What are the #1 and #2 hydraulic pumps driven by?
Separate transmission accessory gearbox modules
What powers the backup hyd pump?
115 VAC electric motor
Each hydraulic pump is a ____________ pressure, __________ volume pump. They maintain the required _______ PSI over any rate of control movement for their own system.
constant, variable, 3000
Why do the hyd pumps have a return bypass capability?
To prevent the return filter from becoming completely clogged and causing hydrostatic lock up in the flight controls.
What does the #1 hyd pump supply pressure to?
The #1(first stage) fore, aft, and lateral primary servos and the #1 tail rotor servo
What does the #2 hyd pump supply pressure to?
The #2 (second stage) fore, aft, and lateral primary servos and components of the pilot assist area
What parts of the pilot assist area get pressure from the #2 pump?
Pitch, roll, and yaw SAS actuators, pitch boost servo, collective and yaw boost servos, and the pitch trim assembly
What does the pressure reducer in the pilot assist module do?
Reduces the 3000 PSI pump pressure to 1000 PSI for use by the pitch trim servo
The backup hydraulic pump can supply hydraulic pressure to the #1 and/or #2 hydraulic systems ________________ or _________________.
independently, simultaneously
Besides supplying pressure to the #1 and/or #2 systems, what does the backup pump pressurize?
The 2nd stage tail rotor servo and the APU accumulator
When will the backup pump be on?
It supplies hydraulic pressure to flight control components during ground checks (main rotors not turning), or
the following conditions:
#1 Reservoir Low (caution light)
#2 Hydraulic Pump (caution light)
#1 Hydraulic Pump (caution light)
APU Accumulator L
What prevents both primary servos from being turned off at the same time?
Electrical interlock
When will the RSVR 1 LOW, RSVR 2 LOW, or BACKUP RSVR LOW lights come on?
<60% hyd fluid in the resevoir
When will the hyd pump filter button pop? When will the return bypass?
70 psid, 100 psid
What 5 lights bring on the backup pump?
#1 Rsvr Low (Caution)
#1 Hyd Pump Fail (Caution)
#1 T/R Servo Fail (Caution)
#2 Hyd Pump Fail (Caution)
APU Accum Low (Advisory)
If a leak continues after LDI has tried to isolate it, where is the leak most likely to be?
1st or 2nd Stage Primary Servos
Hydraulic fluid levels may be up to ______ into the overfill zone on the hydraulic resevoir.
3/8
An entry should be made on 2408-13-1 if the TEMPE labels show an exceedance of ____ C or ____ F, and the A/C should not be flown until maintenance action has been taken.
132, 270
Do not service the rotor brake with the _____ ______, instead contact maintenance for assistance.
hand pump
Why is the use of the hand pump necessary to service the hydraulic pumps?
The pump modules are sealed from the atmosphere and a spring in the resevoir maintains a positive pressure on the system at all times.
____________ ___________ is th primary source of power to the aircraft. The primary system consists of ___ ___________ sytems
Alternating current, two independent
Eac generator is a ___/____ vac generator.
115/200
On the UH-60M the 200 amp DC converters have been replaced with ____ amp DC converters.
400
The two new __ VSC __ amp-hour SLAB batteries provide power to independent Battery, Battery Utility, and DC Essential buses, and also uninterrupted emergency power to essential systems for approximately ___ minutes.
24, 5, 15
The battery system is designed so that either battery can power both __ _________ ______.
DC Essential Buses
What are the 8 cold capsule lights?
EMER RLSE BATT GOOD
TST LT BATT LOW
OIL HOT ACC LOW
APU FAIL APU ON
How low is the battery charge if the BATT LOW CHARGE caution light is illuminated? How is this extinguished? Will it appear in flight?
<20.5 VDC; by applying AC power and the batteries begin to charge. No, unless battery is the only source of power.
The APU generator is ___-_____ ___/___ VAC, providing 20/23.8 KVA of power.
3-phase, 115/200
The APU generator is only capable of providing power to the aircraft electrical system when?
