 5 Heading Cursor Indicates desired heading for flight director and or autopilot operation 2010 Captain Sim www captainsim com 13 DO NOT USE FOR FLIGHT 6 Course Counter One for each integrated flight system Digital readout displays course as set by course selector 7 Glide Slope Pointer Indicates glide slope location relative to airplane position In view when localizer frequency is selected In parallel with glide slope pointer on ADI 8 Glide Slope Warning Flag IN VIEW over glide slope scale and pointer after localizer frequency is tuned when e Glide slo
82. nal at an ILS station up to a maximum of 200 miles 7 9 COMM Frequency Selector Selects frequency as shown in COMM frequency window Rotate outer ring changes the digits to the left of the decimal point Rotate inner knob changes the digits to the right of the decimal point 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 65 DO NOT USE FOR FLIGHT P12 AUTOPILOT PANEL Autopilot Mode Selector Autopilot Turn And Pitch Controller Autopilot Aileron Switch Autopilot Elevator Switch Altitude Hold Switch Pitch Channel Selector Heading Select Switch OU CN HL 1 Autopilot Mode Selector This control with MAN NAV LOC AUTO G S MAN G S positions is on the aft electronic panel The selector is held magnetically in all positions but MAN The selector is spring loaded to the MAN position The selector must be in the MAN position to engage the autopilot In the MAN position the autopilot will maintain the magnetic heading and pitch that exists at the time the autopilot is engaged If the airplane is in a bank at the time of engagement the autopilot will level the wings Rotating the turn and pitch controller causes the airplane to roll into a turn When the desired heading is reached and the controller is centered the autopilot will maintain the new heading Altitude hold will function in this mode If the heading select switch on the autopilot control panel is
83. neumatic brake line is vented to ambient pressure When the lever is in the INCREASE range metered pneumatic pressure depending on the position of the pneumatic brake lever reaches the transfer tube and applies all main gear brakes simultaneously L13 HEIGHT INDICATOR 1 Decision Height Light 2 Altitude Alert Light 3 Adjustable Altitude Trip Cursor 4 Pointer 5 Flag Display 13 6 Push to Test Button RADIO 0 ar l 5 NN 7 Adjustable Altitude Trip A low range radio altimeter is provided on each of the pilot s panels The low range altimeter displays height above terrain with an altitude pointer moving over a circular scale The range of the altimeter is from 0 feet to 2 500 feet A decision height DH selector is on one comer of the instrument and a decision height cursor is provided on the periphery of the altimeter This cursor can be moved about the periphery of the altimeter with the DH selector thus selecting the altitude at which a decision height light will illuminate A decision height light marked DH is on each pilot s panel and on each radio altimeter These lights will illuminate when the altitude pointer on the associated low range radio altimeter reaches the DH cursor on that altimeter The low range altimeter warning flag is a cross hatched flag which appears on the dial face When the altimeter is operating properly the flag is retracted The cross hatched warning flag appears with power loss to t
84. ngine start lever in cutoff 22 28 33 Engine Fuel Shutoff Valve in Transit Light Blue ON during respective valve transit OUT after valve attains new position Wwo02 CLOCKS 1 Sweep Second Hand 2 Hour Hand 1 2 3 3 Minute Hand 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 86 DO NOT USE FOR FLIGHT WO03 HYDRAULIC BRAKE PANEL 1 Hydraulic Brake Interconnect Light 2 Hydraulic Brake Interconnect Switch 3 Switch Guard 2 4 1 Hydraulic Brake Interconnect Light This green light on the S O lower panel is marked HYD BRAKE INTERCONNECT ON When the switch is in the OPEN position the green light will illuminate if the hydraulic brake interconnect valve is fully open When the switch is in the CLOSE position the light will extinguish only when the valve is fully closed 2 Hydraulic Brake Interconnect Switch This switch on the S O lower panel is marked HYD BRAKE INTERCONNECT and has OPEN CLOSE positions The switch is normally guarded in the CLOSE position When the switch is in the OPEN position the hydraulic brake interconnect valve is open and system A hydraulic pressure will energize the hydraulic brake system 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 87 DO NOT USE FOR FLIGHT W04 ENGINE OIL PANEL 1 2 3 Oil Quantity Instrument 4 5 6 Oil Temperature Indicator 7 8 9 Oil Pressure Indica
