G U L F S T R E A M G 4 5 0
Condensed Notes
Revision 4.0
T A B L E O F C O N T E N T S
For corrections, suggestions, or to be added to the revision distribution list please email: [email protected]
Thank you,
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
T A B L E O F C O N T E N T S
A C R O N Y M N S ...... 3
S Y S T E M PAGE
G E N E R A L ...... 4 D O O R S ...... 4 L I G H T I N G ...... 4 F I R E P R O T E C T I O N ...... 4 C O M M U N I C A T I O N S ...... 5 E L E C T R I C A L ...... 5 A P U ...... 6 P O W E R P L A N T ...... 7 F U E L ...... 8 H Y D R A U L I C ...... 8 L A N D I N G G E A R ...... 9 F L I G H T C O N T R O L S ...... 9 P N E U M A T I C S ...... 10 A I R C O N D I T I O N I N G ...... 10 P R E S S U R I Z A T I O N ...... 11 I C E A N D R A I N ...... 11 O X Y G E N ...... 12 F L O W S ...... 12 P L A N E V I E W A V I O N I C S ...... 13 S O P ...... 15
PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 2
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
S O U R C E S GSCP GROUND SERVICE CONTROL PANEL HOPS HARDOVER PROTECTION SYSTEM GULFSTREAM HMG HYDRAULIC MOTOR GENERATOR FLIGHT SAFETY INTERNATIONAL HUD HEAD UP SYSTEM www.CODE7700.com IDG INTEGRATED DRIVE GENERATOR IVAN LUCIANI I-NAV INTEGRATED NAVIGATION IRU INERTIAL REFERENCE UNIT LAN LOCAL AREA NETWORK A C R O N Y M S LEER LEFT ELECTRONIC EQUIPMENT RACK LPV LOCALIZER PERFORMANCE WITH VERTICAL GUIDANCE LRU LINE REPLACEABLE UNIT ACC AIR CONDITIONING CONTROLLER MAU MODULAR AVIONICS UNIT ACM AIR CYCLE MACHINE MCDU MULTIFUNCTION CONTROL DISPLAY UNIT ACP AUDIO CONTROL PANEL MWS MONITOR AND WARNING SYSTEM ACS AIR CONDITIONING SYSTEM NBPT NO BREAK POWER TRANSFER ADC AIR DATA COMPUTER ND NAVIGATION DISPLAY ADM AIR DATA MODULE NIC NETWORK INTERFACE CARD ADS AIR DATA SYSTEM PDP POWER DISTRIBUTION PANEL AUTOMATIC DEPENDENT SURVEILLANCE POP PILOT OVERHEAD PANEL AEER AUX ELECTRONIC EQUIPMENT RACK PTU POWER TRANSFER UNIT AFCS AUTOMATIC FLIGHT CONTROL SYSTEM REER RIGHT ELECTRONIC EQUIPMENT RACK AGM ADVANCED GRAPHICS MODULE RVDT ROTARY VARIABLE DIFFERENTIAL TRANSDUCER ASC AIRCRAFT SERVICE CHANGE SAV STARTER AIR VALVE ASCB AVIATION STANDARD COMMUNICATIONS BUS SEP STANDBY ELECTRICAL POWER ATN AERONAUTICAL TELECOMMUNICATIONS NETWORK SFD STANDBY FLIGHT DISPLAY BAC BLEED AIR CONTROLLER SVO START VALVE OPEN BAS BLEED AIR SYSTEM SVS SYNTHETIC VISION SYSTEM BIT BUILT-IN TEST SV-PFD SYNTHETIC VISION PRIMARY FLIGHT DISPLAY BITE BUILT-IN TEST EQUIPMENT TCS TOUCH CONTROL STEERING BPCU BUS POWER CONTROL UNIT TLA THRUST LEVER ANGLE BTMS BRAKE TEMP MONITORING SYSTEM TROV THRUST RECOVERY OUTFLOW VALVE CAS CREW ALERT SYSTEM VGP VNAV GLIDE PATH CCD CURSER CONTROL DEVICE VSD VERTICAL SITUATION DISPLAY CDU CONTROL DISPLAY UNIT
CMC CENTRAL MAINTENANCE COMPUTER
CMF COMMUNICATIONS MANAGEMENT FUNCTION CPC CABIN PRESSURE CONTROLLER CPCP CABIN PRESSURE CONTROL PANEL CPOP CO-PILOT OVERHEAD PANEL CPSP CABIN PRESSURE SELECTOR PANEL NOTES CPIP CABIN PRESSURE INDICATOR PANEL
CSD CONSTANT SPEED DRIVE DAU DATA ACQUISITION UNIT DC DISPLAY CONTROLLER DMU DATA MANAGEMENT UNIT DU DISPLAY UNIT EBDI ELECTRONIC BEARING AND DISTANCE INDICATOR ECS ENVIRONMENTAL CONTROL SYSTEM ECU ELECTRONIC CONTROL UNIT EDS ELECTRONIC DISPLAY SYSTEM EDM EMERGENCY DESCENT MODE EEC ELECTRONIC ENGINE CONTROL EVM ENGINE VIBRATION MONITOR
EVS ENHANCED VISION SYSTEM FGCP FLIGHT GUIDANCE CONTROL PANEL FGC FLIGHT GUIDANCE COMPUTER FCOC FUEL COOLED OIL COOLER FPV FLIGHT PATH VECTOR FMU FUEL METERING UNIT FSECU FLAP/STAB ELECTRONIC CONTROL UNIT FQSC FUEL QUANTITY SIGNAL CONDITIONER FWC FAULT WARNING COMPUTER GCU GENERATOR CONTROL UNIT GP GUIDANCE PANEL
PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 3
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
▪ STROBE ▪ THE SYSTEM DEFAULTS TO THE TOP STROBE LIGHT 1 G E N E R A L LIGHT ▪ IT ONLY GOES TO THE BOTTOM STROBE IF THERE IS DIMENSIONS: FAULTS A PROBLEM WITH THE TOP STROBE ▪ LENGTH 89’ 3” ▪ A TRIPPED FAULT INDICATOR COULD BE A BAD TOP ▪ WINGSPAN 77’ 4” BULB, A MOMENTARY ELEC SPIKE, OR A HARD ▪ TAIL HEIGHT 25’ 2” LANDING ▪ WHEELBASE 39’ 1” X 13’ 8” ▪ ANN LIGHT ▪ TESTS ALL BULBS EXCEPT 5: TEST - FIRE HANDLES (2) ▪ MIN TAXI STRIP FOR 1800 TURN 55’ 3” - FUEL CONTROL SWITCHES (2) WEIGHTS: - PAX OXYGEN ▪ MAX RAMP 75,000 LBS (ASC 016) ▪ CABIN RATE OF CHANGE – FULL DESCENT ▪ MAX TAKEOFF 74,600 LBS (ASC 016) ▪ MAX LDG 66,000 LBS / 58,500 LBS (ASC 007C) 4 F I R E P R O T E C T I O N ▪ MAX ZERO FUEL 49,000 LBS / 48,000 LBS (ASC 008) ▪ COMPONENTS ▪ SMOKE DETECTION ▪ BAG COMP SPEEDS: ▪ VMO / MMO 340 KTS / M.88 MT ▪ SMOKE EVAC HANDLE ▪ DEFLATES BAG DOOR SEAL ▪ VTURB >10,000 FT 270 KTS / 0.75 MT ▪ VTURB <10,000 FT 240 KTS ▪ ENG FIRE DETECTION ▪ TWO FIRE LOOPS ▪ FLAPS 100/200/390 250 / 220 / 180 KTS (0.60 MT) ▪ FIRE DETECTOR CONTROL UNIT ▪ MINIMUM MANEUVERING SPEEDS FLAPS 00/100/200/390 200 / 180 / 160/ VREF +5 KTS ▪ PYLON OVERHEAT ▪ 2500F
▪ VLE / VLO / EMERG 250 / 225 / 175 KTS (0.70 MT) ▪ APU FIRE DETECTION ▪ SINGLE LOOP ▪ VA 206 KTS ▪ SENSES FIRES AND ▪ TIRE LIMIT 195 KTS FAULTS ▪ VMCG / VMCA / VMCL 109 / 106 / 99 KTS ▪ PAX COMP AND TAIL ▪ THERMAL SWITCHES ▪ INOP TRIM (MACH/ELEC) 0.75 MT COMP O’HEAT ▪ 1500F ▪ INOP STAB / JAMMED ELEV 270 KTS / 0.75 MT ▪ PAX COMP ▪ LEER, REER, AEER ▪ INOP YD ABOVE 20,000 FT 210 KTS MINIMUM AND TAIL ▪ FWD, L AFT, CENTER AFT, R AFT FLOOR ▪ MAX DEMONSTRATED X-WIND 24 KTS COMP O’HEAT ▪ AFT EQUIPMENT ALTITUDES: DETECTION APU: ▪ MAX OPERATING: 45,000 FT ▪ FIRE ▪ SEALED TUBE ▪ HELIUM GAS ▪ INOP YD AND MACH TRIM 41,000 FT DETECTION 0 0 ▪ FLAPS 10 / 20 25,000 FT
0 ▪ HIGH GAS ▪ LDG GEAR / FLAPS 39 20,000 FT PRESSURE ▪ MAX FIELD ELEV 14,500 FT / 15,000 FT (ASC 068) ▪ HEAT PRODUCES HIGH ▪ SENSOR AUTO-SHUTDOWN PRESSURE
▪ LOW GAS 2 D O O R S PRESSURE ▪ LOOKS FOR RUPTURED ▪ EMERGENCY EXITS ▪ PRIMARY ▪ MAIN ENTRANCE DOOR SENSOR TUBE ▪ NO AUTO-SHUTDOWN (LAND EVAC) ▪ CABIN WINDOWS (4) ▪ FIRE BELL ▪ SECONDARY ▪ BAGGAGE DOOR (GND)
▪ APU FIRE TEST ▪ 6 LIGHTS, 2 CAS MSGs 3 L I G H T I N G APU FIRE ▪ SUBSYSTEMS ▪ FLIGHT DECK LIGHTING APU FIRE DETECTOR FAIL ▪ CABIN LIGHTING ▪ A TEST WILL NOT SHUTDOWN THE APU ▪ SERVICE COMPARTMENT LIGHTING ▪ FIRE BELL WILL ONLY SOUND ON THE GND ▪ EXTERIOR LIGHTING ▪ BEFORE STARTING THE APU CONFIRM ▪ EMERGENCY LIGHTING FIRE BOTTLE DISCHARGE, L-R NOT DISPLAYED ▪ EXTERIOR ▪ BEACON, STROBE, NAV, ICE INSP, LOGO, RAMP, ESSENTIAL AC-BUS FAIL
LIGHTING LANDING, PULSE, TAXI, WING TIP TAXI, AND WHEEL ENG: WELL LIGHTS ▪ SENSORS ▪ AT THE 7TH AND 12TH STAGES ▪ STROBE LIGHT – 2 IN EACH LOCATION MOUNTED ON RAILS ▪ AT THE IDG ▪ STROBE LIGHT FAULT INDICATOR ▪ AT THE BLEED AIR DUCT ▪ SHEATHS OF STAINLESS NAV LIGHTS - 2 IN EACH LOCATION ▪ FRONT ENG MOUNT ▪ TAXI LIGHTS (3) – AUTO OFF ON GEAR RETRACTION STEEL SURROUNDED BY GLASS OXIDE MATERIAL. ▪ ENG ANTI-ICE DUCT (L ENG) ▪ LANDING LIGHTS – AUTO OFF AT 18000’ HEAT AFFECTS CURRENT ▪ L ENG LOOP A, R ENG LOOP B – L ESS DC ▪ LANDING LIGHT OPERATION LIMITED TO 5 ▪ L ENG LOOP B, R ENG LOOP A – R ESS DC MINUTES WHEN ON THE GND ▪ EMERGENCY ▪ OVERWING EGRESS, UNDERWING EGRESS, EMERG ▪ FIRE HANDLE ▪ FUEL – AT THE TANK, FUEL SHUTOFF VALVE LIGHTING LIGHT BATTERIES, EMERG CONTROL SWITCHES, SHUTS OFF: ▪ HYD – HYD SHUTOFF VALVE BETWEEN THE HYD AND MAIN ENTRANCE DOOR EMERG LIGHTS RESERVOIR AND THE HYD PUMP ▪ WHEN ON E-BATTS ONLY THE MASTER LIGHTING ▪ ELEC – AT THE IDG
