Embraer E145 Cockpit Panels

Transcript

Embraer E145 Cockpit Panels The following pages depict the various instrument panels located in the cockpit of the Embraer E145 Regional Jet. Along with these depictions are text box captions that describe the function of most of the buttons and switches that control the various systems on the aircraft. Keep in mind that as aircraft modifications occur, such as ADs, Service Bulletins, etc., the captions may become inaccurate or incomplete. The captions are not all inclusive and are intended as a supplemental study aid to be used in conjunction with the appropriate approved aircraft systems and operations manuals. Because space is limited for the captions the use of acronyms and abbreviations is necessary. The table that follows lists the acronyms and abbreviations used that may not be readily discernable by the reader. Warning and Disclaimer Every effort has been made to make this information as accurate as possible, but no warranty or fitness is implied. The information provided is on an “as is” basis. The author shall have neither liability or responsibility to any person or entity with respect to any loss or damages arising from the information contained herein. - Captain Bill de Groh Abbrev. Meaning Abbrev. Meaning & and CCW Counter-clockwise _x Multiplier (4x = 4 times) Cmd Command Cmpt. Compartment < Smaller/Less/Below Com Communication > Greater/More/Above CVR Cockpit Voice Recorder A Ampere CW Clockwise A/C Aircraft DAP Digital Audio Panel A/I Anti-ice DC Direct Current ABV APU Bleed Valve DCP Display Control Panel AC Alternating Current Decr. Decrease(s) DFDR Digital Data Flight Recorder AEO All Engines Operating EBC Essential Bus Contactor AGL Above Ground Level EIC Essential Interconnection Contactor AHRS Attitude Heading Reference System EBV Engine Bleed Valve ECS Environmental Control System AMM Airplane Maint. Manual EDL Electrical Distribution Logic Amp Ampere EICAS Engine Indicating And Crew Alerting System AP Autopilot Elect. Electric(al) Approx. Approximately ESU Electronic Sequence Unit APU Auxiliary Power Unit F/A or FA Flight Attendant Auto Automatic FADEC Full Authority Digital Electronic Control BACV Bleed Air Check Valve FD Flight Director BC Battery Contactor FI Flight Idle BTC Bus Tie Contactor FO First Officer CA Captain CBV Cross Bleed Valve 25 February 2006, William May 2008 William de Grohde Groh Abbrev. Meaning Abbrev. Meaning Fpm Feet per minute Nm Nautical mile FSBY Forced Standby Mode O2 Oxygen Ft Feet OEI One engine inoperative Fwd Forward Pax. Passenger GCU Generator Control Unit PCA Power Control Actuator GI Ground Idle PCU Power Control Unit GMAP Ground Map Mode PFD Primary Flight Display GPC Ground Power Contactor PRSV Pressure Regulating and Shutoff Valve GPU Ground Power Unit Psi Pounds per square inch Grnd Ground PSU Passenger Service Unit GS Glideslope PTT Push-To-Talk Hdg Heading RCP Radar Control Panel Horiz. Horizontal Rcvr Receiver hPa hectopascals Rdr Radar HSCU Horizontal Stabilizer Control Unit REACT Rain Echo Attenuation Compensation Logic HSV High Stage Valve Ref. Reference(d) Hyd. Hydraulic RH Right Hand Hz Hertz (cycles per second) RTA Receiver/Transmitter/Antenna ICU Interphone Control Unit Sec. Second(s) Incr. Increase(s) SOV Shut Off Valve Kts Knots SPS Stall Protection System Lbs Pounds SRN Short Range Navigation LH Left Hand Sync. Synchronize(s) LRN Long Range Navigation Sys. System Mag. Magnetic TCS Touch Control Steering Man. Manual Temp. Temperature Max. Maximum Tgt Target MFD Multi-Function Display TL Thrust Lever Mic. Microphone TLA Thrust Lever Angle Min. Minimum or Minute V Volt Msg. Message WX Weather radar mode MSL Mean Sea Level Xmtr Transmitter Nav Navigation YD Yaw damper NiCad Nickel-Cadmium 25 February 2006, William May 2008 William de Grohde Groh EMBRAER 145 RIGHT MAIN INSTRUMENT & GLARESHIELD PANELS Rain Echo Attenuation Compensation Technique (REACT) •Pressing cycles antenna stabilization. When off STAB on PFD and OFF on RCP. •Pushed enables REACT •Avail in all mode except GMAP •Always selected when in TEST mode. •Used to invoke stabilization Trim mode •Calibrated Gain Range Select Buttons •In WX, REACT, & GMAP modes 5 to 300 nm available. •In FP mode 5 to 1000 nm available •On ground, after warmup, pressing 4x within 3 sec. inhibits FSBY Radar Control Panel (RCP) •Selects Target Alert Mode. Mode monitors for red (level 3) or greater beyond selected range & +/- 7.5º of A/C hdg. TGT label if target detected. •Radar in Forced Standby Mode (FSBY) when A/C on grnd and Radar Mode knob not set to OFF; FSBY label displayed. FSBY inhibits the xmtr and antenna scan; can override through the STAB button. •REACT – Automatic rcvr calibration to compensate for