Chapter 5 - Limitations Flashcards
NP Limitations
12 - Second Transient 105-107%
Transient (3) 101-105%
Continuous (2) 95-101%
Transient (1) 91-95%
NR (Rotor) Limitations
(Power On)
Power On
TRANSIENT 101 - 107%
TRANSIENT 95 - 101%
CONTINUOUS 91 - 95%
NR (Rotor) Limitations
Power OFF (Autorotation)
Power Off (Autorotation)
MAXIMUM 105 - 110%
TRANSIENT 90 - 105%
NORMAL 110%
UPPER RED RANGE BEGINS AT 110% TO CORRESPOND WITH THE POWER OFF LIMIT
NG (Gas Generator) Limitations
- NOTE:*
- NG DIGITAL READOUT WILL APPEAR WHEN NG INCREASES ABOVE 100%.*
12 SECOND TRANSIENT (2) 105 - 106%
CONTINUOUS (1) 0 - 105%
Torque (Q) Limitations
(10 Second Transient)
DUAL - ENGINE:
ABOVE 80 KIAS (4) 100 - 144%
80 KIAS OR BELOW 120 - 144%
SINGLE - ENGINE SINGLE 135 - 144%
Torque (Q) Limitations
(CONTINUOUS)
SINGLE - ENGINE 0 - 135%
DUAL - ENGINE:
ABOVE 80 KIAS 0 - 100%
AT OR BELOW 80 KIAS 0 - 120%
TGT Limitations
12 SECOND TRANSIENT 903 - 949 C
2.5 MINUTE TRANSIENT (CONTINGENCY POWER) (4) 879 - 903 C
START ABORT LIMIT 851 C
10 MINUTE LIMIT (3) 846 - 879 C
30 MINUTE LIMIT (2) 793 - 846 C
NORMAL (1) 0 - 793 C
NOTE: ON THE POWER POD TGT IS NOT DISPLAYED UNLESS ABOVE 793 C
ENGINE OIL TEMPERATURE Limits
ENGINE TEMP
30 MINUTE LIMIT (2) 135 - 150 C
CONTINUOUS (1) -20 - 135 C
ENGINE OIL PRESSURE Limits
ENGINE Pressure
5 MINUTE LIMIT (3) 100 - 120 PSI
NORMAL (2) 26 - 100 PSI
IDLE (1) 22 - 26 PSI
TRANSMISSION OIL TEMPERATURE Limits
TRANSMISSION Temp
PRECAUTIONARY (2) 105 - 140 C
CONTINUOUS (1) -20 - 105 C
TRANSMISSION OIL PRESSURE Limits
TRANSMISSION Pressure
PRECAUTIONARY (3) 65-130 PSI
CONTINUOUS (2) 30-65 PSI
IDLE AND TRANSIENT (1) 20-30 PSI
FUEL Indication markings
NORMAL (1) > 200 (EACH TANK)
PRECAUTIONARY (2) 0 - 200 (EACH TANK)
Engine NP Limitations
NOTE:
Avoid operations in __ - __% and __% - __% NP range except during start and shutdown.
20% - 40% and 60% - 90% NP
Engine Starter Limits (below 15°C)
At ambient temperatures of __°C and below, __ consecutive start cycles may be made, followed by a __ minute rest period, followed by two additional consecutive start cycles. A __ minute rest period is then required before any additional starts.
At ambient temperatures of 15°C (59°F) and below, two consecutive start cycles may be made, followed by a 3 minute rest period, followed by two additional consecutive start cycles. A 30 minute rest period is then required before any additional starts.
Engine Starter Limits above 15° C:
At ambient temperatures above ___ up to ___, ___ consecutive start cycles may be made. A ___ minute rest period is then required before any additional start cycles.
At ambient temperatures above 15° up to 52°C (59° up to 126°F), two consecutive start cycles may be made. A 30 minute rest period is then required before any additional start cycles.