The main generators are not online.
If the APU generator is the only source of power the _________ _______ cannot be run while the ______ _____ is operating.
windshield anti-ice, backup pump
________ ________ operation still requires that at least one main generator be online and operating.
Blade de-ice
Fuel supply system consists primarily of the low pressure suction ________ ________ _______ _____, fuel filter, fuel filter bypass valve, fuel pressure sensor switch, HMU, and _________ ______ _______ (ODV).
engine driven boost pump; overspeed drain valve
Fuel flow path:
Pump (engine driven)
Fuel filter
HMU
Liquid to liquid cooler
ODV
Fuel low caution comes on when?
When does MAIN FUEL tape turn yellow on MFD?
When fuel in the respective cell reaches approx 172 lbs.
When fuel falls below 200 lbs. in respective tank.
T/F The APU fuel lines are self-sealing?
False
Where is APU fuel drawn from?
#1 fuel cell only
What is the pressure, GPM, and fuel level associated with pressure refuel?
55 PSI @ 300 GPM, 179.5 GAL/tank
What is the pressure, GPM, and fuel level associated with closed circuit refuel?
15 PSI @ 110 GPM, 178 GAL/tank
What is the fuel capacity for gravity refuel?
180 GAL/tank
What is the fuel pressure when only the engine driven boost pumps are in use?
9 PSI
What is the pressure when the submerged boost pumps are in use?
25-27 PSI
What are the four sections of the T701D engine?
cold, hot, power turbine, accessory
Where is the new additional NR sensor and Collective Position Transducer? What are they associated with?
left accessory module, MMU, Transient Droop Improvement
The transient compensation system provides significant droop improvement during some maneuvers by monitoring ________ _______, _________ rate of change, and ___ rate of change.
engine torque, collective, NR
The DEC does not have an insulation blanket, and it is cooled entirely by ____________________?
airflow through the scroll case
How many power sources does the DEC have? What are they?
Primary: engine alternator
Secondary: 400 Hz, 120 VAC airframe power
Complete loss of engine alternator will result in loss of ___ signal. Airframe power will sustain the DEC and there should be no failure of the __________________________, or loss of ___ and ____ indications.
NG, engine to the high side; Q, NP
Functions of the DEC (IN FLT HHOT)
1. Isochronous NP governing, DEC will maintain NP reference
2. NP reference FROM the cockpit (INCR/DECR 96-100%)
3. Fault idication (DEC codes on Q indicator and FMS status)
4. Load sharing/Torque matching (increase Q of low side up to 3% above NP referen
Why does NP signal appear sooner in the UH-60M vs. UH-60A?
Initial NP inidication is @ 4000RPM vs. 6000RPM from ECU
At what NP indication does Q begin to indicate? Why?
35% NP, indication is locked due to logic which prevents Q spike during RU/SD and yaw excursions caused by load sharing during in-flight restart.
What signals are required for Hot Start Prevention?
When does it come on?
AC Power, NP, NG, TGT
NG<60, NP<50, TGT>900
After hot start prevention takes place, how long must pilot wait for restart attempt?
300C TGT or 25 seconds
How can Hot Start Prevention be disabled in an emergency?
By holding either of the NP overspeed test buttons during the start. (upper console vic. Fire Detection Test switch)
TGT Limiting does not prevent overtemp during:
1. Compressor stall
2. Engine starts
3. EPCL in Lockout
Functions of the ODV: (HOPS)
1. Hot Start Prevention (shuts off fuel at 900C)
2. Overspeed Protection (NP 120%+/-1)
3. Purges main fuel manifold and allows back flow of high pressure air for purging
4. Sends fuel trhough manifold to inectors for starting and eng operation
Engine Alternator suplies power to:
Engine ignition exciter
DEC
Functions of the HMU: PMCANVDTO
1. Pumps fuel (at high pressure)
2. Meters fuel (to ODV in response to PAS, LDS, Q motor, & eng variables)
3. Collective Pitch Compenstation (through LDS)
4. Accel/Decel flow limiting (preventing comp stalls, eng damage, or flame out)
5. NG Limiting (limi
When in Lockout and the PCL of the affected engine is set to 10% below the other engine, why does the Q of the AE follow the good engine when collective inputs are made?
