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Airspeed required to maintain 12% RPM for a windmill start?
350K
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When SE, hyd sys switches from 3000 to 5000psi above what airspeed? And it drops from 5000 to 3000psi at what airspeed?
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When is ignition on?
- 10-45% during start
- flameout
- when throttle is in AB until AB is lit
- trigger squeeze +5 sec for any A/G or A/A weapon
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AMAD powers what items?
- fuel boost/motive flow pump
- generator
- hyd pump
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Ice penetration
- increase speed until inlet tems are >5*C
- maintain AOA >6*
- lower gear as late as possible
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Normal fuel flow
- internal wing tanks>tank 4
- externals feed to tank 1>tank 2> left eng
- externals feed to tank 4>tank 3> right eng
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Fuel transfer
- motive flow transfers engine feed (tanks 2/3) and wing tank fuel
- electric pumps for fuselage transfer (tanks 1/4) and dump
- engine bleed air transfers external tanks. External transfer stops with IFR probe extended or hook/gear handle down.
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Feed tank balancing
SDC keeps tanks 2/3 within 100# of each other once tank 4 is empty
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Fuel dump
- 1300#/min
- stops when:
- -switch is off
- -bingo reached
- -tanks 1 and 4 are empty
- -FUEL LOW caution comes on
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FUEL LOW light
<1125# in either feed tank
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FUEL XFER caution
when wing tank asymmetry >350#
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Yaw rate tone
- UA only
- on at 40*/sec
- solid at 60*/sec
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AOA warning tone
- PA only
- on at 14*
- solid by 35*
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How much fuel is in each tank?
- tank 1 1430#
- tank 2 2660#
- tank 3 2680#
- tank 4 3860#
- (total fuselage 10,630#)
- wings 1670#/1670#
- (total internal 13,970#)
- CL 3220#
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At what a/s does hyd pressure change?
- 3000psi <380k
- 5000psi >380k (500k if SE)
- utilities are always at 3000psi
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Leak isolation
- -lose circuit A if <50% remaining
- -regain A and lose B if <30% remaining
- -regain both if <15% remaining
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Hydraulic switching valve
if <900psi (+/- 100psi) on primary system, switching valve mechanically changes to secondary hydraulic power (switches back if primary system is >2000psi)
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Hydraulic
Forward isolation valve (LAWNN)
- gear handle up, gear up and locked
- launch bar
- antiskid
- wheel brakes
- NWS
- nose gear
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Hydraulic
Aft isolation and arming valve
- open with WonW, closed inflight
- aft isolation manually opened with hook retract or HYD ISOL switch in Oride
- arming valve manually opened by emer gear or emer probe extension
- hook retract
- parking brake
- emergency brake
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APU accumulator
- maintained by trickle charge from HYD 2A
- if HYD 2 fail will provide pressure for:
- emer landing gear
- emer probe extension
- emer NWS
- emer brakes
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Brake accumulator
- full at 3000psi
- maintained by trickle charge from HYD 2A
- emergency brakes use HYD 2B and APU acuumulator
- will get BRK ACCUM light if pressure <2000psi (5 applications left)
- provides parking brake with engines off
- provides emer brakes with HYD 2 failure
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Wheels warning
- <7500'
- <175k
- >250fpm rate of descent
- gear not down and locked
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Antiskid
- inop <14k
- inop with emergency brakes
- when gear lowered, system turned on inflight, or on deck with the parking brake set, system starts 4.5 sec bit after 9 sec (do not cycle anti-skid <30 sec prior to landing)
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Arresting hook
- gravity lowered
- need HYD 2B to retract
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HYD caution
circuit pressure <1400psi
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HYD 5000 caution
unable to provide 5000psi when commanded
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The loss of which circuits will make the jet uncontrollable?