Fuel boost pumps shall be on when operating with JP-4 or equivalent (as specificed in Operator’s Manual):
(1) At _______ feet pressure altitude and above.
(2) When operating in _____ with JP-4 at ____ altitude.
Fuel boost pumps shall be on when operating with JP-4 or
equivalent (as specified in Operator’s Manual):
(1) At 5000 feet pressure altitude and above.
(2) When operating in crossfeed with JP-4 at any altitude.
PNEUMATIC SOURCE INLET LIMITS:
The minimum ground-air source (pneumatic) required
to start the helicopter engines is __ psig and __ ppm at
___°C. The maximum ground-air source to be applied
to the helicopter is __ psig at _____ °C,
measured at the external air connector on the fuselage.
The minimum ground-air source (pneumatic) required
to start the helicopter engines is 40 psig and 30 ppm at
149°C (300°F). The maximum ground-air source to be applied
to the helicopter is 50 psig at 249°C (480°F),
measured at the external air connector on the fuselage.
ENGINE START LIMITS
CAUTION
Engine start attempts at or above a pressure
altitude of ___\_ feet could result in
a ____ _____.
Engine start attempts at or above a pressure
altitude of 18,000 feet could result in
a hot start.
CAUTION
Due to fuel volatility, when converting
from JP-4 to JP-5/JP-8, ____ helicopter
refueling operations must be completed
before performing operations with fuel
boost pumps off.
Due to fuel volatility, when converting
from JP-4 to JP-5/JP-8, three helicopter
refueling operations must be completed
before performing operations with fuel
boost pumps off.
When a helicopter operating with JP-4 is restarted
within ___ hours of engine shutdown and the air temperature
is above ___ , a minimum of ___ minutes of dual
engine ground operation at 100% NR is required prior to
takeoff to purge possible hot fuel from engine nacelle area.
When a helicopter operating with JP-4 is restarted
within 2 hours of engine shutdown and the air temperature
is above 21°C (70°F), a minimum of 2 minutes of dual
engine ground operation at 100% NR is required prior to
takeoff to purge possible hot fuel from engine nacelle area.
HELICOPTER MAXIMUM WEIGHT
UH-60M _____lbs
UH-60M external lift mission _____lbs
ESSS/ERFS helicopter onferry mission _______lbs
(Airworthinessrelease required)
HELICOPTER MAXIMUM WEIGHT
UH-60M 22,000 lbs
UH-60M external lift mission 23,500 lbs
ESSS/ERFS helicopter onferry mission 23,500 lbs
(Airworthinessrelease required)
External lift missions above _____ pounds can only be flown with cargo hook loads above _____ pounds and up to _____ pounds.
External lift missions above 22,000 pounds can only be flown with cargo hook loads above 8,000 pounds and up to 9,000 pounds.
Maximum weight is further limited by cargo floor
maximum capacity of ____ pounds per square foot.
Maximum weight is further limited by cargo floor
maximum capacity of 300 pounds per square foot.
Maximum capacity for each storage compartment is _____ pounds.
Maximum capacity for each storage compartment is 125 pounds.
The four cabin ceiling tiedown fittings have a limited load capability of ______ pounds.
The four cabin ceiling tiedown fittings have a limited load capability of 4,000 pounds.
The ____ (number) tiedown fittings installed on the cargo floor can restrain a ____ pound load in any direction.
The 17 tiedown fittings installed on the cargo floor can restrain a 5,000 pound load in any direction.
The ____ (number) net restraint rings in the cargo compartment are rated at _____ pound capacity in any direction.
The eight net restraint rings in the cargo compartment are rated at 3,500 pound capacity in any direction.
The maximum weight that may be suspended from the cargo hook is _____ pounds.
The maximum weight that may be suspended from the cargo hook is 9,000 pounds.
Maximum airspeed with external cargo hook loads up to _____ pounds is ____ KIAS and greater than _____ pounds and a corresponding gross weight greater than ____ pounds will vary due to the external load physical configuration, but shall not exceed ____ KIAS.