The LDS is still functioning.
Why is the engine oil temp limit now -20C?
EICAS is only able to report down to -20C.
What is the UH-60M DEC bias? Why?
112 degrees C
Due to the system's inability to display 4 digit numbers?
Functions of the MMU:
Collective to Pitch - compensates for downwash on aft fuselage and stab. Collective increase = slight forward disk
Collective to Roll - compensates for translating tendency. Collective increase = slight left disk
Collective to Yaw - compensates for torque
Electronic Coupling (Collective to Airspeed to Yaw) helps compensate for the _______ _______ effect caused by changes in collective position. It has the ability to __________ T/R pitch as airspeed increases.
torque effect; decrease
At what airspeed does maximum mixing of Electronice Coupling occur? When does it no longer occur?
0-40 KIAS; >100 KIAS
What controls Electronic Coupling?
#2 FCC
What are the five subsystems of AFCS?
1. Stability Augmentation System (SAS)
2. Trim
3. FPS
4. Coupled Flight Director
5. Stabilator
What does SAS do? (AFCS)
Provides short-term rate dampening in pitch, roll, and yaw axes.
What does SAS provide >50 KIAS? <50 KIAS?
Augments turn coordination; hover augmentation
Where does SAS get it's inputs?
Pitch, Roll, Yaw - EGIs
Airspeed - Air Data Computer
How much control authority does each SAS have? What controls it?
5% ea.; respective FCC
What does Trim do? (AFCS)
Provides control positioning and detent holding force gradient functions
What are the 4 Trim actuators
Electromagnetic - collective, roll, yaw
Electrohydromechanical - pitch
T/F SAS/Boost is required for operation of Trim
True
How much force is required by the slip clutches if there is a trim acutator jam?
Yaw - 80 lbs. max
Roll - 13 lbs. max
Collective - 22 lbs. max
What does FPS do? (AFCS)
Basic autopilot through long-term rate dampening functions in pitch, roll, yaw when coupled with trim
When coupled with trim, how much control authority does FPS have?
100%
What does FPS provide <50 KIAS? >50 KIAS?
<50 KIAS >50KIAS
Att Hold Pitch Att Hold
Att Hold Roll Att Hold
Hdg Hold Yaw Hdg Hold/Turn Coordination
What systems must be on/operational for FPS to function 100%?
1. SAS 1 and/or SAS 2
2. SAS/BOOST
3. Trim
4. Stabilator
What does the Coupled Flight Director do? (AFCS)
Provides a means for the pilot to select defined autopilot functions, automatic flight control positioning, and provides steering cues for display on the MFD when coupled
What does the Stabilator do? (AFCS)
Improves flying qualities wih the use of electromagnetic acutators in response to collective, airspeed, pitch rate, and lateral acceleration inputs
What is the Stabilator?
Variable angle of incidence airfoil that enhances handling qualities in the pitch axis in forward flight
Functions of the Stabilator: (SCALP)
1. Streamlines w/ rotor downwash at low airspeeds (<30 KIAS)
2. Collective Coupling (to min pitch att excursions due to collective inputs)
3. Angle of incidence decreases >30 KIAS (to improve stability; ADC+FCC)
4. Lateral sideslip to pitch coupling (redu
Stabilator inputs: (CLAP)
FCCs: collective stick position, lateral acceleration, airspeed, pitch rate data
What do the Air Data Computers provide to the FCCs? What are they connected to?
Airspeed, barometric altitude, barometric rate information;
Pitot-static system
What is the primary function of the Embedded Global Positioning/Inertial Navigation Units (EGIs)?
To compute attitude, heading, present position, and turn rate data
The EGIs are used in the ___________ system.