85. nose up The main electric trim system will operate the stabilizer from 0 6 units airplane nose up to 12 25 units airplane nose up 14 15 16 Engine Start Levers Three engine start levers with CUTOFF IDLE detents are on the control stand This lever operates the windmill bypass and shutoff valve in the FCU With this lever in the IDLE detent fuel if supplied to the engine In the CUTOFF detent all fuel supply to the engine is shut off With this lever in the IDLE detent and with the engine start switch in the GROUND or FLIGHT position the 20 joule ignition system is energized The start levers control the main fuel shutoff valves when in the CUTOFF position 11 Parking Brake Lever The parking brake lever on the control stand can be set when the brakes are fully applied to latch the brakes in the depressed position When the parking brake is set hydraulic return from the main gear antiskid valves will be blocked and the anti skid system will be de energized 13 Parking Brake Warning Light This red light on the control stand will illuminate when the parking brake handle is in the SET position 18 Stabilizer Cruise Trim Switch This switch is spring loaded to the center or neutral position Manual operation of the switch controls operation of the stabilizer trim actuator by the cruise trim motor www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 64 DO NOT USE FOR FLIGHT When this switch is actuated t
86. o 16 R Service Door 3 7 14 Landing Gear Door Annunciators Three annunciators on the S O lower panel marked L MAIN GR DOOR NOSE GEAR DOOR and R MAIN GR DOOR will illuminate when the corresponding doors are not up and locked 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 8 DO NOT USE FOR FLIGHT W08 AUDIO SELECTOR PANEL 1 2 3 oa 1 5 9 15 Communication Receiver Switches 6 Transmitter Selector 7 Microphone Push to talk Switch 8 Mic Selector Switch fy fy A fi 9 10 11 12 13 14 13 1 5 9 15 Communication Receiver Switches Switches on each audio selector panel are used to connect audio from a selected facility to the associated crew member s headphones or loudspeaker at the Captain s F O s stations Any one or any combination of audio facilities can be monitored by moving the appropriate switches to the UP position provided the emergency audio switch is in NORM position 6 Transmitter Selector Selects desired transmitter 7 Microphone Push to talk Switch Press to transmit through oxygen mask or boom microphone 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 90 DO NOT USE FOR FLIGHT 1 3 5 Fuel Heat Valve Light 2 4 6 Fuel Icing Caution Light 7 8 9 Fuel Heat Switch 10 1 Tank Fuel Temperature Indicator 1 3 5 Fuel Heat Valve Light These lights marked FUEL HEAT VALVE ENG 1 E
87. on lights are mounted flush with the fuselage and forward of the wing leading edge The lights are controlled by a switch on the lower edge of the overhead panel marked WING with ON OFF positions 11 Main Wheel Well Lights Switch Each main wheel well is illuminated by two clear lights one on the forward bulkhead and one on the keel beam near the ceiling The lights can be controlled by a switch marked WHEEL WELL with NORMAL ON positions on the overhead panel With the switch in the NORMAL position the wheel well lights are controlled by the switch in each respective wheel well When the switch is in the ON position the wheel well lights will be on regardless of the switch position in the wheel wells 007 STALL WARNING SYSTEM 1 Stall Warning Power Failure Light 3 Stall Warning Test Switch 2 Test Indicator The stall warning system provides a means of alerting the pilots of a flight condition approaching a stall When the system is armed and a near stall attitude is sensed a shaking device on the Captain s control column makes the control column shake The stall warning system components are as follows an angle of airflow sensor a flap position transmitter a stall warning computer a control column shaker motor and a landing gear safety oleo squat switch circuit An internal heater is provided for the angle of airflow sensor unit for the vane anti icing The landing gear safety oleo squat switch circuit is used for arming