CONTROL KNOB FUNCTIONS
PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 4
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
▪ 2 FIRE BOTTLES ▪ HALON 1301 (CF3Br) ▪ CVR ▪ 120 MIN (L AND R) ▪ 600 PSI AT 700F ▪ COCKPIT VOICE RECORDER UNIT – TAIL COMP – SOLID ▪ “BOTTLE DISCHARGE” CAS WHEN AT 200 PSI STATE DIGITAL MEMORY, WATER ACTIVATED BEACON – ▪ RIGHT BOTTLE IS #1 SHOT INTERNAL BATTERY ▪ LEFT BOTTLE IS #2 SHOT ▪ 2.5 G IMPACT SWITCH ▪ INTENTIONAL DISCHARGE: INTO THE ENG ▪ DFDR ▪ 25 HRS OF DATA – TAIL COMP NACELLE ▪ DFR/CMC EVENT SWITCH ON OVERHEAD ▪ THERMAL DISCHARGE: INTO THE TAIL (RECORDS -30 SEC + 1 MIN) COMPARTMENT ▪ ELT ▪ AEER ▪ L/R ENGINE ▪ 121.5 MHz, 243.0 MHz, and SAT FREQ 406.025 MHz FIRE TEST ▪ 72 HR TRANSMIT TIME ▪ LAT LONG INTERFACE FROM IRS “EIGHT LIGHTS”
6 E L E C T R I C A L 6 LIGHTS, 2 CAS MSGs: ▪ LOOP A LIGHTS (2) LOOP B ▪ MASTER WARN LIGHTS (2)
▪ FIRE HANDLE LIGHTS (1) ▪ L/R FUEL CONTROL SWITCH LIGHTS (1)
▪ THREE-CHIME AURAL WARNING TONE
▪ ENGINE FIRE CAS MESSAGE (1)
▪ ▪ ENGINE FIRE LOOP ALERT CAS MESSAGE (1)
▪ ENGINE FIRE DETECTION FAULT TEST
“EIGHT LIGHTS”
NOTE: CHECKS THE FAULT DETECTION EIGHT (8) AMBER LIGHTS: CIRCUIT OF THE FIRE ▪ TEST LEGEND IN THE FAULT TEST SWITCH ▪ 1 HMG (SEP) ▪ G450, 5 Kva, 115 V, 400 HZ, 3 PHASE DETECTION CONTROL ▪ FAULT LEGENDS IN THE LEFT/RIGHT LOOP A/B AC UNIT, NOT THE LOOPS. SWITCHES ▪ 1 E-INV / “STBY” INVERTER ▪ 1 Kva, 115 V AC, PHASE A ▪ TWO-CHIME AURAL CAUTION TONE ▪ 1 (OR 2) 60 Hz CONVERTER ▪ 115 V, 60 HZ, SINGLE PHASE AC ▪ FIRE DETECTION LOOP FAULT CAS MESSAGE ▪ 2 BATTERIES ▪ 24 V, 24 CELL, 45 AMP HR, LEAD ACID ▪ 2500F ▪ TAIL COMPARTMENT (2) ▪ 2 BATTERY CHARGERS ▪ 38 AMP CHARGE MODE, 40 AMP TR THERMAL ▪ R AFT FLOOR NEAR HOT AIR DUCTING (3) MODE SWITCHES ▪ CENTER AFT FLOOR NEAR HOT AIR MANIFOLD (2) ▪ 2 EXTERNAL POWER ▪ AC (115 V, 400 HZ) & DC (28 V - 300 - RED CAS ▪ L AFT FLOOR NEAR HOT AIR DUCTING (3) AMPS) ▪ 2 BPCUs BUS POWER CONTROL UNIT 0 ▪ AFT BAGG / AEER (2) ▪ 150 F ▪ 3 GENERATORS ▪ 40 Kva, 115 V, 3 PHASE AC ▪ CABIN FLOOR BENEATH MED AREA (5) THERMAL ▪ 4 E-BATTS ▪ 24 V, 9 AMP HR, LEAD ACID SWITCHES ▪ LEER (3) - AMBER CAS ▪ REER (2) ▪ 4 GCUs ▪ 2 IDG ▪ ▪ PORTABLE FIRE ▪ HALON (8.2 LBS) – OIL, GREASE, AND ELEC FIRES. 1 APU GEN EXTINGUISHERS ▪ WATER AND ANTIFREEZE (7 LBS) – PAPER OR ▪ 1 HMG (SEP) CLOTH FIRES. ▪ 5 AC BUSES ▪ 2 MAIN AC BUSES, L/R ▪ 2 STBY AC BUSES, L/R ▪ LAV FIRE ▪ INTEGRATED FIRE DETECTOR AND ▪ 1 ESS BUS EXTINGUISHERS EXTINGUISHING UNIT (9 CU IN EXT AGENT) ▪ ▪ CAPPED FUSIBLE ALLOY (1700F) 5 TRUs 115 V AC TO 28 V DC – 250 AMPS ▪ ▪ DISCHARGE INTO TRASH BINS (3-15 SEC) 2 ESS TRUs, L/R ▪ 2 MAIN TRUs, L/R ▪ 1 AUX TRU 5 C O M M U N I C A T I O N S ▪ 5 AC SOURCES ▪ 2 IDGs, L/R ▪ VOICE ▪ VHF (3) – TRANSCEIVERS AND ANTENNAS, ▪ 1 APU GEN MCDU OR CCD (8.33 OR 25 KHz INCREMENTS) ▪ 1 HMG ▪ HF (2) – TRANSCEIVERS AND COUPLER, MCDU ▪ 1 EXT AC ▪ HF ANTENNA ATTACHMENT MAKES ACFT AN ANTENNA ▪ 7 DC BUSES ▪ 2 MAIN DC BUSES, L/R ▪ SATCOM ▪ 2 ESS DC BUSES, L/T ▪ VHF #3 NORMALLY USED FOR DATA ▪ 2 BATT BUSES, L/R ▪ ACP ▪ EMER BUTTON ▪ BYPASSES ACP ▪ 1 GND SERVICE BUS ▪ DIRECT LINK BETWEEN ▪ 8 DC SOURCES ▪ 2 BATTs, L/R HEADSET AND COMM #1 ▪ 5 TRUs ▪ SELCAL ▪ VHF (3) AND HF (2) ▪ 1 EXT DC ▪ 4 LETTER DECODER CARD IN EACH AUDIO INTERFACE UNIT (AIU)
PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 5
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
AC POWER SOURCES CONTROLLED AND PROTECTED BY GCUs (4) 60 HZ CONVERTER 115 V, 60 HZ ▪ GALLEY POWER ▪ CSD IDGs (2) 40 kVA, 115 V, 3 PHASE AC (1 0R 2) AUTO SHED ▪ APU GEN 40 kVA, 115 V, 3 PHASE AC IDG LOAD LIMIT ▪ WHEN AMBIENT >1100F/43.50C, LIMIT IDG LOAD 0 ▪ HMG 5 kVA, 115 V, 400 HZ, 3 PHASE TO 45% (18kVA) TO KEEP FUEL TEMP <95 C ▪ L & R STBY AC BUSES ▪ AUX TRU ▪ L ESS DC BUS 7 A P U – H O N E Y W E L L 3 6 – 1 5 0 ▪ R ESS DC BUS ▪ SINGLE SHAFT, CONSTANT SPEED GAS TURBINE ENGINE AC POWER FLOW: 1) IDG/APU GEN/EXT AC ▪ ACCESSORY ▪ APU GEN ▪ “GENERALLY, AC POWERS HEATERS, 2) L & R MAIN AC BUSES GEARBOX DRIVES: LUBRICATION PUMP (OIL PUMP) ▪ INTEGRAL OIL RESERVOIR (2 QTS) MOTORS, AND CHARGERS” 3) L & R STBY AC BUSES ▪ SPEED SENSOR ECU L MAIN AC BUS ▪ L ESS AC BUS ▪ EXHAUST SECTION ▪ EJECTOR PUMP DRAWS AMBIENT AIR WHICH ▪ L ESS TRU L ESS DC BUS LOWERS EGT AND NOISE ▪ L MAIN TRU L MAIN DC BUS ▪ ELEC – L OR R BATT BUS APU MASTER SWITCH ECU ▪ AUX TRU (PRIMARY) ▪ ECU MODES ▪ NON-ESS (GND) ▪ L BATT CHARGER ▪ 38AMP CRG MODE ▪ ESS (AIR) ▪ 15 MIN AFTER LND ▪ 40AMP TR MODE ▪ FUEL COMPONENTS ▪ L TANK/L PUMP ▪ X FLOW & R PUMP ▪ R ESS AC BUS R MAIN AC BUS “ BURNS 200 PPH ▪ FUEL SHUTOFF VLV ▪ APU MASTER ▪ R ESS TRU R ESS DC BUS (30 GAL PER HR)” ▪ APU FUEL CONTROL ▪ FIRE “5 TRUs; 7 COUNTING ▪ R MAIN TRU R MAIN DC BUS ▪ APU GEN ▪ 40Kva, 115 V, ▪ GND 95% + 4 SEC THE BATT CHARGERS” ▪ AUX TRU (SECONDARY) ▪ ▪ R BATT CHARGER ▪ 38AMP CRG MODE 3 PHASE AC AIR 99% + 2 SEC ▪ 40AMP TR MODE ▪ APU AIR LOAD CNTL VLV MANIFOLD & ▪ L/R ECS (PACKS) TRUs (5) – 250 A EA 115 V AC TO 28 V DC ISO VLV: “AVAIL 100% RPM + 90 SEC” ▪ ENG START ▪ STARTER LIMITS – BATTERY ▪ 3 ATTEMPTS AUX TRU PRIORITY: 1) L ESS DC BUS WHEN OPERATING THE 28 V DC MOTOR MOUNTED ▪ 1 HR COOL DOWN “LEFT BEFORE RIGHT, 2) R ESS DC BUS HMG THE AUX TRU CAN TO THE DRIVESHAFT OF THE ESSENTIAL BEFORE 3) L MAIN DC BUS POWER BOTH THE L AND ACCESSORY GEARBOX MAIN” 4) R MAIN DC BUS R ESS DC BUSES. ▪ STARTER LIMITS – DC CART ▪ 3 ATTEMPTS WITH 15 MIN COOL DC POWER SOURCES: DOWN IN BETWEEN ▪ MAIN BATTERIES (2) ▪ 24 V, 45 AMP HR ▪ APU START ▪ 1 HR COOL DOWN
“2 APU START ▪ LEAD-ACID ▪ AUX PUMP ▪ CONSECUTIVE STARTS LIMIT 6 AT 10 MIN INTERVALS ATTEMPTS + 30 MIN” ▪ L & R ESS DC BUSES ▪ MAX ALTITUDE / LOAD <0.85 MT FL370 / 100% (40kVA) ▪ GSB (R BATT ONLY) ▪ MAX ALTITUDE / LOAD >0.85 MT ≥ FL300 / 85% ▪ E-BATTS (4) ▪ L & R E-BATTS ▪ L & R EMERG DC ▪ GUARANTEED START ALTITUDE ≤ FL370 - 24 V, 9 AMP HR BUSES ▪ MASTER ON: 1) ECU PERFORMS BIT - LEAD-ACID ▪ ESS FLT INST BUS (“READY” FLASHES – BULB CHECK) - ACTIVATES IF ESS ▪ IRUs (3) 2) OIL TEMP SENSED DC BUS HAS < 20 V ▪ FWD & AFT 3) APU DOOR OPENS (650 OR 270) ▪ EMERG LTS E-BATTS 4) FUEL SHUTOFF VLV OPENS ▪ AVIONICS E-BATTS ▪ CAPT AUDIO PANEL 5) “READY” LIGHT (15 SEC) (2) POWER ▪ CLOCKS (2) ▪ START BUTTON: 1) APU STARTER (LEFT BATT) ▪ GEAR HANDLE AND LIGHTS 2) 5% - APU FUEL CONTROL SHUTOFF VLV ▪ EBDI “100% RPM = 62,000 RPM” OPENS & IGN ▪ SFD 3) 7% - “READY” LIGHT GOES OUT ▪ MCDU 1 – STBY ENG INST AND FUEL 4) 46-60% - STARTER CUT-OUT MAX EGT: 973O (START) ▪ MCDU 3 – BACKUP RADIO (COM,NAV,XPDR 1) 5) 95% - IGN CUT-OUT 747O (RUNNING) ▪ GND SERVICE BUS 6) 95% + 4 SEC – GEN ON ▪ GND ▪ R MAIN BATT ▪ FUELING PANEL MAX RPM: 107% 7) 100% + 90 SEC – AIR AVAIL ▪ EXT DC ▪ ENG OILER ▪ STOP BUTTON 1) OVERSPEED SIGNAL TO ECU (107%) ▪ WHEEL WELL LTS 2) FUEL CONTROL UNIT SHUTS OFF FUEL ▪ AIR ▪ R MAIN DC BUS ▪ BTM ANTI-COL LT TO APU ▪ UTILITY LTS 3) BIT TEST ▪ SWITCHES (3) ▪ FWD EXT ACCESS 4) SURGE CONTROL VALVE CYCLES ▪ TAIL COMPARTMENT 5) <35% RPM, ECU CLOSES INLET DOOR ▪ REMOTE REFUELING 6) ECU MONITORS EGT AND RPM FOR 5