Stabilator
What are the #1 and #2 hydraulic pumps driven by?
Separate transmission accessory gearbox modules
What powers the backup hyd pump?
115 VAC electric motor
Each hydraulic pump is a ____________ pressure, __________ volume pump. They maintain the required _______ PSI over any rate of control movement for their own system.
constant, variable, 3000
Why do the hyd pumps have a return bypass capability?
To prevent the return filter from becoming completely clogged and causing hydrostatic lock up in the flight controls.
What does the #1 hyd pump supply pressure to?
The #1(first stage) fore, aft, and lateral primary servos and the #1 tail rotor servo
What does the #2 hyd pump supply pressure to?
The #2 (second stage) fore, aft, and lateral primary servos and components of the pilot assist area
What parts of the pilot assist area get pressure from the #2 pump?
Pitch, roll, and yaw SAS actuators, pitch boost servo, collective and yaw boost servos, and the pitch trim assembly
What does the pressure reducer in the pilot assist module do?
Reduces the 3000 PSI pump pressure to 1000 PSI for use by the pitch trim servo
The backup hydraulic pump can supply hydraulic pressure to the #1 and/or #2 hydraulic systems ________________ or _________________.
independently, simultaneously
Besides supplying pressure to the #1 and/or #2 systems, what does the backup pump pressurize?
The 2nd stage tail rotor servo and the APU accumulator
When will the backup pump be on?
It supplies hydraulic pressure to flight control components during ground checks (main rotors not turning), or
the following conditions:
#1 Reservoir Low (caution light)
#2 Hydraulic Pump (caution light)
#1 Hydraulic Pump (caution light)
APU Accumulator L
What prevents both primary servos from being turned off at the same time?
Electrical interlock
When will the RSVR 1 LOW, RSVR 2 LOW, or BACKUP RSVR LOW lights come on?
<60% hyd fluid in the resevoir
When will the hyd pump filter button pop? When will the return bypass?
70 psid, 100 psid
What 5 lights bring on the backup pump?
#1 Rsvr Low (Caution)
#1 Hyd Pump Fail (Caution)
#1 T/R Servo Fail (Caution)
#2 Hyd Pump Fail (Caution)
APU Accum Low (Advisory)
If a leak continues after LDI has tried to isolate it, where is the leak most likely to be?
1st or 2nd Stage Primary Servos
Hydraulic fluid levels may be up to ______ into the overfill zone on the hydraulic resevoir.
3/8
An entry should be made on 2408-13-1 if the TEMPE labels show an exceedance of ____ C or ____ F, and the A/C should not be flown until maintenance action has been taken.
132, 270
Do not service the rotor brake with the _____ ______, instead contact maintenance for assistance.
hand pump
Why is the use of the hand pump necessary to service the hydraulic pumps?
The pump modules are sealed from the atmosphere and a spring in the resevoir maintains a positive pressure on the system at all times.
____________ ___________ is th primary source of power to the aircraft. The primary system consists of ___ ___________ sytems
Alternating current, two independent
Eac generator is a ___/____ vac generator.
115/200
On the UH-60M the 200 amp DC converters have been replaced with ____ amp DC converters.
400
The two new __ VSC __ amp-hour SLAB batteries provide power to independent Battery, Battery Utility, and DC Essential buses, and also uninterrupted emergency power to essential systems for approximately ___ minutes.
24, 5, 15
The battery system is designed so that either battery can power both __ _________ ______.
DC Essential Buses
What are the 8 cold capsule lights?
EMER RLSE BATT GOOD
TST LT BATT LOW
OIL HOT ACC LOW
APU FAIL APU ON
How low is the battery charge if the BATT LOW CHARGE caution light is illuminated? How is this extinguished? Will it appear in flight?
<20.5 VDC; by applying AC power and the batteries begin to charge. No, unless battery is the only source of power.
The APU generator is ___-_____ ___/___ VAC, providing 20/23.8 KVA of power.
3-phase, 115/200
The APU generator is only capable of providing power to the aircraft electrical system when?
