Aircraft Systems Flashcards
T5
Free power turbine inlet temperature
Nr
Main rotor speed
Low rotor tone limits
98% +/- .5%
Steady tone at 91% +/-.5%
Tail gearbox or intermediate gearbox chip detector limits
Chip too big to burn off or 140°C +/-6°C
Usable fuel
- 4 lbs pressure
4234. 8 lbs gravity
Boost pumps fail
16.5 psi
Low-level fuel caution light
170-200 hover
210-280 3° nose down
Fuel dump rates
600 both
315 forward
365 aft
On engage droop stops go out at
And do what?
75% Nr
Prevent downward motion of main rotor blades
Sources of AC power
External
Inverter
Two generators
Sources of DC power
Battery
2 TRUs
One TRU fail, or both fail
One - monitored bus dropped
Both - monitored bus and primary bus dropped, essential run off battery
DC busses
Essential bus for DC flight instruments and all equipment necessary for safety of flight
Primary bus for all equipment essential for Mission completion
Monitored bus for equipment not required for safety of flight
Battery bus for the pilot domelight cockpit spotlights and CPI
Radio bus 1
Power from and to
Powered by the essential bus via the radio master one switch and supplies power to: ILS/VOR, VHF/AM, ICS, Secure voice, IFF, TACAN, UHF
(IVISITU)
Radio bus 2
Power from and to
Powered by the primary bus via the radio master 2 switch and provides power to: Doppler, OTPI, UHF antenna, HF, ASN-123, UHF/ADF, LF/ADF
(DO U HAUL)
What is the purpose of the tail rotor
To counteract the forces of the main rotor
Max speed
151 KIAS
Fuel consumption
1000 fwd
1200 hover
Basic weight and Max gross weight
14,500
20,500
Engine type
Components
2x GE T58-GE-8F axial flow gas turbine engines of the turboshaft type
Gas generator
free power turbine
Ng
Gas generator compressor speed which is dependent upon fuel flow and monitored by the fuel control unit
Anti-flap restrainers
Released at 25% Nr
Prevent upward motion of main rotor blades
Ibis
Pressure indicator at blade root combined with detector assembly gives visual and in-flight indication (master caution) of blade serviceability
Main gearbox
Couples both engines through single planetary gear assembly (which reduces engine RPM)to the rotor head
How many hydraulic systems and what are they
Three
Primary
auxiliary or ASE
utility
Accessory section
Driven by and supplies power to
Number one engine
Primary utility and AUX hydraulic pumps, HP torque meter oil pump, 2 AC generators, and two main gearbox lubricating oil pumps
MGB oil indications
Temp & presure
120°C
12 psi
Nf
Free power turbine speed, dependent upon speed selector level position and rotor load
Inverter, powered by, power to?
Powered by DC battery or external DC, to provide 115 volt VAC to pre-start instruments
AC power distribution #2 gen load
Pilot VGI Heater blower No.2 fuel pump Copilot windshield anti-ice AC utility receptacle
No. 1 gen fail
No.2 drops load (except pilot VGI and sonar) and picks up No.1’s load
No.2 gen fail
Entire load dropped, No.1 picks up pilot VGI
Battery power
Purpose? Recharged by?
24 volt 22 amp
Limited ground ops and emergency power source in event of dual TR failure
Charged by TRs during normal ops
No 3 radio bus
Powered from primary bus, no switch VHF/FM KY-75 RadAlt Sonobouy Rxs Sonar power Sonar guillotine
ASE
Provides in flight stability
Some automatic flight control using various inputs
Fed into Flight controls using AUX servocylinders
Affects pitch, roll, yaw, and BarAlt
Utility hydraulic system pressure
3000 psi
Rescue hoist 1250
Utility hydraulic system powers
Landing gear Blade (1st) and pylon fold Rotor brake Windshield wiper Rescue hoist Haul down Cable reeling machine
Landing gear up powers what system
Armament system
Weight on wheels for what
Landing gear locked in down position
Landing gear emergency extension
3000psi air blow down
Gauge of pressure on broom closet
Emergency release handle: vents hydraulics and gear is lowered by gravity
Rescue hoist capacity Length Psi Power Shear power
600lbs 1250 psi utility hydraulics 100ft usable cable First and last 10 ft red Shear powered by DC essential bus
Radar blind arc
20°fwd
10°aft
Radar freq
9.375GHz
Gain
Varies intensity of displayed video radar returns (clutter)
STC
Sensitivity time control. Used to reduce sea clutter -decreases receiver gain for close targets
- varies between 0 to 20 nautical miles
- reduces effect of gain
FTC
Fast time constant.