88. on with the switch in the open position during ground operation 5 7 10 Engine Inlet Anti Ice Switches These switches marked ENGINE INLET ENG 1 ENG 2 ENG 3 with OPEN CLOSE positions Each switch controls three bleed air duct shut off valves for the respective engine left 8th stage 13th stage right 8th stage In addition the switch for 42 engine controls the 6th stage bleed valve 6 8 11 Engine Inlet Anti Ice Valve Position Lights Green These lights marked VALVE pos ENG I ENG 2 ENG 3 The lights provide a visual check of agreement between the control valve position and their respective control switch position Illuminated valve position agrees with switch position 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 49 DO NOT USE FOR FLIGHT 9 Anti Ice Valve Position Light Selector The five position rotary switch is used in conjunction with the lights to check Anti Ice Valve position The switch is marked OFF L COWL R WING 1 When in L LEFT position the three valve position lights are connected to their respective engines left 8th stage anti ice valve If each valve position agrees with its control switch position either OPEN or CLOSE the position lights illuminate Should any of the three valves be in a position opposite to its switch the respective light will be xtinguished 2 When in R RIGHT position the three valve position lights are connected to t
89. ontaining magenta and red areas by at least 20 nautical miles e 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 e 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 LS d 2 nn pm 7 fy a a n iy i Ls T ul F Minn t mm 20 NM CKM CORRIDOR T Lu C DERE 7 TG M a ia 3 me i ny 2 es 2 lal a B A E www captainsim com 60 DO NOT USE FOR FLIGHT 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
90. ontrolled by elapsed time switch 2 4 Hours And Minute Hands Reset by knob on lower lefthand corner of clock 3 Elapsed Time Switch Rotating switch clockwise to 0 resets elapsed time hands to 12 o clock position Rotating switch clockwise to GO starts elapsed time hands Rotating switch clockwise to STOP stops elapsed time hands Do not move switch counter clockwise from GO to 0 or from 0 to STOP 5 Winding amp Setting Control Winds clock when turned clockwise One complete winding good for 8 days With knob pulled out turning in either direction will set main hour and minute hands 2010 Captain Sim www captainsim com IT MANUAL Part II Aircraft and Systems 8 DO NOT USE FOR FLIGHT 6 Lower Minute Register Hand Controlled by push button 7 Sweep Second Hand Controlled by push button on lower right hand corner of clock 8 Push Button With sweep second hand at the 12 o clock position e Pushing button once starts the second hand pushing a second time stops the hand pushing a third time resets hand to 12 o clock position e Minute register hand indicates elapsed time In minutes of sweep second hand L03 AUTOPILOT DISENGAGED WARNING LIGHT 1 Autopilot Disengaged Warning Light A red light press to test and reset marked AUTOPILOT DISENGAGED is on both the Captain s and the First Officer s panel With the autopilot engaged the lights will come on flashing any time either or both channels of the aut
91. opilot become disengaged for any reason Note An interchangeable autopilot component may be installed which will cause the autopilot disengaged warning lights to illuminate any time power is applied to the airplane or any time power is switched to airplane power The lights can be extinguished by depressing the autopilot disengaged warning light on the Captain s or First Officer s panel or by firmly depressing either autopilot release switch on either control wheel Note If a failure occurs in the elevator pitch channel use the autopilot disengaged warning light reset to extinguish and rearm the lights and it will not disengage the operating aileron roll channel The autopilot warning lights will illuminate steadily when any one of the self test switches of the control channel boxes in the lower 43 compartment is not in the off position The lights cannot be extinguished except by positioning the switch to OFF The lights can be tested by depressing the light on the Captain s or First Officer s panel The depressed light will illuminate steadily while the remaining light will flash The lights can also be tested by the master test and dimming switch 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 9 DO NOT USE FOR FLIGHT 1 Vmo Pointer 2 Airspeed Pointer 3 Movable External Reference Marker 4 Cursor Control 5 Vmo Mode Selector 1 Vmo Pointer Displays ma