MIN ▪ ▪ MAIN DOOR CLOSED, AND AUTO OFF 7) AFTER 5 MIN “APU MASTER” CAS ▪ FWD ACCESS DOOR CLOSED, AND DISPLAYED ▪ TAIL COMPARTMENT DOOR CLOSED ▪ SURGE CONTROL VALVE ▪ PREVENTS COMPRESSOR STALLS BPCUs (2): ▪ L & R NETWORKS ▪ > 16,500 FT OPENS AT 60% RPM “LOCATED IN THE LEER ▪ POWER DISTRIBUTION
AND REER” ▪ POWER PROTECTION
STBY INV / 28 V DC T0 1 kVA, 115 V AC ESS AC BUS, PHASE A
(E-INV)
PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 6
G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS
8 P O W E R P L A N T: R O L L S – R O Y C E T A Y – 6 1 1 – 8 C ▪ ENG OIL ▪ R ENG OIL TANK – 15.5 PINTS (10.8 USABLE) ▪ MEDIUM BYPASS TURBOFAN ▪ L ENG OIL TANK – 14.5 PINTS (10.8 USABLE) ▪ 13,850 LBS OF THRUST AT SEA LEVEL ▪ LUBRICATES THE ROLLER/ THRUST BEARINGS AND ▪ THE RIGHT ENGINE IS THE CRITICAL ENGINE GEARS ▪ HP AND LP COMPRESSOR SECTIONS ARE DRIVEN BY THEIR OWN COAXIAL ▪ PRESSURE REGULATED (200 PSI) SHAFTS/SPOOLS (SHAFT WITHIN A SHAFT) – BEARINGS ▪ TEMPERATURE CONTROLLED VIA FCOC ▪ CLOCKWISE ROTATION ▪ OIL PUMP DRIVEN BY THE ACCESSORY GEARBOX ▪ OIL COOLING VIA FUEL-OIL HEAT EXCHANGER ▪ FUEL-OIL HEAT EXCHANGER (FCOC), IDG FCOC ▪ 75% OF LP COMPRESSOR “FAN AIR” BYPASSES ▪ CHECK OIL BETWEEN 5-30MIN AFTER SHUTDOWN ▪ 25% HP SECTION COMBUSTION CHAMBER - LAST FLIGHT OF THE DAY ▪ BYPASS AIR AND COMBUSTION AIR ARE MIXED BY A CRENELATED - 14 CUMULATIVE HRS FLANGE ▪ ENG OIL REPLENISHING SYSTEM – 14 PINTS ▪ LP / INNER ▪ 3 STAGE LP COMPRESSOR SECTION – ENG FRONT ▪ OIL TANK OIL QUANTITY TRANSMITTER OIL SPOOL DRIVEN BY 3 TURBINE STAGES – AFT ENG PUMP FCOC OIL TEMP TRANSDUCER OIL ▪ INLET GUIDE VANES DIRECT LP AIR IN THE FILTER (DPI BYPASSES AT 30 PSI) ENG BEARINGS, COMPRESSOR TO REGULATE PRESSURE RADIAL DRIVE, AND ACC GEARBOX SCAVENGE ▪ HP / OUTER ▪ 12 STAGE HP COMPRESSOR SECTION DRIVEN BY 2 PUMPS MAGNETIC CHIP DETECTORS OIL TANK… SPOOL TURBINE STAGES ▪ AIR TURBINE ▪ APU AIR ▪ STARTER IS CONNECTED ▪ FIXED STATORS ARE BETWEEN EACH COMPRESSOR STARTER ▪ EXTERNAL AIR TO THE ENG ACCESSORY STAGE ▪ CROSSBLEED GEARBOX AND TURNS THE ▪ COMBUSTI0N ▪ 10 COMBUSTION LINER ASSEMBLIES HP SECTION OF THE ENG CHAMBER ▪ 10 FUEL SPRAY NOZZLES ▪ SHOULD CLOSE AT 41- ▪ TWO IGN PLUGS – LINERS 4 & 8 O’CLOCK POSITIONS 44% HP ▪ ACCESSORY ▪ HIGH SPEED GEARBOX ON THE HP COMPRESSOR ▪ NORMAL ▪ START MASTER ▪ THE EEC PROTECTS DRIVES ▪ LOW SPEED GEARBOX ON THE LP COMPRESSOR START ▪ FUEL CONTROL AGAINST OVERTEMPS SWITCH AND OVERSPEEDS ▪ ENG FUEL ▪ TANK BOOST PUMPS (ELEC) FUEL SHUTOFF SYSTEM VALVES LP PUMP FUEL-OIL HEAT EXCHANGER ▪ ALTERNATE ▪ CRANK ▪ CREW SELECTS IGN FUEL FILTER LOW PRESSURE SWITCH (15 PSI) HP THE ELEC FUEL START MASTER ▪ THE EEC DOES NOT PUMP FUEL FILTER FUEL METERING UNIT HP CONTROL (EEC) IS ▪ FUEL CONTROL PROTECT START FUEL SHUTOFF VALVE FUEL FLOW TRANSMITTER A COMPONENT SWITCH FUEL SPRAY NOZZLES (10) OF THE FADEC ▪ THE LP PUMP CAN SUCTION FEED THE ENG
▪ FADEC / ▪ THE EEC IS AT THE HEART OF THE FADEC ▪ FUEL CONTROL ▪ HP FUEL SOV CLOSES – CUTS OFF ALL FUEL TO EEC ▪ EACH EEC HAS DUAL CHANNELS SWITCH – OFF THE SPRAY NOZZLES ▪ EACH EEC RECEIVES INPUT FROM THE 3 MAUs AND ▪ EEC CHANNEL CHANGE THE 3 ADMs ▪ IGN OFF ▪ EACH EEC OUTPUTS TO THE FWCs AND CMC ▪ QUICK RELIGHT POSSIBLE BY RETURNING SWITCH ▪ AT >35% HP RPM A DEDICATED GEN (3 PHASE AC, TO RUN PERM MAGNET ALTERNATOR (PMA), RECTIFIED BY ▪ GND OPS KEEP ▪ 60% - 72% LP RPM PROHIBITED >10 SEC THE PSU INTO 28 V DC) POWERS THE FADEC AND EEC OUT OF ZONE: ▪ AUTOMATIC PROTECTION IF PARK BRAKE IS SET
▪ EEC ▪ PRIMARY CONTROL MODE LP% HP% TGT TIME CONTROL - USES HP FOR IDLE (LOW OR HIGH) START – GND/AIR - - 7000C / 780C0 - MODES - USES EPR ABOVE IDLE OVR SPD/TEMP 96.5 101.6 8200C 20 SEC ▪ ALTERNATE CONTROL MODE – LP RPM – TAKEOFF IN TAKEOFF 95.5 100.6 8000C 5 / 10 MIN ALT IS PROHIBITED MAX CONT 95.5 97.5 7150C - ▪ REVERSE THRUST CONTROL MODE – LP RPM THRUST REV 65.0 - - 30 SEC ▪ “SOFT REVERSION” – EEC REVERTS TO LP
▪ “HARD REVERSION” – CREW SELECTS LP ENG GND START: O ▪ IDLE ▪ FLAPS > 22 ▪ MAX TAILWIND / X-WIND 25 KTS CONTROL – ▪ LANDING GEAR DOWN ▪ MAX TGT TO START 2000C HIGH IDLE ▪ WOW IN THE AIR 0 ▪ MIN OIL TEMP -40 C ▪ REMAINS IN HIGH IDLE FOR 5 SEC AFTER LANDING PERFORM CRANK CYCLE (SEE ▪ OIL TEMP <-100C ▪ THRUST ▪ ELEC CONTROLLED QRH), TURN GEN OFF REVERSERS ▪ HYDRAULICALLY OPERATED 0 0 ▪ 2 LOCKING LATCH MECHANISMS ▪ START SYNOPTIC 800 TGT SCALE (NORM 1000 ) ▪ 3 START CYCLES OF 3 MIN EACH ▪ MECHANICAL SPRINGS HOLD T/Rs SHUT, HYDRAULIC ▪ STARTER DUTY PRESSURE UNLOCKS THE HOOKS ▪ 15 SEC BETWEEN START CYCLES ▪ MAX REVERSE – 65% LP DECREASES TO 55% ▪ AFTER 3 CYCLES DELAY 15 MIN
BETWEEN 60 AND 50 KTS (30 SEC MAX) ▪ START TGT 7000C ▪ IDLE REVERSE BY 60 KTS ON LANDING ENG AIRSTART: ▪ INOP T/Rs - ADD 600 FT TO THE ACC-STOP DIST ▪ ALTITUDE PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 7 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ENG FUEL TEMP: 10 H Y D R A U L I C ▪ MINIMUM -400C ▪ MAXIMUM / TRANSIENT +950C / 1300C (15 MIN) ▪ OAT >1100F / 43.50C LIMIT IDG LOAD TO 45% (18kVA) FUEL TANK TEMP: ▪ MINIMUM -400C ▪ MAXIMUM +540C OIL TEMP: ▪ MIN FOR START -400C ▪ MIN FOR THROTTLE ADVANCE -300C ▪ MIN FOR TAKEOFF THRUST +200C (QRH) ▪ MAX TEMP / TRANSIENT +1050C / +1200C (15 MIN) OIL PRESS – MIN: ▪ TAKEOFF / MCT / IDLE 30 PSI / 25 PSI / 17 PSI 9 F U E L ▪ WING FUEL ▪ 29500 LBS OF FUEL ▪ 4370 GAL TANKS ▪ FIVE ▪ SEPARATED BY RIBS COMPARTMENTS AND JOINED BY O THE WING 3 BAFFLES ▪ 6 DRAINS DIHEDRAL FORMS A NATURAL ▪ VENTS GRAVITY FLOW ▪ QTY PROBES (20) ▪ 5 V – CAPACITORS TOWARDS THE ▪ TEMP SENSOR (LEFT ▪ MAX+54OC WING ROOT HOPPER) ▪ MIN -40OC ▪ TEST ▪ 7000/7000/14000 ▪ LEFT SYSTEM ▪ RESERVOIR – ▪ 6.4 GAL (4.4 FOR LEFT, 2.0 18.4 GAL STORAGE FOR AUX) ▪ HOPPER TANK ▪ 190 GAL (1283 LBS) ▪ FULL SHOWN AT 2.8 GAL LOW LEVEL PROBE – ▪ FLAPPER VALVES ▪ MANIFOLD – ▪ MIN 2.75 GAL 650 LBS IN HOPPER ▪ EJECTOR PUMPS DISTRIBUTION OVERFLOW THE ▪ SHUTOFF VALVE ▪ CLOSED BY FIRE HANDLE HOPPER TANK ▪ FILTER (PUMP ISOL FROM RES) ▪ HYD FLUID-TO-FUEL MANIFOLD HEAT EXCHANGERS ▪ RIGHT ▪ RESERVOIR ▪ 1.5 GAL ▪ FQSC ▪ “FUEL QUANTITY SIGNAL CONDITIONER” SYSTEM ▪ FULL SHOW AT 0.7 GAL ▪ PROCESSES SIGNALS FROM PROBES 7.5 GAL ▪ MIN 0.7 GAL ▪ REPORTS QUANTITY TO MAUs ▪ MANIFOLD – ▪ CONTROLS AUTO REFUEL PROCESS DISTRIBUTION ▪ VENTILATION ▪ FORWARD AND AFT VENT DUCT ▪ SHUTOFF VALVE ▪ CLOSED BY FIRE HANDLE ▪ VENT PLENUM ▪ FILTER (PUMP ISOL FROM RES) ▪ FLOAT-OPERATED VENT / RELIEF VALVES MANIFOLD ▪ NONRELIEVING FLOAT VENT VALVES ▪ ENG DRIVEN HYD PUMPS ▪ 3000 PSI ▪ OVERBOARD LINE VENT INLET AND FLUSH VENT ▪ 20.5 GAL/MIN – TAKEOFF INLET/OUTLET (RAM AIR INLET) ▪ 14.5 GAL/MIN – FLT IDLE ▪ 10.5 GAL/MIN – GND IDLE ▪ BOOST PUMPS ▪ L/R MAINS ▪ L/R ESS DC 16 PSI MIN ▪ L/R ALT ▪ L/R MAIN DC ▪ ELEC DRIVEN AUX HYD PUMP ▪ 3000 PSI ▪ FUEL SHUTOFF ▪ CONTROLLED BY THE FIRE HANDLE (ESS DC) ▪ 1 OR 2 GAL/MIN (ASC) VALVES ▪ FAIL FROZEN ▪ L & R HEAT ▪ IN THE L & R FUEL HOPPERS EXCHANGERS ▪ APU SHUTOFF ▪ CONTROLLED BY THE APU MASTER (ESS DC) VALVE ▪ FAIL FROZEN ▪ AUX PUMP ▪ ARMED TO ACTIVATE WHEN L SYS/PTU PRESS <1500 PSI AND BRAKE >10O,WOW – GND ▪ FILTRATION ▪ GRAVITY FUELING SCREENS ▪ BOOST PUMP INLETS ▪ PTU ▪ ARMED TO ACTIVATE WHEN L SYS PRESS <1500 PSI NOTE: ▪ FUEL FILTER – PRIOR TO FUEL METERING UNITS G450 FUEL FILTERS (FMUs) ▪ 3000 PSI WILL NOT BYPASS ▪ 10 GAL/MIN - 5 PSI DIFFERENTIAL – FUEL FILTER L-R CAS - 55 PSI DIFFERENTIAL – FUEL PRESSURE LOW L-R ▪ PREVENTS AUTO ▪ L HYD LOW (<1 GAL) CAS PTU OPERATION ▪ R HYD HOT (>1040C) ▪ FUEL ▪ CROSSFLOW (ESS DC) ▪ PRESSURIZED FUEL ▪ HMG ▪ POWERED BY L ▪ 5kVA, 115 V, 400 Hz AC BALANCING ▪ INTERTANK (ESS DC) ▪ VALVE BETWEEN SYS OR PTU HOPPERS ▪ ACCUM ▪ LEFT SYSTEM ▪ 1200 PSI ▪ 400 LB IMBALANCE ▪ ≥ 60500 LBS PRECHARGE – SHOCK ▪ RIGHT SYSTEM ▪ 1200 PSI ▪ 2000 LB IMBALANCE ▪ ≤ 55000 LBS ABSORPTION ▪ AUX SYSTEM ▪ 1200 PSI PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 8 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ GEAR ▪ GEAR UP ▪ GEAR HORN SYSTEM COMPONENT UNSAFE ▪ < 345 FT ▪ SILENCE AVAIL IF EMER LEFT RIGHT PTU AUX WARNING ▪ TLA < 5O FLAPS < 22 O ELEVATOR ●● √ √ ▪ DUMP VALVE, ▪ ELEC MOVES THE DUMP SHUTTLE VALVE TO THE STALL BARRIER ●● √ √ IF PRESSED HYD FLUID POSITION FROM THE NITROGEN GAS AILERONS ●● √ √ EXTENSION POSITION SPOILERS (FLT & GND) ●● √ √ ▪ REMOVES HYD PRESS FROM DE-SPIN SYSTEM. IF GND SPOILER SERVO ●● √ √ GEAR PINS ARE LEFT IN AND THE HANDLE IS RAISED RUDDER ●● √ √ THE DE-SPIN SYSTEM APPLIES BRAKE PRESSURE. TO YAW DAMP ●● √ √ RELEASE THE BRAKE PRESSURE BEFORE LANDING L THRUST REV ● √ THE DUMP VALVE MUST BE PRESSED. R THRUST REV ● √ ▪ PARK BRAKE ▪ 1700 PSI MIN TO SET (3000 PSI RECOMMENDED) PTU MOTOR ● √ FLAPS ●●● √ √ √ 12 F L I G H T C O N T R O L S LDG GEAR/DOORS ●●●● √ √ GND √ ▪ ELEVATOR ▪ CABLES, CRANKS, AND PUSHRODS NOSEWHEEL STEERING ●● √ √ ▪ HYDRAULIC BOOST ACTUATOR (L, R HYD) BRAKES ●●●● √ √ √ √ ▪ TWO TRIM TABS, L & R HMG MOTOR ●● √ √ ▪ AILERONS ▪ CABLES, CRANKS, AND PUSHRODS PARK BRAKE PRESSURE ● √ ▪ HYDRAULIC BOOST ACTUATORS (L, R HYD) MAIN ENTRANCE DOOR ● √ ▪ L WHEEL L AILERON, R WHEEL R AILERON ▪ CONTROL WHEELS ARE JOINED ▪ L HYD FAIL LOSE: ▪ THE TWO OUTBOARD SPOILERS ASSIST ROLL ▪ L THRUST REVERSER AUTHORITY (55O) ▪ L YAW DAMPER ▪ TRIM TAB IN THE LEFT AILERON ONLY ▪ R HYD FAIL LOSE: ▪ RUDDER ▪ CABLES AND BELLCRANKS ▪ R THRUST REVERSER ▪ DUAL TANDEM HYDRAULIC ACTUATOR (L, R HYD) ▪ R YAW DAMPER ▪ 220 ▪ PTU ▪ TRIM ADJUSTS THE NEUTRAL POSITION OF THE RUDDER 11 L A N D I N G G E A R ▪ DUAL CHANNEL YAW DAMPER (L, R HYD) ▪ EXTENSION ▪ LANDING GEAR HANDLE ▪ FLAPS ▪ FOWLER TYPE FLAPS O O AND ▪ REQUIRES ELEC (ESS DC) TO OPERATE (0 TO 39 ) ▪ MOVES IN CONJUNCTION WITH STABILIZER VIA RETRACTION ▪ REQUIRES HYD (L SYS OR PTU) TO ACTUATE FSECU ▪ (NORM) COMPONENTS ELECTRICALLY CONTROLLED – RVDTs (2) ▪ HYDRAULICALLY OPERATED (L,PTU,AUX HYD) – FLAP ▪ SEQUENCING VALVES DRIVE GEAR BOX (2 FLAP HYD MOTORS) ▪ NITROGEN ▪ OPENS GEAR DOORS AND UPLOCKS ▪ JACKSCREWS DRIVEN BY TORQUE TUBES DRIVEN BY (EMERG) ▪ PRESSURIZES THE HYD LINES WITH NITROGEN GEARBOX – HYD MOTOR ▪ DRIVES THE GEAR DOWN AND LOCKED ▪ FORCE LIMITERS ▪ ANTI-SKID ▪ TOUCHDOWN PROTECTION – LOCKED WHEEL ▪ ALT FLAP – SECONDARY CONTROL – BYPASSES THE BRAKES ▪ TOUCHDOWN/HYDROPLANE PROTECTION – HYD FSECU (ALT FLAP = “FSECU BYPASS”) PRESS REMOVED FROM BRAKES TIL 30KTS SENSED ▪ ELECTRICALLY CONTROLLED OR 5 SECONDS OF GND CONTACT ▪ STAB ▪ ELECTRICALLY POWERED/OPERATED ▪ BRAKE SNUB – ON RETRACTION (FOR 3 SEC) (-1.0O TO -4.6O) - ELEC MOTOR/GEARBOX & TORQUE TUBE ▪ NO PROTECTION BELOW 10 KTS - PRIMARY CHANNEL – MAIN DC BUS ▪ WHEEL-SPEED TRANSDUCERS (70% DIFFERENTIAL) - SECONDARY CHANNEL (EMER STAB) – R STBY AC ELECTRONIC LOGIC BUS (HMG) ▪ SWITCH ON – BRAKES SYNOPTIC 3000 PSI SCALE ▪ COMMAND SIGNALS: ▪ SWITCH OFF – BRAKES SYNOPTIC 800 PSI SCALE - PRIMARY – FLAP HANDLE ▪ DISPATCH ▪ OPERATIVE GROUND SPOILERS 0 - SECONDARY – YOKE ELEV TRIM (EMER STAB) WITH ANTI- ▪ FLAPS 20 SKID INOP ▪ COWL/WING ANTI-ICE OFF ▪ FSECU ▪ SIGNALS THE FLAP POWER DRIVE UNIT TO REQUIRES: ▪ DRY RUNWAY HYDRAULICALLY MOVE THE FLAPS ▪ NOSEWHEEL ▪ ELEC CONTROLLED “STEER BY WIRE”- ELEC SIGNAL ▪ SIGNALS 2 AC MOTORS TO DRIVE THE STAB STEERING TO A TRANSDUCER ▪ MONITORS: FLAP ASYMMETRY, FLAP/STAB ▪ HYDROMECHANICAL ACTUATION (L HYD / PTU SYS) MISCOMPARE, ETC… ▪ TILLER – 80O TO 82O (<18 KTS) ▪ ▪ PEDAL STEERING – 7O (16O – TILLER MALFUNCTION) EMER STAB ▪ STAB POSITION IS CONTROLLED WITH YOKE ELEC ▪ SHIMMY DAMPENING PITCH TRIM, “PULL IT DOWN” O ▪ WOW ▪ WOW ON EACH MAIN ▪ COMBINED WOW ▪ SPOILERS ▪ ROLL AUGMENTATION (2 OUTBOARD PANELS – 55 LIMIT) ▪ FWC PRESUMPTIONS: ▪ AIR: RA >150 FEET ▪ FLT SPOILERS (6 PANELS – 26O LIMIT) FWC WARNS OF ▪ GND: <50 KT O ▪ GND SPOILERS (6 PANELS – 55 ) DISAGREEMENT AIRSPEED ▪ ELECTRICALLY CONTROLLED ▪ HYDRAULICALLY OPERATED (L AND R HYD) ▪ WHEEL SPEED ▪ GROUND SPOILERS ▪ DISABLED WITH “LATERAL CONTROL” OFF SENSORS (>47 KTS) ▪ THRUST REVERSERS PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 9 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ GND ▪ R ESS DC SUBCOMPONENTS: SPOILERS ▪ ARMED ▪ MANIFOLD PRESSURE REGULATING VALVES ▪ PLA – IDLE ▪ HIGH STAGE BLEED VALVES ▪ WOW – GND ▪ FAN AIR VALVES ▪ OR, WHEEL SPIN UP (>47 KTS) IF FLAPS > 22 O ▪ CHECK VALVES ▪ OR, WHEEL SPIN UP (>47 KTS) W/ GPWS GND SPLR ▪ “BLEED AIR ▪ APU AND ENG BLEED AIR – ON O’RIDE ON CONFIGURATION” ▪ BOTH ENG BLEED ON AND ISOL VALVE OPEN DISPATCH WITH ▪ OPERATIVE ANTI-SKID 0 GND SPOILERS ▪ FLAPS 20 14 A I R C O N D I T I O N I N G ▪ COWL/WING ANTI-ICE OFF INOP REQUIRES: ▪ FUNCTIONS: ▪ CABIN AIRFLOW ▪ STALL ▪ PLI VISIBLE AT 0.70 AOA ▪ TEMP CONTROL BARRIER ▪ SHAKER AT 0.85 AOA ▪ EQUIPMENT COOLING ▪ PUSHER AT 1.00 AOA ▪ CABIN AIRFLOW ▪ MODULATED VIA AIR CONDITIONING ▪ GUST LOCK ▪ MECHANICAL LATCHES AND TEMP CONTROLLERS (ACC) VIA PACKS VIA TRIM AIR ▪ AILERONS, ELEVATOR, AND RUDDER CONTROL VALVES AND DELIVERED VIA 3 ZONE DELIVERY ▪ ≤ 60 KT GUSTS DUCTS. HOPS “FORCELINKS”. HOPS CAN BE RESET WITH CBs ONLY ▪ MANUAL TEMP CONTROL: 350F - 2300F 0 0 ▪ AILERON ▪ BOTH L AND R HYD FLUID IS SHUTOFF TO BOTH ▪ AUTO TEMP CONTROL: 60 F - 90 F AILERON AND BOTH SPOILER ACTUATORS (GND/FLT) ▪ EQUIPMENT ▪ FANS FOR LEER AND REER (L/R PSUs) COOLING HIGH SPEED ▪ APU ▪ PRESSURE ▪ RAM AIR ▪ COOLS THE PACK HEAT EXCHANGER REGULATED BY ▪ A FAN RUNS WHEN ON THE GND TO DRAW LOAD CONTROL AIR IN ▪ EXTERNAL AIR VALVE ▪ AIR EXHAUSTED THROUGH LOUVERS ▪ TWO SEPARATE AND INDEPENDENT PNEUMATIC SYSTEMS ▪ CAPABLE OF OPERATING CONNECTED VIA ISOLATION VALVE ▪ PNEUMATICALLY ▪ BLEED AIR VALVES ▪ CONTROLLED BY ▪ BLEED AIR DRIVEN TURBINES AKA ▪ MODULATED BY SWITCHES ▪ DIFFUSERS “MANIFOLD PRESSURE THE BAC ▪ RAM AIR SWITCH ▪ HEAT ▪ PRIMARY AND SECONDARY “RADIATORS” ▪ MAX TEMP 4500F REGULATING VALVES” ▪ 40 ±3 PSI GOAL ▪ ENG START EXCHANGERS SWITCHES ▪ WATER ▪ AIR IS CENTRIFUGALLY SPUN FORCING ▪ BLEED AIR ▪ OPENS AND CLOSES 12TH STAGE AIR TO EXTRACTORS MOISTURE OUT CONTROLLERS SUPPLEMENT 7TH STAGE AIR AS NECESSARY “NO SOCK” ▪ MOISTURE IS ALSO VAPORIZED VIA HEAT (BAC) ▪ CONTROLS TEMP VIA PRE-COOLER ▪ MANIFOLDS: ▪ COLD AIR ▪ GASPERS (ESS DC BUS) ▪ CONTROLS PRESSURE VIA BLEED AIR VALVES MANIFOLD ▪ THREE DUCTS ▪ PRESSURE TARGET ▪ IF 7TH < 15 PSI IN CRUISE 12TH STAGE OPENS ▪ IF 7TH < 26 PSI IN DESCENT 12TH STAGE OPENS ▪ HOT AIR ▪ OZONE SCRUBBERS ▪ IF 7TH <35 PSI SINGLE PACK 12TH STAGE OPENS MANIFOLD ▪ 4000F ▪ TEMPERATURE ▪ NORMAL: ▪ 400OF MAX ▪ TRIM AIR VALVES ▪ MIX HOT AIR WITH COLD AIR TARGET (AT PRE- ▪ SINGLE BLEED OR COOLER OUTPUT) SINGLE WING A/I: O ▪ 500 F MAX ▪ ISOLATION VALVE ▪ OPENS: ▪ MANUALLY