The main generators are not online.
If the APU generator is the only source of power the _________ _______ cannot be run while the ______ _____ is operating.
windshield anti-ice, backup pump
________ ________ operation still requires that at least one main generator be online and operating.
Blade de-ice
Fuel supply system consists primarily of the low pressure suction ________ ________ _______ _____, fuel filter, fuel filter bypass valve, fuel pressure sensor switch, HMU, and _________ ______ _______ (ODV).
engine driven boost pump; overspeed drain valve
Fuel flow path:
Pump (engine driven)
Fuel filter
HMU
Liquid to liquid cooler
ODV
Fuel low caution comes on when?
When does MAIN FUEL tape turn yellow on MFD?
When fuel in the respective cell reaches approx 172 lbs.
When fuel falls below 200 lbs. in respective tank.
T/F The APU fuel lines are self-sealing?
False
Where is APU fuel drawn from?
#1 fuel cell only
What is the pressure, GPM, and fuel level associated with pressure refuel?
55 PSI @ 300 GPM, 179.5 GAL/tank
What is the pressure, GPM, and fuel level associated with closed circuit refuel?
15 PSI @ 110 GPM, 178 GAL/tank
What is the fuel capacity for gravity refuel?
180 GAL/tank
What is the fuel pressure when only the engine driven boost pumps are in use?
9 PSI
What is the pressure when the submerged boost pumps are in use?
25-27 PSI
What are the four sections of the T701D engine?
cold, hot, power turbine, accessory
Where is the new additional NR sensor and Collective Position Transducer? What are they associated with?
left accessory module, MMU, Transient Droop Improvement
The transient compensation system provides significant droop improvement during some maneuvers by monitoring ________ _______, _________ rate of change, and ___ rate of change.
engine torque, collective, NR
The DEC does not have an insulation blanket, and it is cooled entirely by ____________________?
airflow through the scroll case
How many power sources does the DEC have? What are they?
Primary: engine alternator
Secondary: 400 Hz, 120 VAC airframe power
Complete loss of engine alternator will result in loss of ___ signal. Airframe power will sustain the DEC and there should be no failure of the __________________________, or loss of ___ and ____ indications.
NG, engine to the high side; Q, NP
Functions of the DEC (IN FLT HHOT)
1. Isochronous NP governing, DEC will maintain NP reference
2. NP reference FROM the cockpit (INCR/DECR 96-100%)
3. Fault idication (DEC codes on Q indicator and FMS status)
4. Load sharing/Torque matching (increase Q of low side up to 3% above NP referen
Why does NP signal appear sooner in the UH-60M vs. UH-60A?
Initial NP inidication is @ 4000RPM vs. 6000RPM from ECU
At what NP indication does Q begin to indicate? Why?
35% NP, indication is locked due to logic which prevents Q spike during RU/SD and yaw excursions caused by load sharing during in-flight restart.
What signals are required for Hot Start Prevention?
When does it come on?
AC Power, NP, NG, TGT
NG<60, NP<50, TGT>900
After hot start prevention takes place, how long must pilot wait for restart attempt?
300C TGT or 25 seconds
How can Hot Start Prevention be disabled in an emergency?
By holding either of the NP overspeed test buttons during the start. (upper console vic. Fire Detection Test switch)
TGT Limiting does not prevent overtemp during:
1. Compressor stall
2. Engine starts
3. EPCL in Lockout
Functions of the ODV: (HOPS)
1. Hot Start Prevention (shuts off fuel at 900C)
2. Overspeed Protection (NP 120%+/-1)
3. Purges main fuel manifold and allows back flow of high pressure air for purging
4. Sends fuel trhough manifold to inectors for starting and eng operation
Engine Alternator suplies power to:
Engine ignition exciter
DEC
Functions of the HMU: PMCANVDTO
1. Pumps fuel (at high pressure)
2. Meters fuel (to ODV in response to PAS, LDS, Q motor, & eng variables)
3. Collective Pitch Compenstation (through LDS)
4. Accel/Decel flow limiting (preventing comp stalls, eng damage, or flame out)
5. NG Limiting (limi
When in Lockout and the PCL of the affected engine is set to 10% below the other engine, why does the Q of the AE follow the good engine when collective inputs are made?