attenuation losses. RCT label displayed. A blue field indicates ranges where further compensation not possible. Active in all modes except GMAP. Tgts within blue field cannot be calibrated & should be considered dangerous. •Min. target depth of 5 nm •TGT label with no target •Calibrated Gain •Radar operational if FP mode selected. •TEST mode, auto set 100 nm •OFF – On-side controller slaved to cross-side controller; SLV displayed on RCP. •SBY – Standby mode. STBY label displayed. WAIT label displayed during 40-100 sec. warm-up. Cycles between 120º or 60º azimuth sweep for on-side AND cross-side displays. •Pushed – Calibrated Gain •WX – Weather detection mode. CA & FO RTA settings alternate on each sweep, CA’s on left sweep & FO’s on right. To get 100% duty factor one Radar Control Panel must be set OFF. WX label if rdr selected for display on MFD; otherwise TX label •Pulled – Manual gain active & VAR label displayed on PFD Interior Lights Control Panel •GMAP – Ground map mode. GMAP label displayed. •Antenna Tilt +/- 15º • Range indicators between +5º & -5º are expanded •FP – Flight Plan mode. Radar put in standby & no radar data presented. A singular display of nav data & a FLTPLN label displayed. Clock Avionic Switched DC Bus •TEST – Test pattern displayed with a TEST label. •Antenna beam width 7.9º Primary Flight Display (PFD) [Avionic Switched DC Bus] Digital Audio Panel (DAP) Foot Warmer Valve Gasper vent Switch altimeter ref. between Inches and HPa. Standard altimeter setting button Causes MFD to present PFD or EICAS displays from on-side IC-600. Switch on fwd side of yoke disengages nose wheel steering DG – AHRS hdg channel operates as free nonslaved gyro. SLVD – AHRS slaved to flux valve. PAX – reroutes audio signal from crew mic to pax cabin when any PTT is pressed. EMER – directly connects mic & headphones to com/nav radios. CA to Com/Nav 1, FO to Com/Nav 2. Allows slewing of hdg when AHRS not slaved to mag hdg of flux valve. Panel not present in AH900 equipped a/c. PSU O2 latches energized; 6 sec. timer Remote Start/Stop/Reset for chronograph Down – Off Center – Hot Mic Up - PTT CLOSED – Disables PSU O2 latches. Also resets O2 ON indicator & cabin signs after system activation on AUTO or MANUAL. •Pitch Trim with 3 sec. timer Touch Control Steering (TCS) •Disengages AP •While pressed allows manual maneuvering without disengaging the AP •When released syncs to new pitch attitude & vertical mode & maintains it. •Lateral control returned to previously selected mode. •Pressing & releasing after GS capture in APR mode with AP engaged releasing AP will return to ILS center beam. •Capt’s has priority Quick Disconnect Button •Disconnects AP; AUTOPILOT voice msg self canceled above 2500 ft with a valid radar altimeter •Inhibits stick pusher •Disconnects all trim systems while pressed. ADC – selects cross-side ADC. ADC 1(2) on PFD. PFD comparison montiors HDG Δ > 6 for a/c roll < 6 or >12 for a/c roll > 6 ROL Δ >6 PIT Δ >5 ATT if both ROL and PIT set ALT Δ 200 ft or more IAS Δ > 5 kts LOC Δ.> 1/2 dot (below 1200 ft.) GS Δ.> 2/3 do (below 1200 ft.) ILS if both LOC and GS set 25 February 2006, William May 2008 William de Grohde Groh AHRS – selects cross-side AHRS. ATT 1(2) & MAG 1(2) on PFD. SG – selects cross-side symbol generator (IC600). ADC 1(2), ATT 1(2), MAG 1(2), & SG 1(2) on PFD. •Slide, with mask stowed, tests the mask. Flow indicator turns yellow momentarily & OXY ON flag appears •Slide, with mask not stowed & left door closed, shuts off O2 to the mask. •Rotated CW to EMERGENCY position supplies 100% O2 under positive pressure •Pressed, tests regulator demand mechanism Vertical CDI Scaling per dot For CN: GS = 0.35 For FMS: ENR = 750’ TERM = 0.35 APPR = 0.35 VNAV = 250’ AUTO – PSU O2 latches energized & cabin signs on when cabin altitude > 14,000 ft. MANUAL – activates PSU O2 latches at any altitude. •N – O2/Air mixture based on cabin altitude; pure O2 above 33,000 ft. •100% - Pure O2 at all altitudes. Must be selected with EMERGENCY position for protective breathing Horizontal CDI Scaling per dot For CN: LOC = 1.25 VOR = 5 For FMS: ENR = 2.5 nm TERM = 1.0 (0.5 nm) APPR = 0.15 nm EMBRAER 145 CENTER MAIN INSTRUMENT & GLARESHIELD PANELS •Bank angle reduced from 27º to 14º in HDG mode . •Auto selected climbing > 25,000 ft & canceled < 24,750 ft in HDG mode. •Annunciated only in HDG Select mode Couples FD to nav source selected on flying pilot’s DCP. VOR/LOC if NAV selected and LNAV if FMS selected •Engages AP & YD Same as NAV but with higher gain. Also enable GS Mode. •Hdg Hold (ROL) holds present hdg when selected •Cycles between full rose HSI & sector format on PFD •Pressed again disengages AP but keeps YD •First press enters Elapsed Timer Mode •In sector