Limitation UH60 Flashcards
Rotor Brake/Gust Lock
Emergency Max Rotor Speed
76%
Rotor Brake/Gust Lock
Below NR%
40%
Rotor Brake/Gust Lock
Engine OFF <12 SEC.
150-180 PSI
Rotor Brake/Gust Lock
MIN/MAX Rotor Brake
450/690 PSI
Rotor Brake/Gust Lock Operating against the gust lock is ____________
prohibited
Slope Limitations
NOSE UP/RIGHT/LEFT
15 DEG
Slope Limitations
NOSE DOWN
6 DEG
Slope Limitations
Max Tail Wind
15 KTS
Landing Gear Limitations
Gross Weight Up to 16,825 LBS: Level
540 FPM
Landing Gear Limitations
Gross Weight Up to 16,825 LBS: Slope
360 FPM
Landing Gear Limitations
Gross Weight Above 16, 825 LBS: Level
300 FPM
Landing Gear Limitations
Gross Weight Above 16,825 LBS: Slope
180 FPM
APU Operations
43*C Engine/Rotor ON
30 minutes
APU operations
51*C Engine/Rotor OFF
Continuous
APU Operations
APU Oil Hot Caution
30 Minutes
Max Airspeed/Wind Limits
VNE
193 KTS
Max Airspeed/Wind Limits
Landing Light Extended Prior To:
130 KTS
Max Airspeed/Wind Limits: Landing Light Max Speed Extended
180 KTS
Max Airspeed/Wind Limits
Search Light Extended Prior To
100 KTS
Max Airspeed/Wind Limits
Search Light Max Speed Extended
180 KTS
Max Airspeed/Wind Limits
1 Hydraulic Pump/1 SAS INOP
170 KTS
Max Airspeed/Wind Limits
2 Hydraulic Pump/2 SAS INOP
150 KTS
Max Airspeed/Wind Limits
2 Hydraulic Pump/2 SAS INO (IMC)
140 KTS
Max Airspeed/Wind Limits
Cabin Doors Open
145 KTS
Max Airspeed/Wind Limits
Stabilator INOP Autorotation Airspeed Limit
120 KTS
Max Airspeed/Wind Limits
Stabilator Full Down at Speeds Below
40 KTS
Max Airspeed/Wind Limits
Stabilator Set at 0* Above
40 KTS
Max Airspeed/Wind Limits
Max Autorotation Airspeed Below 16,825
150 KTS
Max Airspeed/Wind Limits
Max Autorotation Airspeed Above 16,825 LBS
130 KTS
Max Airspeed/Wind Limits
Max Airpseed OEI
130 KTS
Max Airspeed/Wind Limits
Max Forward Touchdown Speed Limit
60
Max Airspeed/Wind Limits
Rotor Start & Stop Winds
45 KTS
Max Airspeed/Wind Limits
Side/Rearward Hover Winds
45 KTS
Prohibited Manuevers
Hovering Turns
30*/sec
Prohibited Maneuvers
Max Pitch
30*
Prohibited Maneuvers
Max Roll
60*
Prohibited Maneuvers
Simultaneous moving of both ________ levers to ______ or ______ (Throttle Chop) in flight is prohibited
EPC
IDLE
OFF
Prohibited Maneuvers
Rearward Ground Taxi is __________
prohibited
Cargo Hook Limits
Max Load
9000 LBS
Cargo Hook Limits
Max Bank Angle
30*
Cargo Hook Limits
Rearward Flight
35 KTS
High Speed Yaw Maneuvers
Avoid abrupt full pedal inputs above:
80 KTS
Flight in Icing Conditions
Equipment Installed, Operational, & Turned On Permitted to Fly into Trace or Light Icing (List all 5)
- Windshield Anti-Ice
- Pitot Heat
- Engine Anti-ice
- Engine Inlet Anti-ice Modulating Valve
- Insulated Ambient Air Sensing Tube
Flight in Icing Conditions
Flight into heavy or severe icing is __________________
Prohibited
Turbulence & Thunderstorm Operation
Intentional flight into severe turbulence is ______________
Prohibited
Turbulence & Thunderstorm Operation
Intentional flight into severe thunderstorms is ______________
Prohibited
Turbulence & Thunderstorm Operation
Intentional flight into turbulence with a sling load and an INOP collective trim is ___________
Prohibited
Blue Force Tracker Temperature Limits
Normal Operating Temperature *F
-6
Blue Force Tracker Temperature Limits
Normal Operating Temperature *C
-26-71*c
NP1/NP2
12 Second Transient
105-107%
NP1/NP2
High Transient
101-105%
NP1/NP2
Continuous
95-101%
NP1/NP2
Low Transient
91-95%
NP1/NP2
Avoid Operations High
60-90%
NP1/NP2
Avoid Operations Low
20-40%
NR Power ON
High Transient
101-107%
NR Power ON Continuous
95-101%
NR Power ON
Low Transient
91-95%
NR Power OFF
Maximum
110%
NR Power OFF
Transient
105-110%
NR Power OFF
Normal
90-105%
NG
12 Second Transient
105-106%
NG
Continuous
0-105%
10 Second Transient-Dual Engine
Above 80 KIAS