Hyd 1B/2A/2B
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Systems lost with Hyd 2A failure
- landing gear extend/retract
- antiskid
- wheelbrakes
- NWS
- normal probe extend
- launch bar
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Generators
- on at 60%, off at 52%
- if either generator fails the bus tie will close, connecting the two buses
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GEN TIE light
- ac buses are isolated
- parking brake NOT pulled prior to first engine start
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TR failure
- single TR-no indication
- dual TR will lose:
- -HUD
- -bleed air (pressure and OBOGS)
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Battery
- provides 5-10 min of power to FCC
- auto shutoff after 2 min if APU is not online
- with 1 gen online, gauge should be >28v
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BATT SW caution light
- battery on without external AC power (before engine start)
- battery switch off inflight
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Maintenance bus
- ladder
- canopy
- APU start
- gen tie logic
- SMP and maint code checks
- airborne: FCC and INS keep alive logic
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Dual gen failure
- lose all displays
- lose cabin pressure
- caution lights inop
- RPM and EGT only on EFD
- comm 1 only
- must use standby instruments
- must use emer gear (no anti-skid)
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Battery power during dual gen failure
- battery switch must be on to power FCCs
- if battery gauge = 28v, PMGs are powering FCCs
- if battery gauge = 24v, battery is powering FCCs (land ASAP)
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Electrical reset
resets generator, PMG or electrical relay
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CBs in cockpit
- L side: FCC 1 and 2, launch bar
- R side: FCC 3 and 4, hook, landing gear
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Parking brake
- must be set to run anti-skid bit, gen tie logic, or INS alignment
- will get PARK BRAKE light if set with RPM>80%
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Nose gear extension
- HYD 2A
- Nose gear will not retract if:
- -nose WonW switch failure
- -launch bar failed to retract
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Emergency gear extension
- acutuated by APU accum pressure
- <170k
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NWS
- primary HYD 2A
- backup with HYD 2B and APU accum (NWS cue flashes if using APU accum pressure)
- auto disengage with:
- -WoffW
- -launch bar down
- -power off FCCs
- automatically engages on touchdown with WonW
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APU ACCUM light
- if accumulatore pressure is <2450psi
- inflight after
- -APU start
- -after emer gear extension
- -after emergency probe extension
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PMG
Permanent Magnetic Generator
- on at 50%, off at 20%
- one on each AMAD
- NOT controlled by generator switch
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GEN light
- generator is not producing AC power
- single GEN light with AMAD PR caution could indicate major mechanical damage
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ECS
primary bleed air pressure regulator and shut-off valves
- valve located off of each engine, prior to Y junction
- will close if air or electricity is lost
- can be closed by BALD
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ECS
secondary bleed air pressure regulator and shut-off valve
- downstream of Y junction
- electrically controlled by the OFF and AUG PULL position of the bleed air knob
- will fail to the open position
- can be closed by BALD
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Bleed air knob - OFF
- secures all 3 bleed air pressure and regulator shut-off valves
- will lose:
- -OBOGS
- -cabin pressure
- -external fuel transfer
- -crossbleed start
- -g-suit
- -windshield anti-ice and rain removal
- Bleed air valves will close during fire test. Must rotate BA knob OFF then NORM to reset valves and cautions.
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Bleed air knob-AUG PULL
- augments ECS air for avionics cooling
- will override APU shutdown
- must have:
- -WonW
- -APU on
- -bleed air knob in any position besides OFF
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ECS modes
- AUTO (normal)
- -WonW and throttles idle - aft avionics cooling fan is primary source of avionics cooling, ECS is secondary
- -WonW, either throttle >74% or inflight - ECS provides all avionics cooling
- MAN (prohibited)
- OFF/RAM
- -stops normal flow
- -ram air for scoop for cockpit airflow
- -emergency avionics cooling fan for avionics cooling
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Defog handle
- HIGH-airflow to windshield
- NORM-airflow to cockpit louvers and windshield
- LOW-airflow to cockpit louvers and foot heater
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Cabin pressure schedule
- 0-8k: ambient
- 8k-24.5k: 8,000'
- >24.5k: .4 x a/c altitude
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Cabin pressure switch
- NORM: on schedule
- DUMP: dumps cabin pressure, normal ECS flow to cockpit and avionics
- RAM/DUMP: dumps cabin pressure, stops ECS airflow
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AV COOL switch
- ram air scoop for emergency cooling of FCC A, one AHRS, right T/R
- maintain >325k
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BALD
bleed air leak detection
- shuts down ECS flow if leak detected
- if leak detected downstream of Y junction will get both L BLD/R BLD
- can close pri/sec pressure regulator valves
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OBOGS DEGD caution
- concentration falls
- hose disconnected
- mask removed without securing Oxy flow
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Two CAS modes
- Up-Auto (UA)
- -Flaps-AUTO
- ->240k
- Powered Approach (PA)
- -Flaps-HALF or FULL
- -<240k
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Indications of a spin
- 120KCAS (+/- 10KCAS)
- yaw rate threshold exceeded
- -15-20*/sec for 15 sec or 50-60*/sec for 2s
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