format WX radar can be displayed •Start/Stop/Reset Allows CA’s or FO’s FD to control the AP Cycles between on-side VOR/LOC SRN source (green) or cross-side VOR/LOC SRN source (yellow) •Speed Hold Mode •Flight Level Change •Hdg Select (HDG) follows hdg bug •Vertical Speed Hold Mode •Allows hdg selection Cycles between on-side FMS LRN source (magenta) and crossside FMS LRN source (yellow) •Altitude Hold Mode •Pressing synchronizes hdg bug to current hdg Displays FD bars Master Warning Button •Allows crs selection •Engages YD •Pressing synchronizes selected course to VOR bearing Setting Knobs •Pressing again disengages both AP & YD Cycles between ground speed and time-to-go. Display Control Panel (DCP) OFF – Associated bearing pointer sources disabled NAV– Selects associated VOR as bearing pointer source Engine Indication & Crew Alerting System (EICAS) ADF – Selects associated ADF as bearing pointer source Standby Attitude Indicator •Pull to cage & rotate to adjust miniature airplane FMS – Selects associated FMS as bearing pointer source •Power warning flag Power off Caged •Rotation allows setting Radio Altimeter decision height Open motor winding Loss of power •Essential DC Bus 2 •On grnd, pressing activates IC-600 first level IBIT test. If held > 6 sec. activates IC600 second level IBIT test. EICAS test commanded from CA’s panel only. Multi Function Display (MFD) Standby Airspeed Indicator Standby Altimeter •In flight, pressing activates Radio Altimeter Test Backup Ess Bus Avionic Switched DC Bus Optional Integrated Standby Instrument System (ISIS) •Replaces the three electromechanical standby instruments with a single LCD screen •CAGE button resets attitude only •Inhibits EGPWS when approaching airports not covered by EGPWS database thus avoiding unwanted terrain alerts. •STD button sets standard barometer setting •The + or – keys adjust brightness •Rotary knob allows altimeter setting •Striped bar in button when pressed •Cancels LANDING GEAR voice msg. in case of Radio Altimeter loss only when flaps < 22º •TEST/RESET function enabled by pressing ON, waiting 1 sec. then pressing ARM •RESET function deactivates ELT after manual or auto activation Some EICAS messages inhibited Rotation allows setting airspeed bug values Rotation allows pilot to scroll through EICAS messages if display limit of 15 exceeded. •Striped bar in button when pressed •Flight Level Change Mode •Striped bar extinguishes if TLs advanced or flaps set above 22º , or gear down & locked •Climb •ON – Activates ELT •ARM – Allows automatic activation 100 +/- 10 ft Indicates when emergency/parking brake is applied Flashing ELT alert light indicates ELT transmitting •Powered from Essential Bus 2 TEST displayed 240 kts / 0 to 10,000 ft 240 kts to 270 kts / 10,000 to 12,000 ft 270 kts / 12,000 to 17,377 ft “LANDING GEAR” voice msg activated when: •Flaps < 22º, one TL < 45º (59º if OEI), and Radio Altitude < 1200 ft. Can be canceled. •Flaps set at 22º, one TL < 45º (59º if OEI), and Radio Altitude < 1200 ft. Cannot be canceled. 0.56M / 17,377 to 37,000 ft •Descend -2,000 fpm / 37,000 to 12,000 ft -2,000 to -1,000 fpm / 12,000 to 10,000 ft -1,000 fpm / less than 10,000 ft •Flaps set at 45º. Cannot be canceled. FMS Roll Cmds for “Direct To” changes •30 bank up to 20K •Dec. linearly above 20K up to 32K •20 bank above 32K •Roll rate limited to 3/sec Takeoff: V1-15 to 400’ RA Landing: 200’ RA to 3 sec. after W-on-W 25 February 2006, William May 2008 William de Grohde Groh FMS Roll Cmds for “Leg-to-Leg” changes •27 bank up to 20K •Dec. linearly above 20K up to 32K •15 bank above 32K •Roll rate limited to 3/sec EMBRAER 145 CENTER PEDESTAL •Disconnects CA’s elevator control from FO’s Inhibition Logic •Takeoff •Active > V1-15 •Deactive. RA > 400 ft, or < 60 kts, or > 1 min. •Landing •Valid < 200 ft •Deactve. WOW > 3 sec., or > 1 min. •Checks takeoff configuration warning by simulating TLs advanced •If ok, “TAKEOFF OK” voice message •Mechanical gust lock secures only the elevator •Electromechanical gust lock does the same thing but uses a solenoid and locking pins installed in the horizontal stabilizer. Powered by DC Bus 2 & incorporates an amber indication light on the glareshield. •If fail, “TAKEOFF ___” voice message & NO TAKEOFF CONFIG EICAS msg FLAPS SPOILERS TRIM •CA’s side has all AP servos & stick pusher BRAKES •Cannot be reset in flight •Disconnects CA’s aileron control from FO’s Illuminates when disconnection mechanism activated •FO’s side has roll trim actuator & artificial feel unit •Cannot be reset in flight Illuminates when disconnection mechanism activated Thrust Reversers have 3 locking systems. The Primary & Secondary are electrically controlled & hydraulically actuated. The third lock is completely