100-144%
10 Second Transient-Dual Engine
80 KIAS or Below
120-144%
10 Second Transient-Single Engine
10 Second Transient
135-144%
Continuous - Single Engine
Continuous
0-135%
Continuous-Dual Engine
Above 80 KIAS
0-100%
Continuous-Dual Engine
80 KIAS or Below
0-120%
TGT
12 Second Transient
903-949*C
TGT
2.5 Minute Transient (Continuous Power)
879-903*C
TGT
Start Abort
851*C
TGT
10 Minute Limit
846-879*C
TGT
30 Minute Limit
793-846*C
TGT
Normal
0-793*C
Engine Oil Pressure
5 Minute Limit
100-120 PSI
Engine Oil Pressure
Continuous
26-100 PSI
Engine Oil Pressure
IDLE
22-26 PSI
Engine Oil Temperature
30 Minute Limit
135-150*C
Engine Oil Temperature
Continuous
-20-135*C
Transmission Oil Pressure
Precautionary
65-130 PSI
Transmission Oil Pressure
Continuous
30-65 PSI
Transmission Oil Pressure
IDLE & Transient
20-30 PSI
Transmission Oil Pressure
>10 Nose UP
30-35 PSI
Transmission Oil Pressure
>15 Nose UP
10-15 PSI
Transmission Oil Temperature
Precautionary
105-140
Transmission Oil Temperature
Continuous
-20-105
Back Up Pump Operations
Temperature (1 of 3)
-54-32*C
Back Up Pump Operations
Temperature (2 of 3)
33-38*C
Back Up Pump Operations
Temperature (3 of 3)
39-52*C
Back Up Pump Operations
Operation/Cooldown (1 of 3)
Unlimited/ n/a
Back Up Pump Operations
Operation/Cooldown (2 of 3)
24/72 minutes
Back Up Pump Operations
Operations/Cooldown (3 of 3)
16/48 minutes
Engine Starter Limit
<15*C
2 Starts/3 Minute Rest/2 Starts/30 Minute Rest
Engine Starter Limit
15-52*C
2 Starts/30 Minute Rest
Engine Starter Limit
Required Before Additional Starts
30 Minutes
Windshield Anti-Ice Limitations
Anti-Ice Check Max Temperature *C
27*C
Windshield Anti-ice Limitations
Anti-ice Check Max Temperature *F
80*F
DUAL-ENGINE FAILURE
Indications:
_________________—–__________________—–___________
*
*
Immediate Actions
1. _________________________________________
1 ENG OUT + #2 ENG OUT + Steady Tone
*Change in NP, TGT, NG, Q, P, NR, ENG OUT warnings and audio
*Change in engine noise
- Autorotate
SINGLE ENGINE FAILURE
Indications
_____________—–________________—–________________
*___________________________
*___________________________
Additional Indications
__________—–__________
__________—–__________
Immediate Actions
1. _______________________________(if possible)
2. ___________________________-________________________
1 ENG OUT - or - #2E NG OUT -or - Steady Tone
*Changes in NP, TGT, NG, Q, P, NR, ENG OUT warnings and audio
*Change in engine noise
ENG 1 OIL PRESS - or - ENG 2 OIL PRESS
FUEL 1 PRESS LOW - or - FUEL 2 PRESS LOW
- Achieve safe single engine airspeed (if possible)
- External cargo/stores - Jettison (if required)
FIRES
Indications
_____________
*________________________________________
*________________________________________
*________________________________________
If ENG EMER OFF Handle/APU fire T-handle illuminates in flight:
1. ____________________-_______________________________________________
2. _____________________________-______________________________
3. ______________________________________-_____________(as appropriate)
4. ____________________-_______________________________________________
If an electrical fire is present:
1. _________________________________-________________
Urgency to land
____________________
FIRE
*ENG EMER OFF HANDLE-illuminated
*Smoke trail/visible flames/visible arcing or flame, sharp smell
- Establish - airspeed of 80 KIAS or less
- ENG POWER CONT lever - OFF
- ENG EMER OFF handle/APU fire Thandle - Pull (as appropriate)
- FIRE EXTGH switch - MAIN/RESERVE as required
- BATT and GENERATORS switches - OFF
LAND AS SOON AS POSSIBLE
ENGINE CONTROL MALFUNCTION - (DEC/EDECU) LOW SIDE FAILURE
Indications
_______________—______________
*Decreasing NR
*Low Q/TGT malfunctioning engine and high Q/TGT on other engine.