ON ▪ APU AIR ON ▪ START MASTER ▪ CRANK MASTER ▪ PNEUMATIC ▪ PACKS USERS: ▪ ENG ANTI-ICE ▪ WING ANTI-ICE ▪ STARTER ▪ VALVES ▪ L/R BLEED AIR VALVES (ESS DC, FAIL CLOSED) ▪ L/R COWL ANTI-ICE VALVES (ESS DC, FAIL OPEN) ▪ L/R WING ANTI-ICE VALVES (ESS DC, FAIL CLOSED) ▪ L/R STARTER VALVES (ESS DC, FAIL CLOSED) ▪ ISOLATION VALVE (ESS DC, FAILS FROZEN) ▪ L/R PACK VALVES (ESS DC, FAIL OPEN) PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 10 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS 15 P R E S S U R I Z A T I O N 16 I C E A N D R A I N ▪ COMPONENTS: ▪ CABIN PRESSURE CONTROLLER (CPC) - REER ▪ PROTECTED ▪ WING LEADING EDGES ▪ BLEED AIR HEAT (130OF) ▪ CABIN PRESSURE CONTROL PANEL (CPCP) COMPONENTS ▪ ENG COWL INLET ▪ BLEED AIR HEAT ▪ CABIN PRESSURE SELECTOR PANEL LEADING EDGES ▪ CABIN PRESSURE INDICATOR PANEL ▪ WINDSHIELDS ▪ ELEC HEAT (114OF) ▪ THRUST RECOVERY OUTFLOW VALVE (TROV) ▪ CABIN WINDOWS ▪ ELEC HEAT ▪ CABIN PRESSURE RELIEF VALVE ▪ EVS WINDSHIELD ▪ ELEC HEAT ▪ PRESSURIZATION AC MOTOR #1 ▪ PROBE SENSORS ▪ ELEC HEAT MOTORS (3) ▪ CPC CHANNEL 1 (MODE: AUTO1) CONTROLLED - AOA PROBES IN BOTH AUTO AND SEMI - PITOT PROBES NOTE: THE ACTIVE CPC ▪ ESS AC POWERED - TAT PROBES CHANNEL AUTOMATICALLY COWL ANTI-ICE: SWITCHES EVERY FLIGHT. AC MOTOR #2 0 ▪ CPC CHANNEL 2 (MODE: AUTO2) CONTROLLED ▪ SAT < 10 C, VISIBLE MOISTURE A/I ON FOR TAXI AND TAKEOFF 0 NOTE: CPC CHANNELS CAN IN BOTH AUTO AND SEMI ▪ SAT < 1 C, VISIBLE MOISTURE, -SET 85% LP FOR 2 SEC PRIOR TO BE MANUALLY SWITCHED BY GND OPS CYCLING THE CPCP ▪ R MAIN AC POWERED T/O MANUAL PUSH-BUTTON. DC MOTOR -SET 85% LP FOR 1 MIN EVERY HR ▪ MANUALLY CONTROLLED, BYPASSES THE CPC ▪ COWL ANTI-ICE VALVES FAIL OPEN – ELEC CONT, PNEUM DRIVEN. TH TH ▪ L ESS DC POWERED ▪ 7 AND 12 STAGE BLEED AIR DOWNSTREAM OF THE ENGINE BLEED ▪ MODES: ▪ AUTO ▪ ADS, FMS, MAU PRESSURE REGULATING SHUTOFF VALVE – NO PRECOOLER. 500/300 FPM ▪ FLIGHT AT 9 KTS WING ANTI-ICE: AUTO & SEMI HAVE OR PLA >15O ▪ THE BLEED AIR CONTROLLER CONTROLS THE WING ANTI-ICE CONTROL VALVES. DUAL CHANNELS ▪ LDG AT -1,000 DESCENT ▪ 12TH STAGE AIR AUGMENTS 7TH STAGE AIR TO PROVIDE 400OF (500OF (R MAIN AC & S.E.) TO THE BLEED AIR MANIFOLD. L ESS AC) ▪ SEMI ▪ CREW PROG CPCP ▪ THE WING ANTI-ICE CONTROL VALVES FAIL CLOSED. ▪ CREW SEL FLT/LDG ▪ CROSS-OVER DUCT PROVIDES REDUNDANCY. ▪ MANUAL ▪ LEADING EDGE TARGET TEMP: 130OF. O AFTER LANDING ▪ CLIMBS THE CABIN AT 500 FPM FOR ONE ▪ OVER TEMP PROTECTION AT 180 F. THE CPCS MINUTE, THEN ▪ ICE DETECTORS ▪ VIBRATING SENSOR ▪ 40,000 HZ ▪ CLIMBS THE CABIN AT 2000 FPM UNTIL THE ▪ AUTO MODE: ON ▪ INHIBITED > FL350 TROV IS FULLY OPEN ▪ TAKEOFF ▪ OFF < 1500 FT AGL ▪ 90 SECONDS AFTER LANDING THE CPRV ▪ LDG ▪ TIL TOUCHDOWN OPENS ▪ AUTO MODE: OFF ▪ TIME DELAY ▪ ICE DETECT – 1 MIN ▪ CABIN PRESSURE ▪ PARTIALLY OPENS AT 9.74 PSI ▪ COWL A/I – 3 MIN RELIEF VALVE ▪ FULLY OPENS AT 9.94 PSI TO 10.15 PSI ▪ WING A/I – 5 MIN ▪ NEG DIFF PRESSURE RELIEF AT -0.25 PSI ▪ COLD WEATHER ▪ REFERENCE AOM CH 7 – ALL WEATHER ▪ LIMITATIONS ▪ MAX DIFF - AIR ▪ 9.94 PSI OPERATIONS OPERATIONS AND PROCEDURES ▪ MAX DIFF - GND ▪ 0.3 PSI ▪ REFERENCE COLD WEATHER OPERATIONS ▪ ▪ ▪ CABIN PRESSURE 8000’ LFE <7500’ MANUAL (CWOM) LOW TRIP POINTS ▪ 10000’ ▪ LFE 7500’-9500’ ▪ ≤ 0 OC CONSULT CWOM – WATER DRAINING ▪ ▪ 14500’ LFE 9500’-14000’ ▪ ALTIMETRY: QRH-NG ALTERNATE NORMALS ▪ 15500’ ▪ LFE >14000’ (ASC 068) ▪ 10000’ ▪ MANUAL MODE ENG START: ▪ O2 MASK DROP ▪ 14750’ ± 250’ ▪ QRH-NG, ALTERNATE NORMALS “COLD WEATHER START AND OPERATIONS” ▪ 15750’ ± 250’ (HIGH ALT SWITCH, ASC 068) ▪ -40OC: MINIMUM OIL TEMP FOR START ▪ EDM ARMED: ▪ ≥FL400 & O ▪ AUTOPILOT ENGAGED ▪ ≤ -10 C OIL TEMP – PERFORM CRANK CYCLE NOTE: DURING VERY COLD (QRH-NG). TURN GEN SWITCHES OFF FOR ▪ EDM MODE ▪ “CABIN LOW PRESS” TEMPERATURES START. ACTIVATED ▪ A/T ENGAGE – GO TO IDLE BAROMETRIC ALTIMETERS ▪ ALLOW MAX LP AND HP RPM FOR 45 SEC ▪ GP SPEED – MAN 340 KTS READ ERRONEOUSLY HIGH, PRIOR TO SELECTING FUEL CONT ON 0 THUS CAUSING THE THE AIRCRAFT ▪ GP HDG – 90 LEFT TURN ▪ GP ALT – 15000’ ACTUAL AIRCRAFT COWL ANTI-ICE (GND AND FLT): AUTOMATICALLY: O O ▪ GP FLCH ALTITUDE TO BE ▪ SELECT ON IF SAT ≤+10 C (50 F) WITH VISIBLE SIGNIFICANTLY LOWER ▪ AIRCRAFT TURN LEFT 900, DESCENDS AT MOISTURE / CONTAMINATED SURFACE THAN INDICATED CONDITIONS VMO/MMO, CAPTURES 15000’ ALTITUDE. G450 AIRCRAFT ▪ GP SPEED – MAN 250 KTS WITH ASC 059B HAVE TEMP ENG ICING NOTES COMPENSATION ▪ CAN OCCUR BELOW 8OC CAPABILITY THROUGH ▪ AS AIR IS DRAWN INTO THE ENGINE THE LANDING INIT IF SELECTED TEMPERATURE DROPS AND THE MOISTURE ON FLIGHT CONFIG PAGE 2. CONDENSES INTO DROPLETS. THESE DROPLETS CAN STRIKE METAL PARTS AND FREEZE ▪ ICE SHEDDING PROCEDURE: REDUCE POWER LEVER (ONE AT A TIME) TO IDLE FOR 5 SEC, ADVANCE TO 85% LP FOR 2 SEC, THEN RETURN TO NORMAL SETTING PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 11 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS TAXI: 17 O X Y G E N ▪ -30OC: MINIMUM OIL TEMP FOR TAXI ▪ OXYGEN BOTTLES (2) ▪ TAXI WITH FLAPS UP ▪ 1800 PSI NORMAL, 1500 PSI MINIMUM ▪ HEAT BRAKES TO 100OC. THIS DISSIPATES ▪ 230 CUBIC FEET TOTAL MOISTURE FROM THE BRAKES; PREVENTS ▪ LOCATED BENEATH THE FLOORBOARDS FROZEN BRAKES ON LANDING ▪ PRESSURE REGULATORS REDUCE PRESSURE TO 55-60 PSI ▪ WHILE STOPPED EXERCISE BRAKES TO 3000 PSI ▪ OVERBOARD DISCHARGE LINE (GREEN DISK) – DON’T SET PARKING BRAKE FOR EXTENDED - OVERPRESSURE PERIODS - OVERTEMPERATURE ▪ AVOID USING REV THRUST IF POSSIBLE ▪ CREW/PAX O2 VALVE LEVER - ON/OFF ▪ MIN OIL TEMP FOR TAKEOFF IS +20OC ▪ PAX O2 SYSTEM CONTROL KNOB - AUTO/OFF/MAN ▪ PERFORM CONTAMINATION CHECK ▪ THE MASKS DEPLOY AT 14750’ ± 250’ (15750’ ± 250’ – ASC 068) AND IF OAT <1OC PERFORM ENG RUN UP (<60 MIN FLOWS UNTIL THE CABIN REACHES 13750 ± 250’ INTERVALS): ▪ QUICK-DONNING EROS O2 MASKS - N: DILUTED ▪ LP RPM .... 85%, PAUSE 1 MIN, RETURN TO IDLE - 100% TAKEOFF PLANNING: - EMERGENCY OXYGEN ROTARY KNOB – POSITIVE PRESSURE FLOW ▪ DO NOT USE REDUCED (FLEX) THRUST - AUTO POSITIVE PRESSURE FLOW AT FL350. CERTIFIED TO FL400. ▪ CONSIDER USING MIN V1 PRIOR TO TAKEOFF PERFORM ENG ICE CLEARING 18 F L O W S PROCEDURE: AFTER APU START BEFORE STARTING ENGINES ▪ LP RPM ...... 