electric. Loss of electric power latches locks closed MAX – max. takeoff rating mode at any time THRUST SET – FADEC controls engine to achieve N1 target IDLE – GI~ 64% N2, FI~ 68% N2 MAX REV – max. reverse thrust. Doors cmd’d open when TLs at soft detent (TLA 14º) •Cmds outboard spoiler panels to open when: If OEI or one reverser not deployed FADEC will only cmd reverse from good engine if TL requesting reverse and OEI TL set to IDLE TLA of both engines < 50º Flaps < 13º •No intermediate positions Thrust Lever Friction Knob •Electrically controlled thru DC Bus 1 & 2 •Electrically actuated & controlled •Hydraulically actuated •DC Bus 1 & 2 •If one channel fails, remaining motor can drive flaps at half speed •Pulling actuates emergency brakes (no anti-skid) •3º asymmetrical limit disables system for duration of flight •Pull & rotate to set parking brake •Always have toe brakes applied when setting or releasing to prevent hydraulic fluid transfer Thrust Mode select buttons (no ATTCS) •All 4 brakes supplied by Hyd Sys 2 proportional to handle displacement with no protections •Pedal brking •Hyd Sys 1 supplies outbd brakes •Hyd Sys 2 supples inbd brakes •Anit-skid protection > 10 knots wheel speed •Locked wheel protection through anti-skid system > 30 knots wheel speed •Touchdown protection allows braking 3 seconds after touchdown, or when wheel speed > 50 knots. 25 February 2006, William May 2008 William de Grohde Groh Joystick controls MFD designator •With control column held full back, momentary push actuates SPS test (stick shaker, clacker, & stick pusher) •TEST button illuminated after an unsuccessful test or if system has not been tested. •TEST button inhibited inflight till 30 sec. after landing, above 70 KIAS, or with gear not downlocked. •Ice compensation of SPS inhibited for 5 min. after takeoff. •Ice compensation reset if: airborne & flaps set to 45º. SPS ICE SPEED msg remains,or on ground after pressing TEST button. SPS ICE SPEED msg cleared. CON thrust if one of the following: •Cuts out SPS channel 1 or 2 in case of failure •>300 ft AFL & gear not locked down, or •Striped bar in button when pressed Limited to OEI only Pusher inhibited On grnd (except for test) •Below 0.5 G •While Quick Disconnect button pressed •< 200 ft if RA failed •Any Cutout button pressed •> 200 knots •At least 1 channel inop • >1700 ft AFL CLB or CRZ thrust if one of the following: •>500 ft AFL, gear not locked down, AEO, or • >1700 ft AFL and AEO •TO thrust •T/O-1 for the EMB 145 •T/O RSV for the EMB 135/140 EMBRAER 145 AFT CENTER PEDESTAL Control Display Unit (CDU) of Universal UNS-1K Flight Management System (FMS) •Actuates yaw trim •3 sec. timer in case of trim knob failure Pitch control wheel inhibited if any Vertical Mode selected in FD •Cuts out (pressed) or enables (released) HSCU Main or Backup Pitch Trim systems •Striped bar in button when pressed Manually controls roll attitude when AP engaged Actuates pitch trim through the HSCU backup channel Actuates roll trim by repositioning neutral position of aileron command ARINC Communications And Reporting System (ACARS) Printer Must be in DN position in AUTO mode In MAN Mode: •Controls pneumatic outflow valve by metering vacuum pressure to that valve •-1500 fpm to +2500 fpm in MAN mode •On (pressed) •Dumps cabin up to 14,500 ft +/-500 ft Landing Gear Freefall Compartment On floor between co-pilot’s seat and control pedestal •ON inscription when pressed Electrical Override Switch •Inhibited in MAN mode NORMAL – Extension/retraction controlled by LGEU DOORS – Bypasses LGEU to open nose landing gear doors GEAR DOORS – Bypasses LGEU extending landing gear while keeping nose landing gear doors open. Free-Fall Lever Initial movement operates the free fall selector valve relieving hydraulic pressure and connecting the lines to the return. Further movement mechanically unlocks the landing gear uplocks allowing the gear to free-fall to the down and locked position. 25 February 2006, William May 2008 William de Grohde Groh •Auto mode (released) or Manual mode (pressed) •MAN inscription illuminated when pressed EMBRAER 145 OVERHEAD CHANNEL A •ELEC EMERG. – Loss of all generators in flight. The batteries supply the Central & Essential Buses, sharing the load & not being charged. The Inverter, Shed and DC Buses not energized. •ELEC EMERG. ABNORMAL – The EDL configured for an electrical emergency when not required. The generator supplied DC Buses are isolated from the battery supplied Central & Essential Buses & the batteries are not being charged. •ELEC ESS XFER FAIL – The EDL failed to configure for an electrical emergency when required. DC Bus 1 and/or DC Bus 2 are not isolated from the batteries & the batteries are not being