Immediate Actions
If an engine control unit fails to the low side and the other engine is unable to provide sufficient torque, NR will decrease
If NR continues to decrease and single engine flight is not possible:
1. ______________________________-__________________________(Maintain Q approximately 10% below other engine)
LOW ROTOR R.P.M. + “Steady Tone”
- Engine Power Control lever (low Q/TGT engine) - LOCKOUT (Maintain Q approximately 10% below other engine)
The Term Lockout is defined as: __________________________
Manual control of engine RPM while bypassing DEC/EDECU functions.
STABILATOR MALFUNCTION-AUTO MODE FAILURE
1. _____________________-______________ (as required to arrest nose down pitch rate.)
- Cyclic mounted stabilator slew-up switch - Adjust (as required to arrest nose down pitch rate)
FLIGHT CONTROL/ROTOR SYSTEM VIBRATIONS OR MALFUNCTIONS ON GROUND
Indications
*Feedback
*Main rotor/Tail rotor vibration/Severe main rotor flapping
*Binding
*Resistance
*Sloppiness
Immedeate Actions
1. ___________________-______________
2. ___________________-______________
3. ___________________-______________
Urgency to Land
1. ___________________________________________
- ENG POWER CONT levers - OFF
- ENG FUEL SYS selectors - OFF
- FUEL BOOST PUMP switche(s) - Off
- LAND AS SOON AS POSSIBLE
LIGHTNING STRIKE
Indications
*Immediate maximum power
*System instruments may be inoperative
*Loss of automatic flight control functions
*Loss of electric power
Immediate Actions
1. ______________________________-_________(as required to control NP and NR)
Urgency to Land
_____________________________________________
- ENG POWER CONT levers - Adjust (as required to control NP and NR)
LAND AS SOON AS POSSIBLE
MAIN TRANSMISSION FAILURE
Indications
*NR decrease from 100% to 96% with an increase in Q during steady state flight
*No engine malfunctions
*Unusual helicopter vibrations
Urgency to Land
1. __________________________: (__________________________)
- LAND AS SOON AS POSSIBLE: (Keep power applied to the main transmission during descent and landing)
LOSS OF TAIL ROTOR CONTROL
Indications
*Nose of the helicopter will yaw left/right regardless of airspeed
*At higher airspeed, a right yaw may develop more slowly but may continue to increase
*At high power setting, a left yaw may develop more slowly, but can become more significant if power is decreased
*If tail rotor components are lost, the nose will pitch down. Continued level flight may not be possible following this type of failure.