92. pe power fails e Signal is unreliable e In parallel with glide slope warning flag on ADI 9 Navigation Warning Flag IN VIEW e VHF NAV radio power fails e Signal is unreliable 10 Course Bar Movable center portion of course cursor represents segment of VOR radial or localizer beam Relationship of bar to course deviation scale shows airplane position with respect to selected course 11 Heading Selector Rotation of selector adjusts heading cursor on Captain s and First Officer s HSI s Selects heading for computed steering commands Selected heading Captain s HSU transmitted to autopilot and flight director 12 Course Deviation Scale Reference for measuring displacement from selected course course bar One dot deviation of course bar represents approximately 5 degrees on VOR and 1 degrees on localizer 13 Symbolic Airplane Represents airplane position relative to the selected course course bar 14 TO FROM Indicator Indicates direction of VOR station along selected course OUT OF VIEW in localizer operation Shown in TO position 15 Course Selector One for each integrated flight system Rotation adjusts associated course counter and course cursor to desired course for VOR or localizer navigation Course selected for auto pilot on Captain s HSI www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 14 DO NOT USE FOR FLIGHT L09 ANNUNCIATORS 1 MDA light amber Approach Progress Display 2 8
93. positions and is guarded to the ON position When the switch is in the OFF position the upper rudder hydraulic supply shutoff valve is closed which deactivated the rudder O02 YAW DAMPER SWITCHES 1 3 Switch Guard TAW CARPE Ref i5 UPPER LOVER fi c W 2 4 Yaw Damper Engage Switches 1 2 3 4 2 4 Yaw Damper Engage Switches Two switches on the overhead panel each with ON OFF positions one marked UPPER and the other LOWER are used to control the yaw dampers 003 FLIGHT CONTROL WARNING TEST SWITCH 1 Flight Control Warning Test Switch FELT CONTROL WARNING TEST Vg JA EN SAFETY CASUM C A E E DOO p RELAY BYPASS e BYPASS M 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 25 DO NOT USE FOR FLIGHT O04 ANTI SKID CONTROL PANEL 1 2 3 4 1 Anti Skid Test Switch i n E ce er RARE S MNT GI 2 Nose Gear Brake Released Indicator ANTI S ID TEST E SE J 3 Nose Gear Brake and Anti Skid Switch 4 6 Switch Guard OUTED NOSE 5 Main Gear Anti Skid Switch MAIN GEAR ANTI SHKID ow LEFT RiGHT fe 7 10 Brake Released Indicator Sy QUTEO NBD med OUTED LLL LH Em RN HN Ay ry y uas 3 6 7 8 3 10 The anti skid system prevents wheel skidding by controlling applied brake pressure Maximum braking efficiency is obtained when all wheels are in a slight skid or at a maximum rate of deceleration
94. returns show an obvious corridor between two areas of heavy rainfall but the long range setting shows a larger area of heavy rainfall THE BLIND www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 61 DO NOT USE FOR FLIGHT PO5 WINDSHEAR FAILURE LIGHT Windshear Failure Light Iluminates when significant mailfunction is detected by built in test equipment P06 FLAP POSITION SWITCH 1 Flap Position Switch 1 2 GROUNZ AJ IV PROXIMITY ME WARMING M 2 Switch Guard OFF NORM de OVERRIDE 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 62 DO NOT USE FOR FLIGHT P09 CONTROL STAND 17 men II YES FLGLSTT i SLE a WOW o a E L I44 L IE M wm HEP m 910 11 1213 14 15 1617 18 319202122 2324 1 Speedbrake Lever 2 4 7 Thrust Levers 3 5 7 Reverse Thrust Levers 8 Flap Lever 9 24 Trim Wheel 10 23 Stabilizer Trim Indicator 11 Parking Brake Lever 12 17 Go Around Switch 13 Parking Brake Warning Light 14 15 16 Engine Start Levers 18 Stabilizer Cruise Trim Switch 19 Stabilizer Trim Light 20 Flap Lever Scale 21 22 Stabilizer Trim Cutout Switches Main Electric Autopilot and Cruise 1 Speedbrake Lever and Scale A lever on the control stand marked SPEEDBRAKE can be moved over a scale with 0 5 10 20 30 and 40 markings A detent is at the 09 position The lever