Maximum airspeed with external cargo hook loads up to 8,000 pounds is 140 KIAS and greater than 8,000 pounds and a corresponding gross weight greater than 22,000 pounds will vary due to the external load physical configuration, but shall not exceed 120 KIAS.
Maximum airspeed for one engine inoperative is ___\_ KIAS.
Maximum airspeed for one engine inoperative is 130 KIAS.
Maximum airspeed for autorotation at a gross weight of ____ pounds or less is ___ KIAS.
Maximum airspeed for autorotation at a gross weight of 16,825 pounds or less is 150 KIAS.
Maximum airspeed for autorotation at a gross weight of ____ pounds or more is ____ KIAS.
Maximum airspeed for autorotation at a gross weight of 16,825 pounds or more is 130 KIAS.
Sideward/rearward flight limits. Hovering in winds greater than ____ knots (___ knots with ESSS) from the sides or rear is prohibited.
Sideward/rearward flight limits. Hovering in winds
greater than 45 knots (35 knots with ESSS) from the sides
or rear is prohibited.
Sideward/Rearward flight into the
wind, when combined with windspeed, shall not exceed ___
knots (___ knots with ESSS).
Sideward/Rearward flight into the
wind, when combined with windspeed, shall not exceed 45
knots (35 knots with ESSS).
SAS inoperative airspeed limits:
(1) One SAS inoperative - ____ KIAS.
(2) Two SAS inoperative - ____ KIAS.
(3) Two SAS inoperative in IMC - ___ KIAS.
SAS inoperative airspeed limits:
(1) One SAS inoperative - 170 KIAS.
(2) Two SAS inoperative - 150 KIAS.
(3) Two SAS inoperative in IMC - 140 KIAS.
Hydraulic system inoperative limits:
(1) One hydraulic system inoperative - ____ KIAS.
(2) Two hydraulic systems inoperative - ____ KIAS.
(3) Two hydraulic systems inoperative in IMC - ____ KIAS.
Hydraulic system inoperative limits:
(1) One hydraulic system inoperative - 170 KIAS.
(2) Two hydraulic systems inoperative - 150 KIAS.
(3) Two hydraulic systems inoperative in IMC - 140 KIAS.
If use is required, the landing light must be extended prior to reaching a maximum forward airspeed of ____ KIAS. With landing light extended, airspeed
is limited to ___KIAS.
If use is required, the landing light must be extended prior to reaching a maximum forward airspeed of 130 KIAS. With landing light extended, airspeed
is limited to 180 KIAS.
If use is required, the searchlight must be extended prior to reaching a maximum forward
airspeed of ____ KIAS. With searchlight extended, airspeed is limited to ____ KIAS.
If use is required, the searchlight must be extended prior to reaching a maximum forward
airspeed of 100 KIAS. With searchlight extended, airspeed is limited to 180 KIAS.
The maximum airspeed for autorotation shall be limited to ____ KIAS with
Volcano installed.
The maximum airspeed for autorotation shall be limited to 100 KIAS with
Volcano installed.
Maximum airspeed with skis installed is ____ KIAS
Maximum airspeed with skis installed is 155 KIAS
Cabin door(s) may be fully open up to ____ KIAS
Cabin door(s) may be fully open up to 145 KIAS
Gunner window(s) may be fully open up to ____ KIAS.
Gunner window(s) may be fully open up to 170 KIAS.
Flight with cockpit door(s) removed is _______.
Flight with cockpit door(s) removed is prohibited.
Flight with cabin door(s) open is ____ _______ with Volcano installed.
Flight with cabin door(s) open is not authorized with Volcano installed
Manual control available. If the automatic stabilator control system fails in flight and operation cannot be restored:
(1) The stabilator shall be set full down at speeds below ____ KIAS.
(2) The stabilator shall be set at 0° at speeds above ____ KIAS.