Immediate Actions
If during cruise flight a right yaw becomes uncontrollable:
1. _______________-_____________________
2. _______________-_____________________(during deceleration when intended point of landing is assured)
If at low airspeed or hover a right yaw becomes uncontrollable:
3. _______________-_____________________
4. _______________-_____________________(5-10 feet above touchdown)
If an uncontrolled left yaw develops during low aispeed or hover:
5. _______________-_____________________
6. _______________-_____________________(NR will decrease)
7. _______________-_____________________(5-10 feet above touchdown)
8. _______________-_____________________ for landing
- AUTOROTATE - Maintain airspeed at or above 80 KIAS
- ENG POWER CONT LEVERS - OFF (during deceleration when intended point of landing is assured)
- Collective - Reduce
- ENG POWER CONT levers - OFF (5-10 feet above touchdown)
- ENG POWER CONT levers - Retard
- Collective - Increase (NR will decrease)
- ENG POWER CONT levers - OFF 5-10 feet above touchdown)
- Collective - Adjust for landing
FUEL 1 BYPASS AND FUEL 2 BYPASS
Indications
__________—__________
Urgency to Land
1. ________________________________________
- LAND AS SOON AS POSSIBLE
FUEL 1 PRESS LOW AND FUEL 2 PRESS LOW
Indications
__________—__________
Urgency to Land
1. ________________________________________
- LAND AS SOON AS POSSIBLE
HYD PUMP 1 FAIL AND HYD PUMP 2 FAIL
Indications
__________—__________
Additional indications
__________—__________—__________—__________—__________
Urgency to Land
1. ________________________________(Restrict control movements to moderate rate)
HYD PUMP 1 FAIL + HYD PUMP 2 FAIL
TRIM FAIL + FPS FAIL + T/R SERVO 1 FAIL + T/R SERVO 2 ON + BACK-UP PUMP ON
- LAND AS SOON AS POSSIBLE
HYD PUMP 1 FAIL WITH NO BACK-UP PUMP ON ADVISORY
Indications
__________—__________—__________
Immediate Actions
1. ______________________-_____________
HYD PUMP 1 FAIL + T/R SERVO 1 FAIL + PRI SERVO 1 FAIL
- BACK-UP HYD PUMP switch - ON
T/R SERVO 1 FAIL WITH NO BACK-UP PUMP ON ADVISORY OR T/R SERVO 2 ON ADVISORY DOES NOT APPEAR
Indications
__________
Immediate Actions
1. ___________________________-______
Urgency to Land
LAND AS SOON AS PRACTICABLE
T/R SERVO 1 FAIL
- TAIL SERVO switch - BACK-UP
STABILATOR UNCOMMANDED NOSE DOWN PITCH ATTITUDE CHANGE
Indications: Uncommanded nose down pitch attitude occurs
Immediate Actions:
1. _____________________________-__________(as required to arrest nose down pitch rate)
Urgency to Land
LAND AS SOON AS PRACTICABLE
- Cyclic mounted stabilator slew-up switch - adjust (as required to arrest nose down pitch rate)
COUPLED FLIGHT DIRECTOR MALFUNCTION
Indications: Any uncommanded changes in pitch, roll, or yaw other than those observed in normal flight conditions when coupled to the flight director.
Immediate Actions:
1. _______________-_____________________
If coupled FD does not disengage:
2. _______________-_____________________
If coupled FD does not disengage:
3. _______________-_____________________
After FD is uncoupled:
4. _______________-_____________________
- RMT SBY swithc - Press to disengage FD modes
- CPLD switch - Press to uncouple FD
- FPS and TRIM switches - OFF
- FPS and TRIM switches - ON
AFCS
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________
- SAS
- Trim
- FPS
- Stabilator
- Coupled Flight Director
FPS
Basic autopilot-Enhances ______________ through ______________ in pitch, roll, and yaw. It is the “Brain”. When coupled with Trim, FPS has ______ control auth at ______ per sec
Static stability
Long term rate dampening
100%
10%
FPS
Below 50 KTS: Above 50 KTS:
1. 1.
2. 2.
3. 3.
- Att. hold PITCH 1. Att. Hold
- Att. hold ROLL 2. Att. Hold
- Hdg Hold YAW 3. Head Hold/Tn coor
FPS
These systems must be ______ and _________ for FPS to func. at 100%
1. ____________
2. ____________
3. ____________
4. ____________
on
operational
1. SAS 1 and/or SAS 2
2. SAS/Boost
3. Trim
4. Stabilator (helps, but not required)
TRIM
Provies a __________ and ____________ holding force for _____, ______, _____, and _____. Consists of 3 electromechanical actuators (__________, __________, __________), and 1 electrohydromechanical actuator (_________).