- Allows only leading edge of contact to be displayed
- reduces clutter with no effect on gain
Radar power req’s
28VDC from primary bus
115 VAC from #1 gen
26VAC for heading reference
GHARS fail radar limit
15° roll, 10° pitch
Radar TX warning
10’ rotating
50’ not rotating
Doppler feeds
ASE
GHARS
123
GVIs
OTPI channels
1-16
17-31
GHARS components
- GRU
- Flux valve
- CRA-2-2A
- EU
- CRA-3
- MHIC
- Gyro controller
-CRA-2-2A
-CRA-2-2A - compass repeater amplifier provides Mag hdgs from flux valve to RMI, CDI, BDHI
-Flux valve
-Flux valve-Mag hdg ref, located in tail, 30° pitch/roll movement
GRU
Gyro reference unit
Fully gimballed gyro free or slave mode
EU
Electronic unit
located in electronics compartment in the nose interface of all GHARS systems and supplies power to the system
CRA-3
Compass repeater amplifier
Floor between pilots
Amplifies true or grid headings from GRU to ASE, ASN 123, Doppler antenna, radar and BDH I S
What’s the difference between slave and free modes
Slave-flex valve slaves GRU
Free-GRU as free directional Gyro
Variation is automatically updated to the Flux valve heading
Max change of 6°/hr
GHARS outputs
TRUE (BRAD)
- BDHIs
- Radar
- ASN 123
- DOPPLER
MAG to BDHIs, RMIs, CDI
Pitch & roll to Pilots VGI & Radar
Hdg ref to ASE yaw channel
How accurate is the trimpack GPS
100 m at least
If high-level shut off’s are not serviceable when do you cease fueling
When either fuel gauge reaches 2000 lbs when fuelling JP-5 or at 1900 lbs when fuelling JP-4
What are the NATO equivalents for JP4 and JP5
F 40 and F 44 respectively
Accessory drive section drives what systems
Primary utility and auxiliary hydraulic pumps; the high-pressure torque meter oil pump; two AC generators; two MGB lubricating oil pumps; Nr tach generator; and tail Drive shaft take off
Tail rotor pitch limit
10° either side
Inverter
Three phase 400 Hz 115 V AC inverter located on the left-hand side of eBay
Energized by DC power from the DC essential bus
Converts it to AC power to the pre-start engine instruments during starting from DC external power or battery power
When one or both generators are operating the inverter is automatically shut off
HF warnings
Do not transmit when: anyone is on or near the helicopter, the transmission access doors are open, the blades are folded, personnel are seated within 30 cm of the window, or personnel are seated within 60 cm of the HF coupler
HF coupler limitation
2.0 -23.0 MHz
Typical UHF comms panel set up
ON, OP, Plain
ICS ALT modes
ALT 1
ALT 2
1- audio and Microphone signals pass through the isolation amplifier
2- audio and microphone signals pass through the microphone amplifier
VHF/AM range
116.0-151.975
VHF/FM range
- 0-173.9975
* 2.5Khz increments
How many channels does the VHF/FM Sabre radio provide and what are its main uses
12 preselected channels
Mainly used to provide hoisting and back up LSO communications as required as well as SAR Ops
Emergency frequencies
121.5 Mhz VHF/AM
Ch 16 VHF/FM
243Mhz UHF
406 MHz UHF
What radar control panel settings affect ASP
Gain, STC, tilt
What must happen prior to the radar being switched to standby
Number one and two engines running
When should the radar be switched to standby
Post landing, hot fuelling, HIFR check, prior to hoisting or slinging
Is the ASP certified for navigation
No
ASP inflight inputs
GPS px info TH from GHARS via radar Radar AIS Camera
G TRAC
ASP power
CBs?
28VDC direct from primary bus
3CBs
ASP post flight outputs
GTI RAG Gold (OTH plot) TH data Images from camera Radar raw data AIS data GPS data
Doppler outputs
GAG A Ho Ground velocity indicator (GVI) ASN 123 GHARS ASE Hover indicator
Which systems use direction finding
VHF AM and FM, UHF, OTPI
What is the hall down sheer limit
6000 PSI + or -500
