MH-65E Stan 2024 Questions and Answers
"TRUE/FALSE: Due to the Multifunction Displays (MFD) and most CAAS components being
AC powered initial engine starts shall be completed from the data referenced in the TDL 1/2 and
2/2 pages. ** Answ** TRUE
"The System Manager partitions are contained in which MFDs?
A. 1 & 2
B. 2 & 3
C. 3 & 4
D. 1 & 4" ** Answ** D. 1 & 4
TRUE/FALSE: There will be no aural warning if the Flight Director becomes uncoupled from
the AFCS. ** Answ** FALSE
In the event that primary flight information is lost on the MFDs the __________ can be
referenced for airspeed attitude and heading. ** Answ** SFI
The _______________ Page is the primary source for diagnosing and analyzing any warning
caution or advisory annunciation. ** Answ** ENGINE INDICATING AND CREW
ALERTING SYSTEM (EICAS)
"Which bus is not affected when placing the Emergency Electrical Cutoff Switch to OFF?
1. _________________________" ** Answ** BATTERY BUS
The Aerosonic Sensor Unit (ASU) of the SFI accepts pitot (total) and static pressure input from
the _______________ Pitot/Static System. ** Answ** PILOT'S/NO. 2
,The Static Bypass Switch for the _______________ static system is located on the
_______________. ** Answ** PILOT'S/NO. 2
AVIONICS RACK PANEL.
The alternate static pressure valve is used to switch from the _______________ static pressure
ports to _________________________ pressure in the event of icing or an obstruction. **
Answ** EXTERNAL
INTERNAL CABIN
When using the training switch the idled engine spools down to ____ RPM N2 at a
preprogrammed rate and the good engine will increase power up to approximately 62% torque.
** Answ** 320
A safety feature built into the training switch FADEC logic ensures that the idled engine will
provide power up to the actual __________ stop in the event of NR mismanagement. **
Answ** OEI
TRUE/FALSE: Once an engine is shutdown by the DECU via the BIM overspeed protection is
automatically inhibited on the second engine. ** Answ** TRUE
_______________ and _______________ components are labeled conventially No. 1 for the left
side and No. 2 for the right side. ** Answ** AIRFRAME
AVIONICS
Aircrew shall not use the ____________________ if a Level 1 FADEC failure is noted. **
Answ** TRNG SWITCH
The lift capability of the rotor system is limited by the actual collective stop and NR will not
increase above __________ RPM in the Training Mode until the collective is reduced to a power
level below the good engine topping. ** Answ** 320
,A Level _____ FADEC (redundancy failure) can be accessed by selecting the Engine Faults page
on the CDU. ** Answ** 1
A Level _______ FADEC failure is indicated on the EICAS page with a GOV LVL 1 caution
when the FADEC control switch is in the IDLE or OFF position. ** Answ** 1
A Level 1 FADEC failure is indicated on the EICAS page with a _____________ caution. **
Answ** GOV LVL 1
A Level ______ FADEC failure is indicated on the EICAS page with a GOV LVL 2 caution.
** Answ** 2
"A Level 2 FADEC failure is indicated on the EICAS page with a ____________________
caution.
A. GOV LVL 1
B. GOV LVL 2
C. NONREDUNDANT FAILURE
D. FADEC FAIL" ** Answ** B. GOV LVL2
Level _____ or major FADEC failure is indicated on the EICAS page with a FADEC1/FADEC2
FAIL caution along with illumination of the red engine status light. ** Answ** 3
Level 3 or major FADEC failure is indicated on the EICAS page with a FADEC1/FADEC2
FAIL caution along with illumination of the red ____________________. ** Answ**
ENGINE STATUS LIGHT
TRUE/FALSE: During a Level 3 FADEC Failure fuel flow on the affected engine will be frozen
at its present value. ** Answ** TRUE
, Due to FADEC logic returning the TRNG switch back to the flight position should be completed
with the PFD Torque Display less than ________ % and the NR stable at 355 RPM (or 365
RPM) to preclude use of _________________________. ** Answ** 40%
ACTUAL OEI TIMES
"The NR HI mode is used during hover flight single-engine operations and other demanding low
speed maneuvers as it provides a greater margin for NR droop as well as
____________________.
A. increased engine performance
B. increased tail rotor authority
C. increased torque margin
D. significantly greater lift capability" ** Answ** B. INCREASED TAIL ROTOR
AUTHORITY
When one or more of the parameters associated with an engine are in the caution range the data
display label and perimeter (box) will be ______________. In the warning range the data display
label and perimeter (box) will be ______________. ** Answ** YELLOW
RED
No fire extinguishing capability is provided for the ____________________. ** Answ**
MAIN GEARBOX COMPARTMENT
If operating above __________ ft MSL both boost pumps shall be on to prevent a possible feed
tank failure. ** Answ** 8000
In the normal hover attitude (4 degrees nose up) indicated fuel is approximately __________ %
less than at a nose-level attitude. ** Answ** 10%
When the fuel quantity on the individual side drops to __________ lbs. the respective fuel
quantity and tape will turn yellow. ** Answ** 100
"TRUE/FALSE: Due to the Multifunction Displays (MFD) and most CAAS components being
AC powered initial engine starts shall be completed from the data referenced in the TDL 1/2 and
2/2 pages. ** Answ** TRUE
"The System Manager partitions are contained in which MFDs?