95. rked SPOILER SYS B INBD and SYS A OUTBD The switches have ON OFF positions and are guarded in the ON position Each switch controls a motor operated hydraulic shutoff valve When a spoiler switch is in the OFF position hydraulic supply to the corresponding spoilers is shut off Hydraulic locks will prevent upward movement of the flight spoilers when normal hydraulic pressure is not available 14 16 Lower Rudder Switches Standby and System A Switches and guards ganged together Guards up switches up shuts off System A hydraulic pressure to lower rudder Turns on Standby System Pump Two ganged switches on the overhead panel are marked RUDDER SYS A and STANDBY The switches have ON OFF positions When the switches are guarded the system A rudder switch is on and the standby rudder switch is off In this position the standby rudder power unit is functioning as a gust damper When the system A rudder switch is in the OFF position the standby rudder switch is ON and the standby hydraulic system is operating A hydraulic transfer valve will engage the standby power unit hydraulically to operate the lower rudder 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 34 DO NOT USE FOR FLIGHT 18 Upper Rudder Switch System B OFF shuts off system B hydraulic pressure to upper rudder The system B rudder switch on the overhead panel is marked RUDDER SYS B The switch has ON OFF
96. sim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 23 DO NOT USE FOR FLIGHT C07 ENGINE INSTRUMENT PANEL 1 2 3 Thrust Reverser Operating Lights 4 6 Engine Pressure Ratio Setting Pointer 1 3 7 9 Engine Pressure Ratio Bug 5 10 12 Engine Pressure Ratio Setting Display 7 8 13 15 EPR Bug Setting Knob 0 12 13 15 16 18 N1 Tachometers 19 21 Engine Exhaust Gas Temperature 16 18 Indicators 22 24 N2 Tachometers 25 27 Engine Fuel Flow Indicators 19 21 N e 3j I ih L1 22 24 239 27 1 2 3 Thrust Reverser Operating Lights Three amber thrust reverser operating lights marked REVERSER OPERATING This light illuminates to indicate that the reverse thrust unit is not locked in the cruise forward thrust position This light may be dimmed if required Engine Pressure Ratio Indicators An indication of engine thrust output is shown by three engine pressure ratio indicators on the pilot s center panel Engine pressure ratio is defined as the ratio of the turbine discharge total pressure to the engine inlet total pressure Pt7 Pt2 and is a parameter of the thrust developed by the engine The indicator is used as a primary thrust setting instrument since EPR is directly proportional to thrust Most EPR gauges require normal AC from their respective busses 13 15 Engine Pressure Ratio Setting Knob A setting knob enables the pilot to set the reference index and the digital indicator to the preselecte
97. sing B system hydraulics Autopilot elevator switch will trip if pitch channel selector is moved 7 Heading Select Switch This switch on the aft electronic control panel has a center OFF position and a HDG SEL position It is either magnetically held in the HDG SEL position or spring returned to center off With the switch in the HDG SEL position the autopilot is provided with compass system directional information The HDG SEL position may be used in the following modes MAN NAV LOC AUTO G S and MAN G S The switch will automatically return to the OFF position when the turn control knob is out of detent or the localizer or VOR radial selected is captured www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 67 DO NOT USE FOR FLIGHT P13 TRANSPONDER TCAS CONTROL PANEL 1 Function Selector 2 Power Light 3 ATC Display Window 4 ATC Display Range Selector 5 Altitude Source Selector 6 7 9 10 Code Selector Knobs 8 Ident Pushbutton 11 Relative Altitude Display Limit Selector 1 Function Selector Selects operating mode STBY mode places transponder and TCAS system to standby 3 ATC Display Window Displays Code set by ATC Code Selectors 4 ATC Display Range Selector Selects display range of TCAS To cycle through ranges use click zones plus to cycle to the right and minus to cycle to the left 5 Altitude Source Selector Selects which of the transponders is in use