charged. Erases data only on the ground with parking brake set. Only the manufacturer can recover the “erased” data. •Connects (pressed) or disconnects (released) the GPU to/from the electrical system. •GPU AVAIL inscription illuminates when operating GPU is physically connected to aircraft; does not indicate good power. •Inscription goes out when button pressed & GPU connected to electrical network. Priority over alll batts & gens. •Striped bar in button when pressed. •Verify 26.0 - 29.0 V before selecting. Ground Service Bus is energized when BATT 1 & 2 OFF (BC1 & BC2 open) and GPU AVAIL inscription in GPU button (GPC open). Cockpit dome, courtesy, galley, cabin, lav, bagg, & service cmpt. lights •On (pressed), overrides auto transfer to electrical emergency configuration & ensures batteries powering only Essential Buses regardless of EDL. Isolates batteries from DC Buses. (EBC 1 & 2, and EIC closed, BC1 and BTC 2 open). • Auto (released), power contactors operate automatically according to EDL. (EBC 1 & 2, and EIC open, BC1 and BTC 2 closed). •Striped bar in button when pressed. OVRD – BTCs kept closed regardless of EDL provided no overcurrent detected by one of 5 GCUs. AUTO – BTCs controlled by EDL. OFF – Opens BTCs regardless of EDL. •Connects (pressed) or disconnects (released) the 250 VA/400 Hz Static inverter to/from the system. •Inverter supplied from DC Bus 1 & provides 115 vAC to 115 vAC Bus. 115 VAC BUS OFF msg. if Bus deenergized •Tests integrity of CVR •Green STATUS LED illuminates for 1 sec. if test is good DC Bus 2, 2 hr recording, Jack for a 600 ohm headphone to monitor audio signals & tones. •2 sec. 800 Hz tone for successful CVR test •3 sec. 400 Hz tone for successful CVR erase 5g switch •Connects (pressed) or disconnects (released) the 28 vDC, 400 Amp enginedriven generators to/from respective DC Bus •Gens online when N2 > 56.4% •Cycling resets GCU if generator is running. •If current > 400 A, GEN 1 (2, 3, 4) OVLD msg. •Striped bar in button when released. •Connects (pressed) or disconnects (released), 28 vDC 400 Amp, APU StarterGenerator when APU rotor speed > 95% + 7 sec. •BATT 2 used to start APU •Striped bar in button when released. OFF – BC kept open disconnecting battery from electrical system. AUTO – BC controlled by EDL •Two 24vDC, 44 amp-hour NiCad batteries, located in battery cmpt. (Nose left side). •BATT 2 supples power for APU starting, while BATT 1 isolated to provide stabilized power to voltage transient sensitive equipment. •Both BCs open if GPU connected to system •During an Electrical Emergency both batteries can supply Essential Buses for 40 min., which includes 3 APU starts. •If batt > 70C, BATT 1 (2) OVTEMP msg. OVRD – Closes Shed Bus contactors while on ground with at least one generator on line. AUTO – EDL controls Shed Bus contactors. OFF – Opens Shed Bus contactors manually regardless of EDL. •Powers TCAS II & GPWS •Striped bar in button when released. •Connects (pressed) or disconnects •Connects (pressed) or disconnects (released) the Backup Battery to/from the electrical system. •24 vDC, 5A lead acid battery, in fwd avionic cmpt. in front of FO. •Backup Batter y charged when button pressed with BATT 1 in AUTO • BKUP BATT OFF BUS msg when button released. •Supplies Backup Hot Bus, providing stablized power for the GCU's protective function in case of a shortcircuit or near zero system voltage. 25 February 2006, William May 2008 William de Grohde Groh (released) the com/nav supplied by Avionics Switched Buses. •Allows prevention of undesirable voltage transients during APU battery starts on the ground. •Striped bar in button when released. •ON – Emergency lights ON using the 4 dedicated batteries; 15 min. duration; batteries not charging - EMER LT NOT ARMED •OFF – Emergency lights turned off if EMER LTS button on F/A Panel in NORM; batteries not being charged - EMER LT NOT ARMED. (Switch that turns on the lights is the only switch that can turn them off) •ARM – Emergency lights off & batteries being charged; lights illuminate automatically in Elec. Emerg. EMBRAER 145 OVERHEAD CHANNEL B FUEL 1 (2) LOW LEVEL •Fuel remaining ranges from 463 to 584 lbs. •Illuminates red upon fire detection •Pulling will send close cmd to: FUEL IMBALANCE Hyd. Pump SOV •Comes on at 800 lbs difference Bleed Air SOV •Goes off at 100 lbs difference Engine Intake Lip Anti-ice SOV Fuel SOV (on Hot Bus). Remember H.A.L.F. •Rotate CCW fires bottle A & CW fires bottle B •Fire bell can be canceled but visual warning cannot as long as fire signal exists. LOW 1 – opens cross-feed valve & shuts off left selected electric fuel pump OFF – closes cross-feed valve & returns electric fuel pump to normal operation •Selects which electric fuel pump will be operating