_________/_________ required for operation.
Slip clutch req. _____lbs max in yaw, _____ lbs max in roll, _____ lbs max collective during actuator jam. FCC monitors ____________, will turn off ____________________.
gradient
detent
pitch, roll, collective, yaw
roll, yaw, collective
pitch
SAS/Boost
80
22
13
continuously
driving trim actuator
AVCS
Reduces __________ and ______________ vibrations by mechanically generating additional vibrations that are ______________________ with the main rotor (_________________). (1 FG - _____________lbs, 2 FG ______________ lbs)
Uses ____ Force Generators, ___ MU’s each
cabin
cockpit
out-of-phase
90-105 NR
1,000
450
3
2
SAS 1&2
Provides _______________________ in pitch, roll, and yaw axes. Enhances turn coord >___kts. Hover augment <_____kts _____% cont. auth. Ea. controlled by respective _____ computers.
Input:
1. _________, ________, and _________ signals from resp. ________(Nose)
2. __________, air data computer
3. Malf indicated by ______________, reset CPTR 1/2, or turn off that SAS
short term rate dampening
50
50
5
FCC
1. pitch, roll, yaw, EGIs
2. Airspeed
3. erratic movement
STABILATOR
Variable __________________ airfoil that ________ the handling qualities in the pitch axis in __________ flight.
SCALP
1. ____________ w/rotor downwash at low speed (below _____kts) to minimize nose up attitude from downwash. (_____,_____)
2. ___________________ to minimize ________ attitude excursions due to ______________.
3. ________________________ decreases above _____kts to improve ____________________. (_____,_____)
4. ________________________ to _______________ to reduce susceptibility to _____. Stab ___ for right pedal, stab ___ for left pedal. (_______________)
5. ________________________ to improve dynamic stability. Dampen __________________ due to turbulence of “G” forces. (_____,_____)
angle of incidence
enhances
- Streamlines, 30 kts, (ADC, FCC)
- Collective Coupling, pitch, collective inputs
- Angle of Incidence, 30 kts, static stability (ADC,FCC)
- Lateral Sideslip, pitch coupling, gusts, up, down, (Lat. accelerometers)
- Pitch Rate Feedback, pitch excursions, (EGI,FCC)
ODV
HOPS
1. ____________ shuts fuel flow at _____*C, NG ,____%, Np<____%
2. ____________ (NP) from ______ at _______+-1%
3. ____________ main fuel manifold and allows ____________ of ___________ for purging.
4. ____________ fuel through _________ to ____________ for starting & engine operation.
- Hot start prevention, 900*C, 60%, 50%
- Over-speed protection, DEC, 120 +- 1%
- Purges, back-flow, high-pressure air
- Sends, manifold, injectors
HMU
Basic ___________; incl. __________ fuel pump & ________________ servo-actuator.
PM CAN VDTO
1. ____________ fuel at __________
- ____________ fuel to ______ in response to ______, _____, ___ motor from DEC, & _________ variables.
- ____________ through the _____. When the collective is moved, ____ is reset for immediate _____ response.
- ____________ flow limiting preventing _____________, __________, or ___________.
- ____________-Limits ______________ under low temp conditions.
- ____________ of the ___________________________ for optimum performance.
- ________________________________________________. Allows pilot to mechanically bypass _________________.
- ____________ To fine tune ______________. Can be overridden in _____________.
- ____________for manual _____ priming, to remove air from _____.
fuel control, high press., variable geometry
1. pumps, high pressure
- Meters, ODV, PAS, LDS, Q, engine
- Collective Pitch Compensation, LDS, Ng, Np
- Accel/Decel, compressor stalls, engine damage, flame out
- Ng limiting, max torque available
- Variable Geometry Positioning, inlet guide vanes
- DEC lockout PAS Override & Control with DEC Inoperative, torque motor inputs
- Torque Motor to Trim NG Output, engine output, DEC lockout
- Opens Vapor Vent, HMU, HMU
DEC
Controls ____________ of engines and transmits operation info to ____________.
TINT SHHOT F
- ____________: Limits fuel flow when reaching appx. _____ Dual Eng., _____(___min) when opp Q is <50%
- ____________ DEC will maintain _____ reference
- ____________ from the cockpit, (INCR/DECR from _____-_____%)
- ____________ Increase Q of ______ side to match up to ___% NP above reference.
