Flight Line supplement Flashcards
1
Q
Stabilator
A
Variable angle of incidence airfoil that enhances the handling quality in the pitch axis in forward flight
SCALP
- STREAMLINES WITH ROTOR DOWN WASH AT LOW SPEED ( BELOW 30 KNOTS) TO MINIMIZE NOSE UP ATTITUDE FROM DOWNWASH (ADC FCC)
- COLLECTIVE COUPLING TO MINIMIZE PITCH ATTITUDE EXCURSIONS DUE TO COLLECTIVE INPUTS (COLLECTIVE POSITION TRANSDUCERS)
- ANGLE OF INCIDENCE DECREASES ABOVE 30 KNOTS TO IMPROVE STATIC STABILITY (ADC FCC)
- LATERAL SIDE SLIP TO PITCH COUPLING TO REDUCE SUSCEPTIBILITY TO GUSTS. STABILATOR UP FOR RIGHT PEDAL STABILATOR DOWN FOR LEFT PEDAL (LATERAL ACCELEROMETERS)
- Pitch rate feedback to improve dynamic stability. Dampen pitch excursions due to turbulence or g-forces (EGI FCC)
2
Q
ODV
A
HOPS
- Hot start prevention shuts fuel flow at 900° c
- Overspeed protection (NP) from DEC at 120 plus or minus 1%
- Purges main fuel manifold and allows backflow of high pressure air for purging
- Sends fuel through manifold to injectors for starting and engine
3
Q
HMU
A
Hydro mechanical unit
Basic fuel control including high pressure fuel pump and variable geometry servo actuator
PM CAN VDTO
- PUMPS FUEL AT HIGH PRESSURE
- METERS FUEL TO ODV IN RESPONSE TO PAS, LDS, TORQUE MOTOR FROM DEC AND ENGINE
- COLLECTIVE PITCH COMPENSATION THROUGH THE LDS. WHEN THE COLLECTIVE IS MOVED NG IS RESET FOR IMMEDIATE NP RESPONSE
- ACCELERATES/DECELERATES FLOW LIMITING PREVENTING COMPRESSOR STALLS ENGINE DAMAGE OR FLAME OUT
- NG LIMITING- LIMITS MAX TORQUE AVAILABLE UNDER LOW TEMPERATURE CONDITIONS + HIGH
- VARIABLE GEOMETRY POSITIONING OF THE INLET GUIDE VEINS FOR OPTIMUM PERFORMANCE
- DEC/EDECU LOCKOUT PAS OVERRIDE AND CONTROL WITH ECU INOPERATIVE. ALLOWS PILOT TO MECHANICALLY BYPASS TORQUE MOTOR INPUTS
- TORQUE MOTOR TO TRIM NG OUTPUT. TO FINE-TUNE ENGINE OUTPUT. CAN BE OVERRIDDEN IN DEC LOCKOUT
- OPENS VAPOR VENT FOR MANUAL HMU PRIMING TO REMOVE AIR FROM HMU
4
Q
DEC
A
Digital Electronic Control
Controls electrical functions of engine and transmit operation info to cockpit
IN FLT HHOT
- ISOCHRONUS NP GOVERNING. DEC WILL MAINTAIN NP REFERENCE.
- NP REFERENCE FROM THE COCKPIT (INCREASE/DECREASE FROM 96 TO 100%)
- FAULT INDICATION. DEC CODE SENT TO CORRESPONDING ENGINE Q INDICATOR AND THE FMS DEC STATUS PAGE
- LOAD SHARING/TORK MATCHING. INCREASE Q OF LOW SIDE TO MATCH UP TO 3% NP ABOVE REFERENCE
- TRANSLATOR TROOP COMPENSATION. 4-1 IMPROVEMENT TO COMPENSATE FOR TRANSIENT ROTOR DROOP. USES COLLECTIVE POSITION TRANSDUCER SIGNAL
- HISTORY COUNTER. SENDS SIGNALS TO HISTORY COUNTER
- HOT START PREVENTER. TELLS ODV TO SHUT OFF FUEL WHEN 900°C IS REACHED IF NG <60 AND NP <50
- OVER SPEED PROTECTION. TRIGGERED WHEN NP REACHES 120 +/- 1%
- TGT LIMITING. LIMITS FUEL FLOW WHEN REACHING APPROXIMATELY 879 DUAL ENGINE, ALLOWS 903 (2.5 MIN) WHEN OPPOSITE Q <50%.
5
Q
EDECU
A
Enhanced digital engine control unit
Allows 2.5 min contingency power when:
NP drops to 96%
3% drop below NP REFERENCE
Drop from NP REFERENCE of 5%/sec
6
Q
Engine alternator
A
Three windings for three functions:
- Ng signal to cockpit tachometer (green)
- Ignition power to the exciters during start (yellow)
- DEC power (yellow)
Loss of alt. does not result in high-size failure
7
Q
Wait-On Wheels switch
A
CHAFF AIM TUBE
- CVR/FDR: IBIT, erase on gnd
- Hydraulic leak test disabled in flight
- Audio for low NR disabled on the ground
- Flight director modes enabled in-flight
- FMS-Model ACFT, EGI GC or GPS alignment IBIT on ground/ EGI air alignment in flight
- AFCS Pitch, Roll Att hold/ Hdg hold/ Maneuvering Stab/ Rad Alt hold/ Airspeed hold - Enabled in-flight
- IFF Mode 4-Auto Zeroize enabled in flight
- MFD status page activation on grnd
- Thermal protection for B/U pump enabled on the ground
- Under frequency protection disabled in Flight (Right switch)
- Backup pump auto open regardless of switch position enabled in flight. Disabled on ground unless accumulator low
- ESSS jettison disabled on ground (right switch)
8
Q
Equipment available with battery power only:
CVR/FDR, P inb
A
CVR/FDR, P inboard MFD,