(3) Autorotation airspeed shall be limited to ____ KIAS at all gross weights.
Manual control available. If the automatic stabilator control system fails in flight and operation cannot be restored:
(1) The stabilator shall be set full down at speeds below 40 KIAS.
(2) The stabilator shall be set at 0° at speeds above 40 KIAS.
(3) Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
Hovering turns greater than ____ ° per second are prohibited. Intentional maneuvers beyond attitudes ___° pitch or over ___° roll are prohibited.
Hovering turns greater than 30° per second are prohibited. Intentional maneuvers beyond attitudes of +/- 30° pitch or over 60° roll are prohibited.
Rearward ground taxi is ________ .
Rearward ground taxi is prohibited.
Manual operation of the stabilator in flight is _____ except as required by formal training and maintenance test flight requirements or as alternate stabilator control in case the _______ mode malfunctions.
Manual operation of the stabilator in flight is prohibited except as required by formal training and maintenance test flight requirements or as alternate stabilator control in case the AUTO mode malfunctions.
Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of _________in the helicopter and heat damage to _____ on open cargo doors.
Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of exhaust fumes in the helicopter and heat damage to windows on open cargo doors.
Above _____ KIAS avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.
Above 80 KIAS avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.
If the automatic stabilator control system fails in flight and operation cannot be
restored:
(1) The stabilator shall be set full down at speeds below ___ KIAS
(2) The stabilator shall be set at 0° at speeds above ___ KIAS.
(3) Autorotation airspeed shall be limited to ___ KIAS at all gross weights.
If the automatic stabilator control system fails in flight and operation cannot be
restored:
(1) The stabilator shall be set full down at speeds below 40 KIAS
(2) The stabilator shall be set at 0° at speeds above 40 KIAS.
(3) Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
Maneuvering limitations with a sling load are limited to a maximum of ___° angle of bank in forward flight.
Maneuvering limitations with a sling load are limited to a maximum of 30° angle of bank in forward flight.
Rearward flight with sling load is limited to ___ knots.
Rearward flight with sling load is limited to 35 knots.
Bank angles shall be limited to ____° when a PRI SERVO FAIL caution appears.
Bank angles shall be limited to 30° when a PRI SERVO FAIL caution appears.
Do not exceed a touchdown sink rate of ____ feet-per minute on level terrain and ____ feet-per-minute on slopes with gross weights of up to 16,825 pounds;
Above 16,825 pounds gross weight do not exceed ____ feet-per-minute on
level terrain and ____ feet-per-minute on slopes.
Do not exceed a touchdown sink rate of 540 feet-per minute on level terrain and 360 feet-per-minute on slopes with gross weights of up to 16,825 pounds.
Above 16,825 pounds gross weight do not exceed 300 feet-per-minute on
level terrain and 180 feet-per-minute on slopes.
Maximum forward touchdown speed is limited to ____ knots ground speed on level terrain.
Maximum forward touchdown speed is limited to 60 knots ground speed on level terrain.
NOTE
Because of the flat profile of the main
transmission and forward location of both
transmission oil pumps, transmission oil
pressure will drop during nose-up slope
operations. At slope angle of ___°, an
indicated oil pressure of ___ to ___ psi is
normal; and at a ___° slope angle, a pressure
in the range of ___ to ___ psi is normal due to
pitching of the helicopter.
NOTE
Because of the flat profile of the main
transmission and forward location of both
transmission oil pumps, transmission oil
pressure will drop during nose-up slope
operations. At slope angle of 10°, an
indicated oil pressure of 30 to 35 psi is
normal; and at a 15° slope angle, a pressure
in the range of 10 to 15 psi is normal due to
pitching of the helicopter.
____° nose-up, right wheel up or left wheel upslope.
The slope limitations shall be further reduced by ___° for
every ___ knots of wind
15° nose-up, right wheel up or left wheel upslope.