- ____________: Sends signals to the cockpit for___, ___, and ___
- ____________ Sends signals to _________________
- ____________ Tells ___ to shut off fuel when _____*C is reached, Ng<___%, Np<___%.
- ____________Triggered when Np reaches ______+-1%
- ____________ 4 to 1 improvement to compensate for _________________. Uses collective position xducer signal.
- ____________DEC code sent to _________ indicators and _________ status page.
electronic functions, cockpit
- TGT Limiting, 879, 903(2.5 min)
- Isochronous NP Governing, NP
- NP Reference, 96-100%
- Torque Matching/Load Sharing, low, 3%
- Signals to Cockpit, Np, Q, TGT
- History counter, history counter
- Hot Start Preventer, ODV, 900*C, 60%, 50%
- Overspeed Protection, 120 +- 1%
- Transient Droop Compensation, transient rotor droop
- Fault Monitor, ENG Q, FMS DEC
Power Pod
1. Displays ___, ___, ___, ___, and ___
2. NG displays only above _____% NG or NG1/NG2 difference >= ___% or _____ engine out.
3. TGT displays only above _____C or TGT difference >=___C or _____ out
- NR, NP, Q, NG, TGT
- 100%, 5%, DCU
- 793C, 75C, DCU
Stormscope WX-500
1. Detects withing ____NM x or +
2. Stores up to ________ individual _____ or _____ positions for ___ minutes.
3. Maximum of _____ most recent strikes and cells are displayed at any one time.
- 200
- 3600, strike, cell
- 128
Weight-On Wheels Switch
CHAFF AIM TUBE
- ____________: IBIT, erase on gnd
- ____________ leak test disabled in flight
- ____________ for low NR disabled on the ground.
- ____________enabled in-flight
- ____________acft, EGI GC or GPC alignment IBIT on ground/EGI air alignment in flight
- ____________ Pitch, Roll Att hold/ Hdg hold/ Maneuvering Stab/ Rad Alt hold/ Airspeed hold - Enabled in-flight
- ____________Auto Zeroize enabled in flight.
- ____________status page activation on grnd
- ____________protection for B/U pump enabled on the ground
- ____________protection disabled in flight (right switch)
- ____________regardless of switch position enabled in flight. Disabled ond gnd unless Acc. Low
- ____________jettison disabled on ground. (right switch)
- CVR/FDR
- Hydraulic
- Audio
- Flight Dir. Modes
- FMS-Model
- AFCS
- IFF Mode 4
- MFD
- Thermal
- Underfreq.
- B/U Pump Auto OPN
- ESS
Engine Alternator NID
Three windings for three functions:
1. ___ signal to cockpit _______ (_____)
2. __________ power to the _________ during start. (_____)
3. _______ power (_____)
Loss of alternator does not result in __________ because of _____________ to DEC.
- NG, tachometer, green
- Ignition, exciters, yellow
- DEC yellow
Collective Capture:
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________
6. ____________
- ALT
- ALTP
- GS
- RALT
- GA
- VS
Pitch Capture:
1. ____________
2. ____________
3. ____________
4. ____________
- DCL
- IAS
- POSN (Hover)
- VHLD (Hover)
Roll Armed
1. ____________
2. ____________
Roll Capture:
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________
Roll Armed
1. LOC
2. NAV (VOR)
Roll Capture
1. BC
2. HDG
3. LNAV
4. LOC
5. NAV (VOR)
Fuel Flow in the Engine
- ____________
- ____________
- ____________
- ____________
- ____________
- Pump (engine driven)
- Fuel filter
- HMU
- Liquid to liquid cooler
- ODV
Mechanical Mixing
Collective to Pitch
compensates for rotor downwash on the stabilator
Mechanical Mixing
Collective to Roll
Translating Tendency
Mechanical Mixing
Collective to Yaw
Torque Effect
Mechanical Mixing
Yaw to Pitch
Lift component of Tail Rotor
Electronic Coupling
Collective to Airspeed to Yaw- Compensates for ___________ in addition to ____________ to _________ mixing based on ___________________ and ______________. FCC#___ commands yaw trim actuator _____% below ___kts, decreases until ____kts, none above _____kts.
torque effect
collective
yaw
collective position
airspeed
2
100%
40kts
100kts
100kts