A. 1 & 2
B. 2 & 3
C. 3 & 4
D. 1 & 4" ** Answ** D. 1 & 4
TRUE/FALSE: There will be no aural warning if the Flight Director becomes uncoupled from
the AFCS. ** Answ** FALSE
In the event that primary flight information is lost on the MFDs the __________ can be
referenced for airspeed attitude and heading. ** Answ** SFI
The _______________ Page is the primary source for diagnosing and analyzing any warning
caution or advisory annunciation. ** Answ** ENGINE INDICATING AND CREW
ALERTING SYSTEM (EICAS)
"Which bus is not affected when placing the Emergency Electrical Cutoff Switch to OFF?
1. _________________________" ** Answ** BATTERY BUS
The Aerosonic Sensor Unit (ASU) of the SFI accepts pitot (total) and static pressure input from
the _______________ Pitot/Static System. ** Answ** PILOT'S/NO. 2
,The Static Bypass Switch for the _______________ static system is located on the
_______________. ** Answ** PILOT'S/NO. 2
AVIONICS RACK PANEL.
The alternate static pressure valve is used to switch from the _______________ static pressure
ports to _________________________ pressure in the event of icing or an obstruction. **
Answ** EXTERNAL
INTERNAL CABIN
When using the training switch the idled engine spools down to ____ RPM N2 at a
preprogrammed rate and the good engine will increase power up to approximately 62% torque.
** Answ** 320
A safety feature built into the training switch FADEC logic ensures that the idled engine will
provide power up to the actual __________ stop in the event of NR mismanagement. **
Answ** OEI
TRUE/FALSE: Once an engine is shutdown by the DECU via the BIM overspeed protection is
automatically inhibited on the second engine. ** Answ** TRUE
_______________ and _______________ components are labeled conventially No. 1 for the left
side and No. 2 for the right side. ** Answ** AIRFRAME
AVIONICS
Aircrew shall not use the ____________________ if a Level 1 FADEC failure is noted. **
Answ** TRNG SWITCH
The lift capability of the rotor system is limited by the actual collective stop and NR will not
increase above __________ RPM in the Training Mode until the collective is reduced to a power
level below the good engine topping. ** Answ** 320
,A Level _____ FADEC (redundancy failure) can be accessed by selecting the Engine Faults page
on the CDU. ** Answ** 1
A Level _______ FADEC failure is indicated on the EICAS page with a GOV LVL 1 caution
when the FADEC control switch is in the IDLE or OFF position. ** Answ** 1
A Level 1 FADEC failure is indicated on the EICAS page with a _____________ caution. **
Answ** GOV LVL 1
A Level ______ FADEC failure is indicated on the EICAS page with a GOV LVL 2 caution.
** Answ** 2
"A Level 2 FADEC failure is indicated on the EICAS page with a ____________________
caution.
A. GOV LVL 1
B. GOV LVL 2
C. NONREDUNDANT FAILURE
D. FADEC FAIL" ** Answ** B. GOV LVL2
Level _____ or major FADEC failure is indicated on the EICAS page with a FADEC1/FADEC2
FAIL caution along with illumination of the red engine status light. ** Answ** 3
Level 3 or major FADEC failure is indicated on the EICAS page with a FADEC1/FADEC2
FAIL caution along with illumination of the red ____________________. ** Answ**
ENGINE STATUS LIGHT
TRUE/FALSE: During a Level 3 FADEC Failure fuel flow on the affected engine will be frozen
at its present value. ** Answ** TRUE
, Due to FADEC logic returning the TRNG switch back to the flight position should be completed
with the PFD Torque Display less than ________ % and the NR stable at 355 RPM (or 365
RPM) to preclude use of _________________________. ** Answ** 40%
ACTUAL OEI TIMES
"The NR HI mode is used during hover flight single-engine operations and other demanding low
speed maneuvers as it provides a greater margin for NR droop as well as
____________________.
A. increased engine performance
B. increased tail rotor authority
C. increased torque margin
D. significantly greater lift capability" ** Answ** B. INCREASED TAIL ROTOR
AUTHORITY
When one or more of the parameters associated with an engine are in the caution range the data
display label and perimeter (box) will be ______________. In the warning range the data display
label and perimeter (box) will be ______________. ** Answ** YELLOW
RED
No fire extinguishing capability is provided for the ____________________. ** Answ**
MAIN GEARBOX COMPARTMENT
If operating above __________ ft MSL both boost pumps shall be on to prevent a possible feed
tank failure. ** Answ** 8000
In the normal hover attitude (4 degrees nose up) indicated fuel is approximately __________ %
less than at a nose-level attitude. ** Answ** 10%
When the fuel quantity on the individual side drops to __________ lbs. the respective fuel
quantity and tape will turn yellow. ** Answ** 100