The slope limitations shall be further reduced by 2° for
every 5 knots of wind
___° nose downslope. Landing in downslope conditions
with tail winds greater than ___ knots shall not be
conducted.
6° nose downslope. Landing in downslope conditions
with tail winds greater than 15 knots shall not be
conducted.
The main gearbox may be operated up to ___ minutes
at a time with pressure fluctuations when the helicopter is
known to be at a nose-up attitude
The main gearbox may be operated up to 30 minutes
at a time with pressure fluctuations when the helicopter is
known to be at a nose-up attitude
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace or light icing conditions. Flight into light icing is not recommendedwithout the blade deice. Flight into moderate icingshall comply with paragraph 5.30 c.
(1) ______ _____.
(2) ______ ____.
(3) ______ ____.
(4) ______ ___ ___ _____ _____ ____.
(5) ______ _____ _____ ____ ____.
Helicopters with the following equipment installed,
operational, and turned on are permitted to fly into trace or
light icing conditions. Flight into light icing is not recommended
without the blade deice. Flight into moderate icing
shall comply with paragraph 5.30 c.
(1) Windshield Anti-ice.
(2) Pitot Heat.
(3) Engine Anti-ice.
(4) Engine Inlet Anti-ice Modulating Valve.
(5) Insulated Ambient Air Sensing Tube.
For flight into moderate icing conditions, all equipment
in paragraph ______ and blade deice must be installed,
operational, and turned on.
For flight into moderate icing conditions, all equipment
in paragraph 5.30 b. and blade deice must be installed,
operational, and turned on.
Flight into heavy or severe icing is ______.
Flight into heavy or severe icing is prohibited.
Helicopters equipped with blade erosion kit tape are ______ from flight into icing conditions
Helicopters equipped with blade erosion kit tape are
prohibited from flight into icing conditions
During prolonged ground operation of the backup pump with the rotor system static, the backup pump is limited to the following temperature/time/cooldown limits because of hydraulic fluid overheating.
FAT °C (°F) Operating Time (Minutes) Cooldown Time( Pump Off)(Minutes)
-54° - 32° ___ ___
(-65° - 90°)
33° - 38° ___ ___
(91° - 100°)
24 72
39° - 52° ___ ___
(102° - 126°)
During prolonged ground operation of the backup pump with the rotor system static, the backup pump is limited to the following temperature/time/cooldown limits because of hydraulic fluid overheating.
FAT °C Operating Time (Min) Cooldown Time( Pump Off)(Min)
-54° - 32° Unlimted- -
33° - 38° 2472
39° - 52° 1648
To prevent APU overheating, APU operation at ambient temperature of ___°C and above with engine and rotor operating, is limited to ___ minutes. With engine and rotor not operating, the APU may be operated continuously up to an ambient temperature of ___°C.
If APU OIL HOT caution appears a ___ minute cooling period is required, before checking oil level.
To prevent APU overheating, APU operation at ambient temperature of 43°C (109°F) and above with engine and rotor operating, is limited to 30 minutes. With engine and rotor not operating, the APU may be operated continu ously up to an ambient temperature of 51°C (124°F).
If APU OIL HOT caution appears a 30 minute cooling period is required, before checking oil level.
Windshield anti-ice check shall not be done when FAT is over ___°C.
Windshield anti-ice check shall not be done when FAT is over 27°C (80°F).
Intentional flight into severe turbulence is _________.
Intentional flight into thunderstorms is ________.
Intentional flight into turbulence with a sling load attached and an inoperative collective trim is _______.
Intentional flight into severe turbulence is prohibited.
Intentional flight into thunderstorms is prohibited.
Intentional flight into turbulence with a sling load attached and an inoperative collective trim is prohibited.
With both UES and EIBF installed, do not hover in
winds coming from the right side ___ degrees off the nose
for more than ____ minutes.
With both UES and EIBF installed, do not hover in
winds coming from the right side 90 degrees off the nose
for more than 5 minutes.