98. the generator breaker is tripped This light will not be illuminated if the APU switch is in the OFF position 3 APU Generator Field Light This amber light adjacent to the APU generator field switch when illuminated indicates that the generator field is de energized 4 Fire Switch with Fire Warning Light Red When pulled will arm the respective APU bottle discharge switch trip the APU generator field relay and close the APU fuel shut off and bleed air valve ILLUMINATED Indicates fire in APU shroud Fire alarm bell in cockpit and intermittent APU fire warning horn in nose wheel well also sound Master Fire Warning Lights also illuminate 5 APU Generator Breaker Switch This toggle lock switch marked GENERATOR with CLOSE TRIP positions is on the APU control panel With this switch in the CLOSE position the APU generator is connected to the airplane electrical distribution system if the APU is operating at governed speed external power is off and engine generator breakers are tripped With this switch in the TRIP position the APU generator is tripped The APU generator breaker is automatically tripped by placing the external power switch ON or by moving the engine generator breaker to CLOSE 6 Bottle Discharge Switch Armed only if APU fire twitch pulled 7 APU Generator Field Switch This toggle lock switch marked FIELD with CLOSE TRIP positions is on the APU control panel With this switch in the CLOSE position the fi
99. the stall warning system The stall warning system airflow sensor is anti iced continuously any time airplane power is on With external or APU power connected the anti icing system is not operating except when the system is checked momentarily by the means of the test switch The airflow sensor generates an electrical signal in relation to the airplane stall condition This signal is compared with the flap position in the stall warning computer Whenever the angle of airflow sensor signal exceeds the flap position signal the computer applies 28V DC power to the control column shaker motor 1 Stall Warning Power Failure Light This amber light marked STALL WARNING OFF is on the overhead panel adjacent to the stall warning test switch It will illuminate to serve as a warning any time there is a failure of 115V AC and or 28V DC power and or to indicate vane heater malfunction The light will be on also at all times when the airplane is on the ground and external or APU power is on providing the stall warning test switch is not in the TEST position Power for the light is supplied from the 28V DC battery bus 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 40 DO NOT USE FOR FLIGHT 2 Test Indicator Rotates during test to indicate reliable inputs from stall warning senior and flap position transmitter 3 Stall Warning Test Switch Spring loaded to the NORMAL position and locked from t
100. tions arm the high energy dual ignition system In the GROUND position in addition to arming the ignition system the starter valve is energized and opens allowing the starter to accelerate the N2 rotor The FLIGHT position is used for inflight starting and provides I high energy ignition without engaging the starter On some aircraft a continuous ignition switch provides low energy ignition for conditions requiring continuous ignition such as icing conditions or periods of moderate or greater turbulence On the other aircraft low energy continuous ignition is provided anytime the ignition is in the FLIGHT position with the start lever in the IDLE position When the start lever is in the START position high energy ignition is provided See also CENTRAL FORWARD PANEL PO9 CONTROL STAND Engine start levers 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 44 DO NOT USE FOR FLIGHT 013 ALTERNATE FLAPS PANEL ALTERNATE FLAPS W 1 Switch Guard i off NED ue OUTED AN 1 2 Alternate Flap Master Switch E a S 3 4 Alternate Flap Switches I 2 Alternate Flap Master Switch Operates bypass valve for inboard and outboard trailing edge flaps and leading edge flaps and stats Turns on Standby System pump Arms alternate flap switches 3 4 Alternate Flap Switches These two switches on the overhead panel are adjacent to the alternate flaps master switch The switches marked I
