System 2 Check Flashcards
Generator
- Primary source of power
- 28 VDC/300 amp
- Regulated by the GCU
- Location: Right side panel aft cockpit
Generator Switch
Only one switch can be one (either front or aft cockpit)
Secondary Aircraft Power
- Battery: 24 VDC/42 amp hr
- Aux Battery: 24 VDC/5 amp hr
- External power distributes on the battery bus
Aux Battery Switch
Needs to be in “ON” position to power backup instruments
Kneeboard Lights
Rotate towards you to turn on
Taxi/Ldg Gear Lights
Only on if gear down and locked
Single Point Refueling
- 1100 lbs
- 530 lbs per wing
- 40 lbs in collector tank
- refuels all tanks at the same time
Over Wing Refueling
- 1200 lbs
- 580 lbs per wing
- 40 lbs in collector tank
- will only fill respective tank at a time
Motive Flow Line Low Px
FUEL PX light with MAST WARN will turn on if less than 10 psi
Primary Jet Pump
Provides pressure to go up line to engine from collector tank
EDM
- Engine Data Manager
- keeps us within 20 lbs fuel balance
Fuel Imbalance Light On
> 30lbs imbalance past 2 min
Fuel Probes
- 7 total
- 3 each tank
- 1 in collector tank
- Provides fuel indication quantity
Fuel Tapes
- turn yellow at 150 lbs
- Less than 110 lbs - Low fuel line in respective tank
Float Valves
prevent excess fuel from draining out of heavy wing into vent lines
Aux Battery
Will Power:
- fire detection Loop 1
- instrument associated lights
- IRU
- VHF Radio
- Standby VHF control head
-will provide power for 30 min
Red OIL PX
- Less than 40 psi when above idle
- Less than 15 psi at or below idle
Amber OIL PX
- Between 15 and 40 psi at idle
- Between 40 and 90 psi for 10 seconds above idle
Red OIL PX and Amber OIL PX
-Between 15 and 40 psi for greater than 5 seconds at idle
Needed for engine operation
air, fuel, heat
Sections of engine
- Accessory
- Power Turbine
- Gas Generator
Reduction Gear Box
Steps down 30,000 RPM to 2,000 RPM
PMU Purpose
Process power request
Maintain operations limits
Propeller
- 100% Np at 2,000 RPM
- Fine pitch at idle
- Course pitch at higher RPM
PIU
- Receives input from PMU
- Regulates oil pressure to pitch change mechanism
Fire Detection
- Kinks don’t affect it
- Monitors overall engine temp and discrete temp
- Monitors outside the engine
Engine Failure
- Fuel starvation
- Mechanical failure
- Compressor stall
Fire in Flight
- Fluctuating oil px , oil temp, or hyd px
- Excessive turbine temperature
- Visual indications (smoke or flames)
- Erratic engine operation
- Roughness or vibrations
Fire in Flight Notifications
- Fire message
- MAST WARN light
- Aural tone
Ram Air Switch
- Opens fresh air valve
- ram air is used for ground ops and unpressurized flight
P3 Ports
Left side - OBOGS
Right side - everything else
Temp Control Switch
- Control Heat Exchanger Bypass Valve (open - hotter air. Closed - Colder air because it goes through heat exchanger)
- Keeps temperature at 60-90*F
DEFOG Switch
- front CP only
- opens bi-level flow control bypass valve
- high bleed air auto select
- AC on
- temp still set by Temp Control Switch
EVAP BLOWER
-only switch in each CP
Cockpit Space Temp Sensor
-sends temperature to Temp Control Switch for Bypass valve
DUCT TEMP light
> 300*F
Temp where Heat Exchanger closes Bypass Valve
165*F
Pressurization
- right side P3 port
- less than 8000 ft is unpressurized
- maintains 8000’ PALT until 18,069’ (delta P 3.6+-0.2 psi) until 16,600’ max (31,000’ ) cockpit altitude
CKPT light
19,000’ cockpit light
Dump Pressure switch
-dump solenoid opens control valve
Ram/Dump Switch
-dump solenoid opens control valve and ram air valve
Safety Valve
- delta p regulator will regulate cabin at 3.9 - 4.0 psi
- >3.9 = CKPT PX with MAST WARN
CKPT ALT caution
> 19,000 ‘ PALT
Anti-G System
- Air goes through water separator to separate contaminants
- Safety Valve opens at 7 psi
- outside air pressure will bleed system to deflate g-suit
Emergency Oxygen
- located in seat bucket
- 10 min supply
- auto activated when eject
- can’t stop flow once started
Canopy Components
- frame
- forward windscreen
- forward transperancy
- rear transperancy
Canopy Seals engage
WOW off and bleed air available
CFS
- each handle blows respective cockpit
- doesn’t need electricity
- Auto activated only during ejection
Front Cockpit Charge
Flexible Linear Shape Charge
Ejection Seat Limits
0’/0 airspeed to 35,000’ / 370 knots
MOR Handle
- to initiate seat/pilot separation
- ideal over mountain terrain exceeding 8,000’
SSK
Auto-deploy 4 seconds after seat/pilot separation
ISS
- if set to BOTH, pinned seat will still fire
- rear seat first, front seat 0.37 sec later
Ejection Sequence
-At the top of the rail, rocket motor will fire
Droge Chute
- Purpose: to stabilize and slow down
- if greater than 16,000’ MSL droge chute will stay until 14,000 - 16,000’ MSL at which point the main chute will open
Seat Adjust
-Electrically driven
Ejection Charts
Based on:
- sink rate
- bank angle
- dive angle
2000 ft controlled,
6000 ft uncontrolled