85%, PAUSE 2 SEC ▪ ENG OPERATION ...... CHECK NORMAL ▪ TAKEOFF POWER ...... SET AFTER TAKEOFF: ▪ DELAY GEAR RETRACTION, IF PRACTICAL ▪ CONSIDER CYCLING THE GEAR ▪ WARM WHEEL WELLS USING WING ANTI-ICE NOTE: PERIODICALLY DISENGAGE AUTOPILOT TO CHECK TRIM AND HANDLING MINIMUM MANEUVERING SPEEDS: ▪ FLAPS 0O: 200 KCAS ▪ FLAPS 10O: 180 KCAS ▪ FLAPS 20O: 160 KCAS ▪ FLAPS 39O: VREF + 5 KTS PITOT SYSTEM ICING: ▪ CRUISE AOA: 0.2-0.3 (3-5O PITCH) ▪ APPROACH AOA: 0.4 (3-5O PITCH) O ▪ VREF AOA: 0.5 (3-5 PITCH) PITOT SYSTEM AND AOA VANE ICING: AFTER ENGINE START AFTER LANDING ▪ USE GPS GROUND SPEED BEFORE LANDING: ▪ EXTEND LANDING GEAR EARLIER THAN NORMAL ▪ SELECT ANTI-SKID OFF, PERFORM SEVERAL BRAKE APPLICATIONS TO 3000 PSI, THEN SELECT ANTI-SKID ON LANDING: ▪ PERFORM FIRM TOUCHDOWN ▪ CONSIDER PULLING SPEED BRAKE HANDLE AS A BACKUP TO THE AUTO GND SPLR SYSTEM ▪ LOWER NOSE IMMEDIATELY ▪ APPLY MODERATE-TO-FIRM BRAKE PRESSURE SMOOTHLY AND SYMMETRICALLY ▪ MAINTAIN CONSTANT BRAKE PRESSURE ALLOWING THE ANTI-SKID TO WORK ▪ BE PREPARED FOR DOWNWIND DRIFT ▪ NO TURNS UNTIL VERY SLOW TAXI SPEED IS ATTAINED MISSED APPROACH PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 12 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS 19 P LA N E V I E W A V I O N I C S ▪ AIR DATA SYSTEM ▪ 3 AIR DATA MODULES (ADMs) ▪ HONEYWELL ▪ LCDs (4) – DUs ▪ (EDS) ELECTRONIC (ADS) ▪ SOURCES: PITOT/STATIC AND TAT PRIMUS EPIC DISPLAY SYSTEM ▪ DIGITAL DATA TRANSMITTED TO THE EDS, PLANEVIEW ▪ SFD ▪ INTERNAL IRU SFD, EBDI, FMSs, FADECs, & CPAM AVIONICS ▪ MAGNETOMETER ▪ AUTOMATIC SENSOR REVERSION ▪ IRS IN FLIGHT ONLY (>60 KTS) ▪ ADS ▪ EBDI ▪ IRS 1/2/SFD ▪ RAD ALT ▪ DCs (2) ▪ FWC ▪ CCDs (2) ▪ MONITOR AND ▪ FWCs (2) ▪ WARNINGS (RED, ▪ MAUs (3) ▪ COMPUTERS WARNING SYSTEM WITHIN 2 MAUs TRIPLE CHIME) ▪ RECEIVE AND TRANSMIT DATA VIA ASCBs (MWS) ▪ CAUTION (AMBER, ▪ MAU 1 & 3 – LEER, MAU 2 – REER DOUBLE CHIME) ▪ PLUG IN CARDS (16 IN EACH MAU) – LINE ▪ ADVISORY (BLUE, REPLACEABLE UNITS/MODULES SINGLE CHIME) ▪ EACH MAU HAS DUAL PWR SUPPLIES (A&B) ▪ PFDs ▪ PLI ▪ VISIBLE AT 0.70 AOA - MAU 1A: L ESS DC & R MAIN DC ▪ THRUST DIRECTOR ▪ WHEN A/Ts OFF - MAU 1B: R ESS DC & L MAIN DC ▪ AIRSPEED TREND VECTOR ▪ AIRSPEED IN 6 SEC - MAU 2A: R MAIN DC & L MAIN DC ▪ ALTITUDE TREND VECTOR ▪ ALTITUDE IN 6 SEC - MAU 2B: R ESS DC & L MAIN DC ▪ CCDs ▪ FUNCTIONS THAT THE CCD ▪ GRAPHIC FLIGHT - MAU 3A: L MAIN DC & R MAIN DC DOES THAT THE DC CAN’T PLANNING - MAU 3B: L ESS DC & R MAIN DC DO: ▪ RADIO TUNING ▪ MAU ▪ AIRCRAFT PERSONALITY ▪ AMEND ROUTE ▪ CHART SELECTION MODULES ▪ CONTROL MODULES ▪ GP ▪ RANGE CHANGES, ETC ▪ WEATHER CONTROLLER ▪ ▪ ▪ ▪ TCAS (TA < 500’) RNP OCEANIC/REMOTE 4.0 VALUES ▪ ENROUTE ▪ 2.0 ▪ MCDU ▪ ▪ ▪ TONE, MWS TERMINAL (DEST<30NM OR 1.0 ON SID/STAR) ▪ ACTUATOR MODULES ▪ AP/FD, YD, AT ▪ RAD (RADIO) ▪ 0.5 ▪ TRIM ▪ APPROACH (2 NM FROM FAF) ▪ 0.3 (PITCH,AUTO,MACH) ▪ AOA ▪ CRUISE ▪ O.2 TO 0.3 AOA (30 TO 50 PITCH) ▪ STALL PROTECTION GUIDE ▪ APPROACH ▪ 0.4 AOA ▪ VREF ▪ 0.5 AOA ▪ AGM MODULES ▪ PFD ▪ VSD ▪ ACTUAL FLIGHT PATH ANGLE ▪ ND ▪ SPEED PREDICTION CIRCLE ▪ CAS ▪ TERRAIN UNDER FLIGHT PLAN / TERRAIN UNDER TRACK ▪ SYSTEMS ▪ AUTO ▪ V2 ON TAKEOFF ▪ WEATHER ▪ CAMERA SPEEDS ▪ AT 400’ WITH FLAPS UP AND FLCH – 200 KTS ▪ ▪ ANNUNCIATION AT 1500’ V1, VR, V2 DISAPPEAR ▪ AT 2500’/ + 4NM – 250 KTS ▪ GPS MODULES (2) ▪ 1 IN MAU 2 AND 3 ▪ AT 10000’ – 300/.75 ▪ CMC MODULES AUTOTHROTTLE SPEED SCHEDULE EXAMPLE ▪ DATABASE MODULES ▪ NAV (IN EACH AGM) ▪ TERRAIN ▪ AGMs (4) ▪ CREATE AND DISPLAY GRAPHICS ON DUs ▪ AGMs ARE IN EACH MAU - MAUs 1 & 2 HAVE 1 AGM EACH - MAU 3 HAS 2 AGMs ▪ CONTROLLED BY “DISPLAY SYSTEM CONTROL” SWITCHES (4) (OPERATE ON THE GND ONLY) ▪ OPERATES AUTOMATICALLY WHEN AIRBORNE ▪ SYS LOGIC BORROWS FROM DU#3/AGM#3 WHEN FAILURES OCCUR ▪ DU POWER SOURCES ▪ DU 1 ▪ L ESS DC ▪ DC VREF ▪ FLAP HANDLE POSITION ▪ DU 2 ▪ L MAIN DC ▪ CURRENT AIRCRAFT WEIGHT ▪ DU 3 ▪ R MAIN DC HANDLE ACTUAL CORRECTION ▪ ▪ O O DU 4 R ESS DC ▪ FLAP 10 0 +10 ±2KTS ▪ IRU (3) ▪ ATTITUDE INFO FROM GRAVITY INOP 20O 10O +5 ±2 KTS LASER RING ▪ TRUE NORTH FROM EARTH’S TRUE EAST ROTATION VREF 39O 20O +5 ±2 KTS GYROS ▪ UPDATED BY GPS (2) ▪ PRIMARY PWR IF INPUT >18 V DC < 36 V DC ▪ WARN ▪ GEAR MUST BE DOWN ▪ SECONDARY PWR (E-BATTS) IF PRIMARY PWR < 18 INHIBIT ▪ ON TAKEOFF – COMES OFF AT 400’ V DC ▪ AFTER LANDING – MUST BE DESELECTED BY CREW ▪ STATIONARY ALIGNMENT (5-17 MIN) ▪ INHIBITS AMBER AND BLUE CAS CHIMES – NOT CAS MSG ▪ ALIGN IN MOTION (15-30 MIN) – REQUIRES GPS ▪ EXCEPTIONS: INPUT; TURNS HELP - CAT 2 INVALID ▪ AUTO REALIGN – UPDATES WHEN NOT IN MOTION - LATERAL CPL DATA INVALID (LATERAL OR VERTICAL) ▪ HYBRID IRS – GPS, H IRS, DME/DME, VOR/DME, IRS - LPV UNAVAILABLE PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 13 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ TERRAIN ▪ SELECT WITHIN 15 NM OF AN AIRPORT THAT: ▪ HUD ▪ BOX FOR EVS ▪ FLIR INHIBIT - HAS NO PUBLISHED IAP OPERATIONS ▪ EVS - < 3500’ RUNWAY ▪ AUTO, H OR L - NOT IN TERRAIN DATABASE - IF QFE ALTIMETER IS BEING USED IN NON WGS-84 ▪ AIRPORT LINES / ▪ APPEAR AT 2000’ RA COUNTRIES EXTENDED CENTERLINE ▪ DISAPPEAR AT 325’AGL ▪ ▪ ▪ TERRAIN TERRAIN RANGE 20 NM ▪ DEPICTS 800’/8000’ RWY AWARENESS ▪ CFIT DISPLAY ▪ 5 NM INNER RING ▪ 10 NM OUTER RING ▪ APPEAR AT 350’ RA ▪ RUNWAY LINES / ▪ WINDSHEAR ▪ TAKEOFF ▪ GND TO 1500’ AGL ▪ DISAPPEAR AT 60’ RA EXTENDED CENTERLINE WARNING ▪ APPROACH ▪ 1500’ TO 10’ AGL ▪ DEPICTS 150’/8000’ RWY ▪ MISSED APPROACH ▪ TO 1500’ AGL ▪ 1000’ AIM POINT LINE ▪ RADAR - ▪ WHILE REFUELING ▪ NEVER HONEYWELL ▪ DIST FROM FUELING ▪ 300’ ▪ FLARE CUE ▪ < 100’ RA PRIMUS 880 ▪ DIST FROM PERSONNEL ▪ 49’ ▪ TO TURN ON (GND) ▪ STAB 4 TIMES IN 3 SEC AUTOPILOT ▪ AUTOMATIC FLIGHT ▪ TWO CHANNELS (1 & 2) ▪ MIN ENGAGE HEIGHT ▪ 200 FT CONTROL SYSTEM - EACH CHANNEL HAS ITS OWN FLIGHT ▪ MIN DISENGAGE HEIGHT ▪ PRECISION APPROACH - 60 FT (AFCS) GUIDANCE CONTROL SYSTEM (FGCS) ▪ NON-PRECISION - 50 FT < MDA - EACH FGCS HAS ITS OWN: ▪ LNAV/VNAV – AT DA - AUTOPILOT COLD WEATHER - FLIGHT DIRECTOR O O - AUTOTHROTTLE ▪ 65 F (18 C) ▪ MIN TEMP FOR: - YAW DAMPER - DUs, IRUs, EERs - STALL PROTECTION - SFD (CB – POP E-9) ▪ AFCS INPUTS: - EBDI (CB – CPOP D-9) ▪ ICING CONDITIONS EXIST WHEN IN VISIBLE - FMS, IRS, & GP ▪ 50O F (10O C) ▪ FLIGHT MODE ▪ LATERAL ▪ FMS, HDG, LOC, VOR, ETC.. MOISTURE (COWL HEAT) O O ANNUNCIATIONS: ▪ PERFORMANCE ▪ IAS, FLCH, GA, HOLD, ETC.. ▪ 32 F (0 C) ▪ PURGE WATER IF AIRCRAFT IS LEFT UNHEATED > ▪ VERTICAL ▪ ALT, ASEL, FPA, GA, ETC.. 90 MIN ▪ FLCH ▪ IAS OR MACH ▪ FOR ALT CHANGE > 6000’: ▪ 14O F (-10O C) ▪ GEN SWITCHES OFF FOR ENG START PERFORMANCE MODE (SPEED - CLIMB THRUST ▪ 5O F (-15O C) ▪ PURGE WATER SYSTEM REGARDLESS OF CABIN MODE HOLD MODE) - IDLE THRUST TEMP O O ▪ HOLD ▪ ENGAGES AT 60 ▪ THE AUTOTHROTTLE ▪ -4 F (-20 C) ▪ REMOVE BATTs PERFORMANCE KTS DRIVE MOTORS DE- ▪ -20O F (-28O C) ▪ REMOVE LIFE RAFTS MODE ▪ DISENGAGES ENERGIZE AND THE CREW ▪ -40O F (-40O C) ▪ MIN FOR ENG START AT 400’ CAN EASILY MOVE THROTTLES ▪ TO (TAKEOFF) ▪ ARMED WHEN ▪ EPR TARGET (RATED/FLEX) PERFORMANCE ▪ V2 IN GP MODE ▪ ISOL VALVE IS CLOSED ▪ ENGAGE WHEN ▪ EPR > 1.05 ▪ AIRSPEED < 60 KTS ▪ A/T ENGAGE PRESSED ▪ TO (TAKEOFF) ▪ BOTH ENG ▪ INITIALLY 8O PITCH VERTICAL MODE RUNNING ▪ THEN V2 TO V2 + 10 ▪ UNTIL FLAP CHANGE ▪ ONE ENG INOP ▪ INITIALLY 8O PITCH ▪ THEN V2 TO V2 + 10 UNTIL 1500 ‘ AGL ▪ AT 1500 ‘ AGL - VSE ▪ GA ▪ AVAIL: VERTICAL MODE - < 16500’ MSL - < 200 KTS - < 2000’ AGL TO/GA PRESSED: ▪ COMMANDS: - WINGS LEVEL - INITIALLY 8O PITCH - THEN FLAP SPEED SCHEDULE UP TO 17 O PITCH LIMIT ▪ GP - BANK ▪ HIGH BANK ▪ 28O (AUTO < 28500’) O ▪ LOW BANK ▪ 17 (AUTO > 29500’) ▪ PFD-CMD ▪ L & R LIT ▪ ILS APP < 1200’ AGL PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 14 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS 20 S O P ▪ CROSSBLEED START NOTE: AOM CHAPTER 6 GROUND/FLIGHT CHARACTERISTICS AND PROCEDURES (ALTERNATE NORMALS QRH NG-16) ▪ AIR START (QRH EB-17) ▪ NORMAL ▪ ROTATE TO 14O TAKEOFF ▪ PM, “POSITIVE ▪ PF, “GEAR UP” RATE” ▪ PM, “400 FT” ▪ PF, “FLAPS UP, FLCH” ▪ STEEP TURNS ▪ 15000’, 250 KTS ▪ DISENGAGE 1. HDG 2. A/T 3. A/P NOTE: WHEN ROLLING THROUGH ≥32O BANK, AN INVERTED TRIANGLE APPEARS AT THE 45O POSITION. IT DISAPPEARS FROM VIEW AT ≤30O. GULFSTREAM HAS ADVISED THAT THE INITIAL, CRITICAL PILOT RESPONSES ▪ APPROACH TO ▪ SET MAN SPEED 160 KTS FOR THE FOLLOWING EMERGENCY PROCEDURES SHOULD BE PERFORMED STALL - CLEAN ▪ BRIEF “STOP TRIM AT VREF” & “CALL 140” PROMPTLY WITHOUT REFERENCE TO A CHECKLIST: ▪ IDLE THRUST I M M E D I A T E A C T I O N : ▪ STOP TRIMMING AT VREF STALL WARNING ACTIVATION ▪ REJECTED TAKEOFF I M M E D I A T E A C T I O N : ▪ ENGINE FAILURE/FIRE AFTER V1 ▪ ANNOUNCE “STALL” ▪ EMERGENCY DESCENT ▪ REDUCE AOA, SELECT TO/GA POWER ▪ RAPID DECOMPRESSION ▪ ROLL, UNLOAD THE WING ▪ ATTITUDE – TO RECOVER TO LEVEL FLIGHT ▪ AUTOPILOT OR AUTOTHROTTLE UNCOMMANDED DISCONNECT ▪ ENGINE EXCEEDANCE ▪ APPROACH TO ▪ FLAPS 20O STALL – TAKEOFF ▪ SET HEADING CHANGE ▪ OVERSPEED CONFIGURATION ▪ IDLE THRUST ▪ STALL PROTECTION/STALL WARNING ACTIVATION ▪ STOP TRIMMING AT VREF ▪ FLIGHT CONTROL JAMS STALL WARNING ACTIVATION ▪ TOTAL LOSS OF BRAKING I M M E D I A T E A C T I O N : ▪ EGPWS ALERT ▪ ANNOUNCE “STALL” ▪ REDUCE AOA, SELECT TO/GA POWER ▪ WINDSHEAR ALERT ▪ ROLL, UNLOAD THE WING ▪ TCAS ALERT ▪ ATTITUDE – TO RECOVER TO LEVEL FLIGHT ▪ IN ADDITION, PILOTS ARE EXPECTED TO DON OXYGEN MASKS ▪ DURING RECOVERY CALL “SYNC HEADING” PROMPTLY WHEN APPROPRIATE (e.g. WHEN SMOKE IS DETECTED) ▪ APPROACH TO ▪ GEAR DOWN, FULL FLAPS ▪ NORMAL START, ▪ BLEED AIR PRESS ▪ 28 PSI MIN STALL – LANDING ▪ VERTICAL SPEED -700 FPM RIGHT ENG: ▪ START MASTER- ▪ R ECS PACK TURNS OFF CONFIGURATION ▪ IDLE THRUST PUSH ▪ STOP TRIMMING AT VREF NOTE: ENSURE ▪ R ENG START-PUSH ▪ L ECS PACK TURNS OFF STALL WARNING ACTIVATION RESIDUAL TGT IS “SVO” O I M M E D I A T E A C T I O N : < 200 C, IF NOT, ▪ VERIFY LP (2%) PERFORM A CRANK ▪ ANNOUNCE “STALL” AND HP (20%) CYCLE. ▪ REDUCE AOA, SELECT TO/GA, CALL “FLAPS 20” ▪ R FUEL CNTL – RUN ▪ “IGN” ▪ ROLL, UNLOAD THE WING NOTE: WITH ▪ AT 44% HP ▪ “SVO/IGN OUT” ▪ ATTITUDE – TO RECOVER TO LEVEL FLIGHT TAILWINDS > 10 KTS, ▪ MIN ENG IDLE ACHIEVE MAX ▪ AT POSITIVE RATE, CALL “GEAR UP, HDG, FLCH” ▪ MIN OIL PRESS ▪ 49% HP CRANKING RPM AND ▪ AT 160 KTS, CALL “FLAPS UP” VERIFY POSITIVE LP ▪ HYD PRESSURES ▪ 17 PSI RPM PRIOR TO ▪ “SINGLE RUDDER” ▪ 0,0,3000,3000 ▪ JAMMED I M M E D I A T E A C T I O N : SELECTING RUN. ▪ ON STABILIZER ▪ REDUCE PITCH WITH BANK / INCREASE PITCH NOTE: PRESS AND HOLD THE START SWITCH UNTIL SVO IS DISPLAYED. OTHERWISE WITH TRIM YOU’LL GET A SAV MAINTENANCE CAS MESSAGE. QRH - START MASTER OFF, CYCLE ▪ CALL “JAMMED STABILIZER CHECKLIST” FUEL CONTROL, ATTEMPT ANOTHER START. ▪ RUNAWAY PITCH I M M E D I A T E A C T I O N : O O NOTE: WHEN THE ENG START PAGE TGT TEMP SCALE CHANGES FROM 800 TO 1000 TRIM ▪ A/P DISC – PUSH AND HOLD THE ENG START IS COMPLETE. ▪ PITCH TRIM – DISENGAGE ▪ ENGINE START ▪ ENGINE FAILURE TO START ▪ A/P DISC - RELEASE ABNORMALS (QRH EB-29 FIRST STEP: FUEL CONTROL…OFF) ▪ CALL “RUNAWAY PITCH TRIM CHECKLIST” ▪ HOT START (QRH EB-31 FIRST STEP: FUEL CONTROL…OFF) ▪ STARTER VALVE FAILS TO OPEN (QRH EB-29 FIRST STEP: START MASTER…OFF) ▪ STARTER VALVE FAILS TO CLOSE (QRH EB-30 FIRST STEP: START MASTER…OFF) PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 15 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ EMERGENCY EDM ARMED: DESCENT ▪ ≥FL400 & NOTE: USE OF THE AUTOTHROTTLE DURING SINGLE ENGINE APPROACH IS PROHIBITED. ▪ AUTOPILOT ENGAGED NOTE: THE QRH HAS ENGINE OUT DRIFTDOWN CHARTS (EB-14). EDM PROCEDURE: EDM ACTIVATED: ▪ DUAL ENGINE ▪ QRH OPTIONS: ▪ “CABIN PRESSURE LOW” FAILURE - DUAL ENGINE FLAMEOUT NOTE: THE GUIDANCE - DUAL ENGINE FAILURE – MID-ALTITUDE PANEL WILL BE I M M E D I A T E A C T I O N : NOTE: MAXIMUM - DUAL ENGINE OUT LANDING PROCEDURE LOCKED UNTIL THE PF DUTIES: “MASKS MASKS!” GLIDE HAPPENS AT ADM HAS BEEN OXYGEN MASK ...... DON ABOUT 0.30 AOA. NOTE: ENG AIRSTART ENVELOPE ≤ 25,000 FT, ≥ 250 KTS (G450); APU START ENVELOPE ≤ 37,000 FT (G450). TERMINATED BY EDM ...... MONITOR DISCONNECTING THE SPEEDBRAKES ...... DEPLOY (NEARING MMO/VMO) NOTE: USE OF THE STANDBY ELECTRICAL POWER (HMG) IS AUTOPILOT. CALL ...... “LOSS OF PRESSURIZATION CHECKLIST” NOT POSSIBLE WITH BOTH ENGINES WINDMILLING. PM DUTIES: “MASKS MASKS!” NOTE: DONNING OXYGEN MASK ...... DON OXYGEN MASKS: PASSENGER OXYGEN MASKS ...... DEPLOY - REMOVE GLASSES EXTERIOR LIGHTS ...... ON - REMOVE HEADSET, TRANSPONDER ...... SET 7700 PUT THEM AROUND YOUR ATC ...... NOTIFY, ASK MSA ALTITUDE NECK LOSS OF PRESSURIZATION CHECKLIST .... COMPLETE GG - DON OXYGEN ▪ ENGINE FIRE / I M M E D I A T E A C T I O N : THE AIRCRAFT AUTOMATICALLY: MASK, SELECT MIC FAILURE AT V1 ▪ CALLOUT “ENGINE FAILURE” ▪ TO MASK A/T ENGAGE – GO TO IDLE ▪ AT POSITIVE RATE, CALL “GEAR UP, MANUAL ▪ - REPLACE HEADSET SPEED – MAN 340 KTS NOTE: A LEFT ENG SPEED, FLCH” OR SELECT SPEAKER ▪ HDG – 900 LEFT TURN FAILURE WILL CAUSE A ▪ HOLD V2 TO V2+10 ON ▪ ALT – 15000’ BREAK POWER ▪ AT 1500’ AGL (OR CLEAR OF OBSTACLES), CALL ▪ TRANSFER. IF USING FLCH “AUTO SPEED” NOTE: CPC CHANNELS ▪ AIRCRAFT TURNS LEFT 900, DESCENDS AT FGC1 THE LATERAL CAN BE SWITCHED BY MODE MAY CHANGE. ▪ AT V2+10, CALL “FLAPS UP” VMO/MMO, LEVELS 15000’ O O SELECTING MANUAL ▪ AT VSE, CALL “SET MCT” (715 C / 860 C) ▪ GP SPEED – MAN 250 KTS AND RETURNING TO ▪ CALL “ENGINE FIRE CHECKLIST” OR AUTO. NOTE: DO NOT REMOVE OXYGEN MASK UNTIL BELOW “ENGINE FAILURE ABOVE V1 CHECKLIST” (AS 10,000 FT – THE AIRCRAFT WILL LEVEL AT 15,000 FT. APPROPRIATE) ▪ CALL “START THE APU” (APU INFLIGHT MANUAL PERFORM EMERGENCY DESCENT: OPERATION – ALTERNATE ELECTRICAL POWER PROCEDURE: SOURCE, QRH EA-20 I M M E D I A T E A C T I O N : ▪ CALL “TRAFFIC PATTERN CHECKLIST” PF DUTIES: “MASKS MASKS!” ▪ CALL “ONE ENGINE INOPERATIVE LANDING OXYGEN MASK ...... DON PROCEDURE CHECKLIST” POWER LEVERS ...... IDLE TCS ...... PRESS AND HOLD ▪ ENGINE FIRE IN I M M E D I A T E A C T I O N : NOTE: A -8000 FPM HEADING ...... TURN 90 DEG FLIGHT AFFECTED ENGINE ...... IDENTIFY V/S DESCENT CAN BE AIRSPEED .... MMO/MVO (IF NO STRUCTURAL DAMAGE) AFFECTED ENGINE POWER LEVER ...... IDLE DIALED, THE AIRCRAFT SPEEDBRAKES ...... DEPLOY AFFECTED ENGINE FUEL CONTROL ...... OFF WILL NOT OVERSPEED AFFECTED ENGINE FIRE HANDLE ...... PULL O O WHEN ON AUTOPILOT NOTE: AN INITIAL PITCH ATTITUDE OF 8 TO 10 NOSE AFFECTED ENGINE FIRE HANDLE .... ROTATE OUTBOARD DOWN IS RECOMMENDED. AS SPEED APPROACHES DUE TO OVERSPEED CALL “ENGINE FIRE IN FLIGHT CHECKLIST” (EC-3) VMO/MMO EXTEND SPEED BRAKES. ADJUST PITCH TO PROTECTION. AVOID OVERSPEED. ▪ ENGINE SHUTDOWN FOR THE FOLLOWING: CALL: “SET 15,000 FT”, “SYNC HEADING”, “MAN SHUTDOWN ▪ ENGINE FIRE NOTE: GUIDELINES ▪ VIBRATION - EXTREME ENG VIB FELT IN THE SPEED, SYNC”, “FLCH” SLOW TCS ...... RELEASE AIRPLANE, OR IF VIB IS ACCOMPANIED BY OTHER DECOMPRESSION: CALL ...... “LOSS OF PRESSURIZATION CHECKLIST” FAILURE INDICATIONS >10 SEC ▪ LOSS OF POWER - EXCESSIVE OR PM DUTIES: “MASKS MASKS!” UNCONTROLLABLE POWER LOSS RAPID OXYGEN MASK ...... DON DECOMPRESSION: ▪ OIL PRESSURE - SUDDEN INCREASE OR DECREASE 1-10 SEC PASSENGER OXYGEN MASKS ...... DEPLOY IN OIL PRESSURE BEYOND LIMITS, OR SUSTAINED EXTERIOR LIGHTS ...... ON HIGH OIL PRESS ABOVE LIMITS EXPLOSIVE TRANSPONDER ...... SET 7700 ▪ TGT - SUDDEN UNCONTROLLABLE INCREASE IN DECOMPRESSION: GP ...... SET (ALT, HDG, SPEED, FLCH) <1 SEC TGT BEYOND LIMITS ATC ...... NOTIFY, ASK MSA ALTITUDE ▪ ANY OTHER ADVISABLE CONDITION LOSS OF PRESSURIZATION