The LDS is still functioning.
Why is the engine oil temp limit now -20C?
EICAS is only able to report down to -20C.
What is the UH-60M DEC bias? Why?
112 degrees C
Due to the system's inability to display 4 digit numbers?
Functions of the MMU:
Collective to Pitch - compensates for downwash on aft fuselage and stab. Collective increase = slight forward disk
Collective to Roll - compensates for translating tendency. Collective increase = slight left disk
Collective to Yaw - compensates for torque
Electronic Coupling (Collective to Airspeed to Yaw) helps compensate for the _______ _______ effect caused by changes in collective position. It has the ability to __________ T/R pitch as airspeed increases.
torque effect; decrease
At what airspeed does maximum mixing of Electronice Coupling occur? When does it no longer occur?
0-40 KIAS; >100 KIAS
What controls Electronic Coupling?
#2 FCC
What are the five subsystems of AFCS?
1. Stability Augmentation System (SAS)
2. Trim
3. FPS
4. Coupled Flight Director
5. Stabilator
What does SAS do? (AFCS)
Provides short-term rate dampening in pitch, roll, and yaw axes.
What does SAS provide >50 KIAS? <50 KIAS?
Augments turn coordination; hover augmentation
Where does SAS get it's inputs?
Pitch, Roll, Yaw - EGIs
Airspeed - Air Data Computer
How much control authority does each SAS have? What controls it?
5% ea.; respective FCC
What does Trim do? (AFCS)
Provides control positioning and detent holding force gradient functions
What are the 4 Trim actuators
Electromagnetic - collective, roll, yaw
Electrohydromechanical - pitch
T/F SAS/Boost is required for operation of Trim
True
How much force is required by the slip clutches if there is a trim acutator jam?
Yaw - 80 lbs. max
Roll - 13 lbs. max
Collective - 22 lbs. max
What does FPS do? (AFCS)
Basic autopilot through long-term rate dampening functions in pitch, roll, yaw when coupled with trim
When coupled with trim, how much control authority does FPS have?
100%
What does FPS provide <50 KIAS? >50 KIAS?
<50 KIAS >50KIAS
Att Hold Pitch Att Hold
Att Hold Roll Att Hold
Hdg Hold Yaw Hdg Hold/Turn Coordination
What systems must be on/operational for FPS to function 100%?
1. SAS 1 and/or SAS 2
2. SAS/BOOST
3. Trim
4. Stabilator
What does the Coupled Flight Director do? (AFCS)
Provides a means for the pilot to select defined autopilot functions, automatic flight control positioning, and provides steering cues for display on the MFD when coupled
What does the Stabilator do? (AFCS)
Improves flying qualities wih the use of electromagnetic acutators in response to collective, airspeed, pitch rate, and lateral acceleration inputs
What is the Stabilator?
Variable angle of incidence airfoil that enhances handling qualities in the pitch axis in forward flight
Functions of the Stabilator: (SCALP)
1. Streamlines w/ rotor downwash at low airspeeds (<30 KIAS)
2. Collective Coupling (to min pitch att excursions due to collective inputs)
3. Angle of incidence decreases >30 KIAS (to improve stability; ADC+FCC)
4. Lateral sideslip to pitch coupling (redu
Stabilator inputs: (CLAP)
FCCs: collective stick position, lateral acceleration, airspeed, pitch rate data
What do the Air Data Computers provide to the FCCs? What are they connected to?
Airspeed, barometric altitude, barometric rate information;
Pitot-static system
What is the primary function of the Embedded Global Positioning/Inertial Navigation Units (EGIs)?
To compute attitude, heading, present position, and turn rate data
The EGIs are used in the ___________ system.
Stabilator