continuously for that engine LOW 2 – opens cross-feed valve & shuts off right selected electric fuel pump •Remaining pumps of associated side are kept in auto standby •To cross-feed select tank with lower fuel •If fuel pressure < 6.5 psi remaining two pumps come on line & will cycle with inoperative pump causing “clicking” in relay box. •Switch powered by Ess DC Bus 2 •Fuel Pump A on associated Essential Bus •Fuel Pump B on cross-side Essential Bus •Fuel tank temperature taken from left tank only & displayed on MFD, FUEL page. •Fuel Pump C on associated DC Bus • FUEL TANK LO TEMP msg. indicates fuel temp. inside left tank is < -40ºC ON – Energizes selected pump •E1 (2) FUEL LO TEMP msg. indicates engine fuel temp. (leaving FCOC) is < 5ºC. OFF – De-energizes selected pump •Pressure refueling to full leaves 7.9 U.S. gallons below fuel tank capacity; must fuel over wing to get that last 7.9 U.S. gallons. •To de-fuel left tank set XFEED to LOW 2 and Tank 1 - ON with de-fuel SOV open Interphone Control Unit (ICU) •Allows interphone com between FA and pilots. •Generates a cabin chime to call FA •Generates cabin chime •On FA’s Call Panels: PILOT •Allows interphone com between pilots and FA in case of normal mode failure •Striped bar when button when pressed •Illuminated CABIN and CAB EMER buttons on ICU, and PILOT and EMER PILOT annunciators on Attendant’s Call Panel •Striped bar in button when pressed Same as CABIN button except on F/A’s Call Panels: EMER PILOT •Turns on or off the associated lights DFDR begins recording when RED BCN switch in ON or A/C is airborne 25 February 2006, William May 2008 William de Grohde Groh . EMBRAER 145 OVERHEAD CHANNEL C Permits testing the fire detection system •Class C baggage compartment On grnd, if pressed & held > 10 sec. APU auto shut down in the same manner as if the FUEL SHUTOFF button was pressed. •Two cargo extinguisher bottles located in rear Electrical Compartment If necessary to repeat fire test, wait at least 6 sec. In the case of APU fire detection, the APU will NOT auto shutdown in flight but will auto shutdown if A/C on the ground. •Causes APU Normal Shutdown, and closes APU Fuel Feed SOV in wing stub (APU FUEL SOV CLSD EICAS msg) & closes APU Main Fuel Solenoid Valve (at APU) •Discharges APU fire bottle •Does NOT illuminate •30 sec delay, per EPC, before pressing OFF – De-energizes FADEC, closes APU Fuel Feed SOV in wing stub (APU FUEL SOV CLSD EICAS msg) & closes APU Main Fuel Solenoid Valve (at APU) R.emoves APU indications & alarms when RPM < 10%, cmds APU shutdown. ON – Energizes FADEC (Ess DC Bus 2 or HOT Bus 1), opens APU Fuel Feed SOV, enables APU indications & alarms on EICAS. FADEC performs self-test. START – Initiates start cycle •Two smoke detectors – Maintenance must reset •Sight glass in lavatory •Button illuminated if smoke detected in baggage compartment •When pressed Discharges both bottles; the high rate & metered discharge bottles Deactivates baggage compartment fans (if not previously deactivated by smoke detection) 50 minutes of protection •Sends stop request to FADEC, and •Closes APU Fuel Feed SOV in wing stub (APU FUEL SOV CLSD EICAS msg) & closes APU Main Fuel Solenoid Valve (at APU) •Striped bar in button when pressed APU Normal Shutdown •Sends stop request to FADEC and closes the APU Main Fuel Solenoid Valve (at the APU). APU start cycle: 3% (0% airborne): ignition energized & Main Fuel Solenoid Valve opens 50%: Starter de-energized Abnormal APU Shutdown: In Flight: Overspeed, underspeed, loss of speed data, failure to start, accelerate, or light, external short, or FADEC failure or loss of signal. On Ground: Fire (APU FIRE aural warning of 10 sec. or more), EGT over-temperature, Loss of EGT, high oil temperature, low oil pressure, oil pressure switch short. 70%: ignition exciter de-energized 95%+7sec: Max Fuel Solenoid Valve energized, pneumatic & electrical power available If no EGT rise then 1 auto restart (swing start): starter de-energized at 20% & re-energized at 5%. OFF – De-energizes ignition system AUTO – Active FADECs control ignition system automatically RESET – Resets FADEC & clears faults ALTN – Alternates FADEC in control •Inoperative if held > 3 sec. One channel for grnd start (14% N2) Both channels for airstart (10% N2) Auto-relight (above 53% N2) ON – Cmds FADECs to continuously activate both ignition channels; A & B. Enabled on grnd only with TLA < 50º  First flt of day 1st press – enables T/O Mode setting Cold eng. starts SAT or oil < 5ºC 2nd press – REF TO TEMP External air or Crossbleed start 3rd press – REF A-ICE Contam.runway TO AND < 10ºC. 4th press – stores values. Data accepted if REF TO TEMP within +/-10ºC & both engines running Moderate or > turb. or heavy