101. 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 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 www captainsim com 57 DO NOT USE FOR FLIGHT clear area does not necessarily mean it is safe 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
102. tor 10 Oil Quantity Test Switch 1 2 3 Oil Quantity Instrument The oil quantity instruments measured in gallons indicate the usable quantity of oil remaining It is recommended to have at least 5 quarts before starting and at least 3 gallons when engines stabilize at idle RPM Normal oil consumption is between Vi U S pint per hour and one U S quart per hour in normal operation An engine which exceeds two U S quart per hour over a ten hour period shall be investigated 4 5 6 Oil Temperature Indicator Oil temperature is measured at the outlet of the fuel oil heat exchanger Maximum oil temperature for all operating conditions is 1209C Note Up to 1579C is allowed for a 15 minute period 7 8 9 Oil Pressure Indicator The normal operating oil pressures are 40 to 55 PSI 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 88 DO NOT USE FOR FLIGHT 1 Panel Fluor Lights Switch E 2 Circuit Breaker Control Switch 3 S O Panel White Background Lights Control 4 S O Panel Lights Control 5 5 S O Panel Red Table Lights Control 1 Panel Fluor Lights Switch Controls white fluorescent lights under light shield W07 DOOR ANNUNCIATOR PANEL 1 FWD Entry 1 6 7 11 1217 2 L Gear Door 3 9 Aft Airstair 4 Cargo V Closed 5 L Service Door 6 Nose Gear Door 7 Equip Access 8 Aft Entry 10 Tail Slid 11 Galley 12 FWD Cargo 13 R Gear Door 14 APU 15 Aft Carg
103. ture Indicators 6 Pneumatic Duct Pressure Indicator 8 Gasper Fan Switch 11 Auto Pack Trip Armed Light 12 16 18 22 Engine Bleed Valve Switches 13 20 Air Conditioning Pack Trip Off Lights 14 21 Bleed Air Trip Off Light 15 19 Pack Switches 17 Bleed Air High Temperature Light 2010 Captain Sim www captainsim com 79 DO NOT USE FOR FLIGHT 1 Air Conditioning Pack Reset Switch Operating the switch will restore normal operation of the air conditioning pack or engine bleed air supply after a trip by either an overtemp or an auto pack trip The air conditioning pack trip off lights will extinguish when the pack is reset After an overheat trip the reset switch will restore normal operation of the air conditioning pack and extinguish the overheat light after the pack has cooled below the overheat temperature 4 9 Cooling Doors Position Indicators A pointer on the indicator reflects cooling doors position 5 7 Pack Temperature Indicators Two indicators on the Second Officer s upper panel indicate left and right pack air cycle machine compressor discharge temperatures The temperature sensors are located between the compressor and the secondary heat exchanger of the respective packs The indicators are used to monitor pack operation Pack temperatures should be 30 40 C for optimum operation 6 Pneumatic Duct Pressure Indicator Indicates pneumatic duct pressure sensed at points indicated by dotted lines on panel Press
104. uct temperature ENG 3 Wing anti ice right supply duct temperature 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 48 DO NOT USE FOR FLIGHT 019 WING ENGINE AND COWL ANTI ICING PANEL 1 4 Wing Anti Ice Valve Position Light Green 1 2 3 4 2 3 Wing Anti Ice Switch Popol best cip 5 7 10 Engine Inlet Anti Ice Switches org NARVE 6 8 11 Engine Inlet Anti Ice Valve Position Lights Green 9 Anti Ice Valve Position Light Selector jort ENIE 2 ENGK mE a pr 6 7 a 9 10 11 1 4 Wing Anti Ice Valve Position Light The lights marked VALVE POS ENQ 1 ENG 3 are on the overhead panel The lights will illuminate if the position of the valves in the anti ice supply duct are in agreement with the wing anti ice switch positions and the anti ice valve position light selector is in the wing position 2 3 Wing Anti Ice Switch The switches are spring loaded to close from the momentary GRD TEST position When the switches are in the OPEN position the respective 13th stage anti ice bleed valve opens Thirteenth stage air flows through an ejector where it draws in and mixes with sixth stage air The mixed air flows through the respective wing anti ice shutoff valve which is also opened by the wing anti ice switch From the wing anti ice shutoff valve the heated air is ducted to the wind leading edges The landing gear safety switch prevents wing anti ice operati