CHECKLIST .... COMPLETE NOTE: DO NOT REMOVE OXYGEN MASK UNTIL BELOW ▪ ENGINE ▪ ENGINE FAILURE CONSIDERATIONS (QRH EB-1) 10,000 FT. EMERGENCIES ▪ ENGINE FAILURE BELOW V1 (QRH EB-1) ▪ ENGINE FAILURE ABOVE V1 (QRH EB-2) ▪ ENGINE FAILURE ▪ QRH OPTIONS: ▪ ENGINE SHUTDOWN IN FLIGHT (QRH EB-13) IN FLIGHT - ENGINE SHUTDOWN IN FLIGHT ▪ ONE ENGINE INOPERATIVE LANDING PROCEDURE - ENGINE FAILURE ABOVE V1 NOTE: QRH STEP (QRH EB-18) “MATCH FGC TO - AIRSTART – WINDMILLING ▪ ONE ENGINE INOPERATIVE GO-AROUND OPERATING ENGINE.” NOTE: DO NOT ATTEMPT AIRSTART IF: PROCEDURE (QRH EB-20) THIS SHOULD OCCUR - FIRE AUTOMATICALLY WITH - FOD THE LOSS OF THE IDG. - FROZEN PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 16 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ DECLARING AN STATE: ▪ GO AROUND – ▪ CALL, “GO AROUND, FLAPS 20” EMERGENCY ▪ AIRCRAFT IDENTIFICATION TWO ENGINE* ▪ SELECT TO/GA, PITCH INTO FD ▪ ▪ NATURE OF EMERGENCY *WITH ENHANCED NAV AT POSITIVE RATE, CALL “GEAR UP, SET UP THE ▪ SOULS AND FUEL ON BOARD (IN TIME) MISSED APPROACH” NOTE: GAC IN-FLIGHT ▪ PILOT’S DESIRES ▪ PM SELECTS: EMERGENCY SUPPORT: ▪ “STANDBY, KEEP AN EYE ON US” 1. GEAR UP 912-965-4178 ▪ AFTER LANDING INTENTIONS 2. GROUND SPOILERS OFF 3. SET/CONFIRMS MISSED APPROACH ALT NOTE: MEDLINK FLIGHT ATTENDANT BRIEF: 4. CONFIRMS PF GP IN FMS IN-FLIGHT EMERGENCY ▪ T - TYPE OF EMERGENCY 5. SELECTS MAN SPEED 200 KTS SUPPORT: ▪ E - WHETHER AN EVACUATION WILL BE 6. SELECTS FLCH 602-239-3627 NECESSARY ▪ AT VREF +20, CALL “FLAPS UP” ▪ S - WHAT SIGNAL WILL BE USED (AND WHEN) FOR ▪ CALL “TRAFFIC PATTERN CHECKLIST” BRACE AND EVACUATE; “EASY VICTOR, ENHANCED NAV NOTE: WHEN GA MODE IS SELECTED WITH THE ACTIVE LATERAL EVACUATE, ETC” MODE BEING LNAV, THE LATERAL MODE DOES NOT TRANSITION TO WINGS ▪ LEVEL/HEADING HOLD; IT REMAINS IN LNAV. T - TIME AVAILABLE TO PREPARE NOTE: A FULLY COUPLED AUTO MISSED APPROACH IS POSSIBLE WITH ONLY – ▪ APRCH ▪ FOR FMS FLOWN APPROACHES THE APRCH “TOGA, FLAPS 20, POSITIVE RATE, GEAR UP, 400’, FLAPS UP” – EVERYTHING ELSE ANNUNCIATOR ANNUNCIATION MUST TURN ON 2NM BEFORE THE WORKS AUTOMATICALLY, - AS LONG AS THE MISSED APPROACH ALTITUDE IS SET IN FAF THE ALTITUDE PRESELECT. ▪ THIS CONFIRMS SENSOR CONFIGURATION IS ▪ GO AROUND – ▪ CALL, “GO AROUND, FLAPS 20” CORRECT AND SENSOR INTEGRITY IS WITHIN SINGLE ENGINE* ▪ SELECT TO/GA, PITCH INTO FD LIMITS FOR THE APPROACH ▪ *WITH ENHANCED NAV AT POSITIVE RATE, CALL “GEAR UP, SET UP THE ▪ BLUE NEEDLE APPROACHES NAV SOURCE: IFMSI MISSED APPROACH” APCH GP APCH ALT VERTICAL LATERAL ▪ PM SELECTS: TYPE BUTTON MINS PRESELECT MODE MODE NOTE: USE OF THE 1. GEAR UP VGP AUTOTHROTTLE 2. GROUND SPOILERS OFF RNP (LPV) DURING SINGLE LPV 3. SET/CONFIRMS MISSED APPROACH ALT ENGINE APPROACH IS 4. CONFIRMS PF GP IN FMS RNAV DA PROHIBITED. 5. SELECTS MAN SPEED (NOT 200 KTS) (LNAV / 6. SELECTS FLCH VNAV) APRI MAA NOTE: SINGLE ENGINE ▪ AT 1500’ AGL (OR CLEAR OF OBSTACLES) AND VREF VGP AUTOPILOT COUPLED RNAV GO-AROUND IS NOT +20, CALL “FLAPS UP, SET VSE” (VSE=0O FLAP VREF) (LNAV) (1) FMS O O DDA APPROVED. ▪ AT VSE (0 FLAP VREF), CALL “SET MCT” (715 C) VOR(2) ▪ CALL “ONE ENGINE INOPERATIVE GO-AROUND PROCEDURE CHECKLIST” RNAV ▪ CALL “TRAFFIC PATTERN CHECKLIST” (CIRCLE) LNAVI ▪ CALL “ONE ENGINE INOPERATIVE LANDING MDA MDA VPATH VOR(2) VNAVI PROCEDURE CHECKLIST” (CIRCLE) ▪ MIN SPEED ▪ TAKEOFF, NORMAL & V1 CUT: V2+10 FOR FLAP ▪ GO AROUND, NORMAL AND S.E.: VREF(20) +20 RETRACTION ▪ WINDSHEAR / I M M E D I A T E A C T I O N : CFIT ESCAPE ▪ DISCONNECT AUTOPILOT AND AUTOTHROTTLES ▪ MAX POWER (ENSURE SPEEDBRAKES ARE QRH: SUPPLEMENTAL RETRACTED) DATA, S-7 WINDSHEAR O O ▪ GREEN NEEDLE APPROACHES NAV SOURCE: INAVI / MICROBURST ▪ 3 TO 4 PER SECOND ROTATION ▪ PITCH UP TO 25O OR PLI APCH GP APCH ALT VERTICAL LATERAL QRH: RED TAB, MA-9 ▪ SPD, VREF -20 KTS OR PLI TYPE BUTTON MINS PRESELECT MODE MODE AND AMBER TAB, MB- 54 - OTHER WARNING ▪ NO CONFIG CHANGES TILL CLEAR ILS APRI DA MAA GS ANNUNCIATIONS NOTE: A PITCH ATTITUDE OF 25 DEG HAS BEEN (1) (4) LOC DDA MAA DEMONSTRATED AT MAX LNDG WT WITH FULL FLAPS. LNAVI LOC LOC VS/FPAI POST WINDSHEAR: MDA MDA (CIRCLE) (3) ▪ CALL “MAN SPEED 250, FLCH” (1) (4) ▪ ENGAGE AUTOTHROTTLES VOR DDA MAA APRI VS/FPA VORAP ▪ TCAS ALERT I M M E D I A T E A C T I O N : VOR VS/FPAI MDA MDA ▪ (3) TCS – PRESS AND HOLD (CIRCLE) ▪ PITCH – FLY-TO-BOX (1) (4) BC LOC BCI DDA MAA ▪ ATC – NOTIFY “TCAS RA” ▪ WHEN CLEAR, “RETURNING TO ASSIGNED BC LOC VS/FPAI BC (3) MDA MDA ALTITUDE” (CIRCLE) (1) DDA = MDA + 60 FT (3) MATCH VERTICAL TRACK (DASHED MAGENTA ON VSD) TO FMS DEPICTED VERTICAL PATH (4) VS/FPA WILL HONOR THE ALT PRESELECT, SET MAA WHEN APPROPRIATE TO NOT INTERFERE WITH DESCENT NOTE: APR AND VS/FPA BUTTONS ARE USED FOR A GREEN NEEDLE VOR APPROACH (VORAPP), THE ALTITUDE WINDOW WILL BE HONORED. PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 17 G U L F S T R E A M G 4 5 0 Condensed Notes TABLE OF CONTENTS ▪ CONTAMINATED ▪ TAKEOFF ▪ FLAPS 20O ONLY ▪ EMERGENCY PARK / EMERG BRAKE ...... SET RUNWAY ▪ OPERATIVE ANTI-SKID EVACUATION L / R FUEL CONTROL SWITCHES ...... OFF RESTRICTIONS ▪ OPERATIVE AUTO GROUND L / R FIRE HANDLES ...... PULL (IF REQ DISCH 1 / 2) QRH LAST PAGE SPOILERS CABIN PRESSURE CONTROL ...... MANUAL ▪ OPERATIVE THRUST REVERSERS NOTE: THE FIRE OUTFLOW VALVE ...... FULL OPEN ▪ MAX STANDING WATER – 0.39IN HANDLE RELEASE APU MASTER ...... OFF ▪ RATED THRUST ONLY, ETC… BUTTON WILL NEED L / R MAIN BATTERIES ...... OFF TO BE PRESSED. O PASSENGERS / CREW ...... EVACUATE ▪ LANDING ▪ FLAPS 39 ONLY ▪ OPERATIVE ANTI-SKID EVACUATION COMMANDS: ▪ OPERATIVE THRUST REVERSERS “OPEN SEAT BELTS, LEAVE EVERYTHING, COME ▪ MAX STANDING WATER – 0.59IN THIS WAY, GET OUT, RUN AWAY FROM THE ▪ THRESHOLD SPEED VREF TO AIRCRAFT” VREF+10 ▪ LANDING DIST ▪ EXCESS ▪ DRY RUNWAY, AN ADDITIONAL ADJUSTMENTS AIRSPEED 300 FT PER 10 KTS “RULE OF THUMB” ▪ WET RUNWAY, AN ADDITIONAL 500 FT PER 10 KTS ▪ EXTENDED FLARE, AN ADDITIONAL 2500 FT PER 10 KTS ▪ DOWNHILL ▪ AN ADDITIONAL 10% OF LANDING DISTANCE PER 1% DOWN SLOPE ▪ FLOATING ▪ AN ADDITIONAL 230 FT PER SECOND ▪ EXCESSIVE ▪ AN ADDITIONAL 200 FT PER 10 TCH FT ABOVE TCH ▪ DELAYED ▪ AN ADDITIONAL 220 FT PER BRAKING SECOND ▪ FLEX TAKEOFF ▪ NO TAILWIND RESTRICTIONS ▪ NO DOWNHILL SLOPE (AFM APPENDIX A) ▪ NO CONTAMINATION ON RUNWAY (BUT WET IS OK) ▪ NO WING ANTI-ICE ▪ ANTI-SKID MUST BE OPERATIVE ▪ AUTO GROUND SPOILERS MUST BE OPERATIVE IF FLAPS 10O, ETC… ▪ TOTAL LOSS OF I M M E D I A T E A C T I O N : BRAKING ▪ THRUST REVERSE – MAXIMUM ▪ PTU AND AUX PUMP – ON ▪ BRAKES – RELEASE ▪ ANTI-SKID – OFF ▪ BRAKES – APPLY 400 PSI MAXIMUM ▪ PARKING BRAKE – APPLY 400 PSI MAXIMUM IF BRAKE PEDALS INOPERATIVE ▪ UNCOMMANDED I M M E D I A T E A C T I O N : NOSEWHEEL ▪ DIFFERENTIAL BRAKES AND RUDDER - USE STEERING ▪ NOSEWHEEL STEERING SWITCH – OFF ▪ REJECTED I M M E D I A T E A C T I O N : TAKEOFF ▪ “ABORT” ▪ IDLE POWER, MAX BRAKES ▪ MAX REVERSE ▪ EXTEND SPEED BRAKES ▪ NOTIFY ATC ▪ SET PARKING BRAKE ▪ ADVISE PAX, “REMAIN SEATED – REMAIN SEATED” ▪ QRH OPTIONS: - REJECTED TAKEOFF (QRH MISCELLANEOUS INDEX, EI-12) - ENGINE FAILURE BELOW V1 - THRUST REVERSER UNLOCK OR DEPLOY DURING TAKEOFF PLEASE EMAIL CORRECTIONS TO: [email protected] REV 4.0, 201909 P A G E 18