precip. STOP – Cmds FADEC to shut engine down provided TLA is IDLE RUN – Allows normal engine operations START – Initiates engine start cycle, and automatically switches FADEC from the FADEC that had the last successful engine start. If held > 3 sec. knob becomes inoperative. In this case select STOP and reset the FADEC to reset knob •T/O Mode: DEC – ALT T/O-1, INC – T/O-1 or T/O (135/140 only) •REF TO TEMP: DEC – decreases temp. setting, INC – increases temp. setting •REF A-ICE: DEC – OFF, INC - ON Turns on/off wing landing lights •Turns on/off both taxi lights & nose landing light, respectively •Taxi & nose landing lights automatically extinguished when nose gear not down & locked, regardless of switch position •Shed Bus 2 must be energized (OVRD with < 3 generators on line) 25 February 2006, William May 2008 William de Grohde Groh EMBRAER 145 OVERHEAD CHANNEL D •Illuminates red upon fire detection Automatic Rudder Shutoff Through Speed Switch •Pulling will send close cmd to: •Rudder limiter for high speed Hyd. Pump SOV •Rudder Sys 1 auto shutoff > 135 kts to reduce rudder authority at high speed Bleed Air SOV Engine Intake Lip Anti-ice SOV •If Sys 2 fails Sys 1 comes back on line automatically with EICAS message Fuel SOV. •RUDDER OVERBOOST if neither Sys shuts off > 135 kts Remember H.A.L.F. •Rotate CCW fires bottle A & CW fires bottle B •Fire bell can be canceled but visual warning cannot as long as fire signal exists. Rudder Hardover Protection (for low speed) •Both Sys 1 & 2 auto shutoff Force on any pedal > 130 lbs, and Rudder deflected > 5º to opposite side, and Both engines running (N2 > 56.4%) •Inhibited at higher speeds due to speed switch logic that reduces rudder authority. Rudder deflection will not achieve 5º •Inhibited with OEI operation •Enables (pressed) or disables (released) associated hydraulic system pressure to both aileron actuators. •Enables (pressed) or disables (released) associated rudder hydraulic actuator. •Striped bar in button when released •Striped bar in button when released •Hyd. Pump driven by engine accessory gear box Priority Valve •Provides 3000 + 100 psi @ 9.2 gal/min •Only on Hyd Sys 1 •E1 (2) HYD PUMP FAIL msg < 1600 psi or N2 < 56.4% •Priority valve closes during ldg gear operation with only electric hyd. pump supplying system, to isolate ldg. gear giving priority to the flight controls. •HYD 1 (2) LO QTY msg if reservoir < 1 liter •Reservoir capacity 6 liters 24 hr parking brake or 6 full emerg. brake applications Accumulator Emerg. Brake Accumulator An accumulator is basically a “hydraulic battery” storing hydraulic energy & providing surge protection. •Closes (pressed) or opens (released) engine-driven Hyd. Pump SOV •Hyd. Pump continues to run if engine running •Striped bar in button when released OFF – Electric Hyd. Pump off ON – Electric Hyd. Pump on. Provides 2900 + 100 psi @ 1 gal/min AUTO – Electric Hyd. Pump in standby ready to come on line if engine driven pump outlet pressure < 1600 psi or N2 < 56.4% HYD SYS 1 (2) FAIL msg if hyd. pressure < 1300 psi Control logo lights on underside of horizontal stabilizer 25 February 2006, William May 2008 William de Grohde Groh Control cockpit dome lights at a fixed intensity •Turns signs on or off with a chime •Both signs are automatically activated when pax O2 dispensing units open EMBRAER 145 OVERHEAD CHANNEL E •Off (released) or selects auto mode (pressed) of wing and/or horizontal stabilizer A/I valves. L pneumatic supplies horizontal. •Off (released) or permits (pressed) automatic activation of engine lip anti-icing •OPEN inscriptions indicates engine lip antiice valve open •OPEN inscription means valves open with system cmd’d open or at least one valve open with system not cmd’d open. •Striped bar in button when released •Source is a valve upstream of HSV with no temperature control (i.e. EBVs can be closed & still operate) •Striped bar in button when released •Can be open on the grnd without limitation •On (pressed) or off (released) •Off (released) or auto mode (pressed) •Striped bar in button when released •Striped bar in button when released •Defog mode if no ice detected - maintains windshield at 26 C. If ice cond. anti-ice mode holds windshield at 43 C •Pitot 1/2, Pitot/Static 3, AOA 1/2, ADS Static Ports 1,2,3,4, & Press. Static Ports 1/2 are heated with at least one engine N2 > 56.4% •3 sensors, 1 temp control, 1 overheat protection, 1 spare •Separate logic ensures Pitot/Static 3 & Press. Sys. Static Port 2 heated in any flight condition •Should be off when OAT > 10ºC on grnd •TAT 1 & 2 heat when TLs > 65º TLA (~78.5 to 82.5% N1) and assoc. engine A/I system on, OR anytime inflight. ENG – Inlet A/I valve open with engine running. On grnd. with wheel speed > 25 kts