105. ule The control module interprets this signal as a locked wheel signal as compared to the simulated wheel rotating signal and gives a full strength release signal to those wheel brakes The corresponding indicators will display REL In either test position the anti skid return valves will open Hydraulic fluid will bleed to return if the brakes are actuated or the parking brake is on during anti skid test A line connects the system A reservoir at the 2 5 gallon level with the tope of the system B reservoir to provide system B with pressurization make up fluid and thermal expansion 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 36 DO NOT USE FOR FLIGHT 3 Nose Gear Brake and Anti Skid Switch System deactivated 5 Main Gear Anti Skid Switch Turns off anti skid system System active only when landing gear lever is down or the nose gear is not locked up and parking brake is off This switch on the overhead panel is marked MAIN GEAR ANTI SKID and has ON OFF positions The switch is guarded in the ON position The main wheel anti skid protection is deactivated when the switch is in the OFF position The main wheel brakes are normally available with this switch in either the ON or the OFF position 7 10 Brake Released Indicator In air gear up all blank system deactivated In air gear down all rel On ground above 15 kts blank On ground below 15 kts nose re
106. ure monitored to indicate proper operation of bleed air system APU or external air source for engine starting and air conditioning 12 16 18 22 Engine Bleed Valve Switches A bleed valve is installed on each engine to permit shutting off the entire supply of bleed air from the engine into the pneumatic duct The valves are controlled by the bleed air switches on the Second Officer s upper panel one switch for 1 and one for 3 and two switches for 2 engine The valves on engines 1 and 3 will override closed in the event of bleed air overtemperature or if the respective fire selector is pulled 13 20 Air Conditioning Pack Trip Off Lights Amber lights marked TRIP OFF for each air conditioning pack are on the Second Officer s upper panel These lights will illuminate when an overheat condition occurs in the main distribution duct the air cycle machine ACM turbine inlet or the ACM compressor discharge duct 14 21 Bleed Air Trip Off Light Two square amber lights marked TRIP OFF are located adjacent to the 1 and 3 Engine Bleed Air Switches A bleed air overtemperature will cause the TRIP OFF light s to illuminate and the respective engine bleed valve s to automatically close The valve may be reopened and the light reset provided temperature is below trip off value by depressing the reset switch www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 80 U11 PRESSURIZATION SYSTEM PANEL 1 2 3 4
107. ximum operating airspeed 2 Airspeed Pointer Displays indicated airspeed derived from pitot static pressures 4 Cursor Control Positions cursor on scale to indicate reference airspeed selected LO5 RADIO MAGNETIC INDICATOR RMI 1 Synchronizing Annunciators 2 Synchronizing Knob 2 3 Compass Warning Flag 4 7 ADF VOR Selector Knob 5 6 ADF VOR Pointers 3 A radio magnetic indicator RMI is provided on each pilot s panel to furnish the radio and magnetic bearing information required for navigation The components of each RMI consist of an azimuth card a lubber line two ADF VOR pointers No 1 and No 2 two ADF VOR switches No 1 and No 2 a synchronizing knob a synchronizing annunciator and a compass warning flag The compass card rotates in a manner such that the heading of the airplane will always be read under a fixed reference index lubber line at the top of the instrument Also fixed indices are provided at 45 90 135 180 225 270 and 315 2010 Captain Sim www captainsim com 727 Captain FLIGHT MANUAL Part II Aircraft and Systems 10 DO NOT USE FOR FLIGHT The rotating compass card or azimuth card is graduated form O to 360 degrees clockwise in two degree increments The card is driven by a motor which receives signals from the directional gyro 3 Compass Warning Flag A compass warning flag on the lower right hand corner of the RMI is marked OFF The warning flag wil

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