an ICE CONDITION will open WING and TAIL A/I valves. •EICAS msg inhibited during takeoff & landing. AUTO – Allows automatic operation of bleed air anti-ice system. On grnd. no A/I valves open. But at wheel speeds > 25 kts an ICE CONDITION will open all A/I valves (ENG, WING, & TAIL) Permits testing wing, horizontal stabilizer, and engine anti-ice valves by simulating an ice condition on ice detectors 1 & 2. ALL – Turns on entire bleed air anti-ice system in flight regardless of ice detection. On grnd inlet A/I valve open & when wheel speed > 25 kts the WING and TAIL A/I valves open, regardless of ice condition. •Pressed- right pack automatically controlled between 18ºC and 29ºC by Digital Temperature Controller •Pull for manual operation •ATTD – Control transferred to FA Panel where green ON light illuminates. •Pressed- left pack automatically controlled between 18ºC and 29ºC by Digital Temperature Controller. •On (pressed) or off (released) AIRBORNE ONLY •Pull for manual operation •Gasper ON with DC Bus 2 energized on grnd regardless of button position •On (pressed) or off (released) •Striped bar in button when released •Controls both recirc fans. On grnd during hot soak days must be OFF; during cold soak days must be ON •Supplies gaspers, and ventilation for the O 2 cyl. cmpt., relay boxes, and rear elect. cmpt. •Striped bar in button when released CLOSED – Closes CBV OPEN – Opens CBV (CROSS BLD OPEN) AUTO – Automatic operation of CBV •Opens (pressed) or closes (released) the Pack Pressure Regulating and SOV (PRSOV) •Electrically controlled, pneumatically actuated •Striped bar in button when released •On grnd, with main door open & pack < 227ºC PRSOV operates in high mode, other times in low mode •EBV (PRSOV) open (pressed) only when bleed air demanded or closed (released). •PACK 1 closes with A/I on below 24,600 ft provided PACK 2 operating •Engine inlet lip A/I taken upstream of HSV •LEAK inscription indicates duct leakage. •HSV (14th stage) open during low thrust, crossbleed starts, and A/I operations •Max thrust (takeoffs & go-arounds) with EBVs open, Pack Valves automatically close by FADEC when: •9th stage air joins 14th stage, both with BACVs, then thru precooler upstream of EBV  OEI up to 9700’ MSL & TAT >19ºC at S.L. decreasing to -5ºC at 9700’ MSL •EBV closed by Fire Handle or automatically with intense hot air leak (BLD VLV CLOSED) AEO up to 1700’ AGL & TAT >19ºC decreasing to -5ºC at 9700’ MSL •Used for engine start, ECS, pressurization, & ice protection •Must reset Pack Valves after auto shutdown •If both Pack Valves closed in flight the ram air valves open & recirculation fans auto shutdown. •Opens (pressed) or closes (released) ABV. Striped bar in button when pressed •On the ground the ram air valves are always closed, regardless of Pack Valve position. LOW – 80 strokes/min HI – 140 strokes/min “BLEED TEMP” on ECS page of MFD is taken downstream of precooler. •APU bleed air not sufficient for A/I TIMER – Intermittent operation, 2 strokes at high speed with 8 sec. delay •Auto closes if LH EBV or RH EBV with CBV are open to prevent reverse flow. BACV downstream of ABV for same purpose. Dry windshield protection parks blades until knob cycled to OFF to reset. •Electrically controlled & pneumatically actuated Maximum speed for operation - 160 KIAS 25 February 2006, William May 2008 William de Grohde Groh •OPEN inscription indicates ABV in open position EMBRAER 145 FORWARD CENTER PEDESTAL DAU 1: Forward aircraft & engine 1 parameters. Ch A: Ess DC Bus 1 & Backup Ess Bus (default) Ch B: DC Bus 1 DAU 2: Aft aircraft & engine 2 parameters. Ch A: Ess DC Bus 2 & Backup Ess Bus (default) Ch B: DC Bus 2 Radio Management Unit (RMU) •Pressing allows Data Acquisition Unit (DAU) Channel B to supply both IC-600 •Striped bar in button when pressed First press: Splits the NAV window into two windows. Top window displays active VOR frequency. The lower window, with the DME Label, displays the active DME frequency in VHF format. An H (DME Hold) is displayed in the DME window and on the PFD to show DME not paired with active VOR/ILS freq. The DME may then be tuned directly by pressing the LSK beside the DME window. Second press: Displays the TACAN channel format and will allow tuning to the DME portion of any TACAN station. Third press: Reverts NAV window to normal DME operation. 25 February 2006, William May 2008 William de Grohde Groh NORM – RMU tuning available EMERG – tuning through RMU inhibited Activates internal self-test of component selected with yellow cursor box. COM transceiver – Hold button 2 sec. DME, ATC, and ADF – Hold for 5 to 7 sec. Tuning Backup Control Head (TBCH) Allows alternative means of tuning Com 2 and Nav 2 NAV (VOR/ILS) – Hold for 20 sec.