Dash 10 - Limits CH0 Flashcards
MINIMUM CREW REQUIREMENTS
The minimum crew required to fly the helicopter is two pilots. Additional crewmembers, as required, will be added at the discretion of the commander, in accordance with pertinent Department of the Army regulations
ENGINE INSTRUMENT CREW ALERTING SYSTEM (EICAS) AND PFD POWER POD COLOR CODES:
Red and yellow striped tapes and red readouts indicate:
limit above or below which continued operation is likely to cause damage or shorten component life.
ENGINE INSTRUMENT CREW ALERTING SYSTEM (EICAS) AND PFD POWER POD COLOR CODES:
Yellow tapes and readouts indicate:
The range when special attention should be given to the parameter the instrument represents
ENGINE INSTRUMENT CREW ALERTING SYSTEM (EICAS) AND PFD POWER POD COLOR CODES:
Green tapes and readouts indicate:
The normal operating range of the parameter the instrument represents.
Rotor/Power Displays Nr/Np tapes:
Red lower limit line:
Yellow minimum contionous:
Yellow max continous:
Red upper limit line: (___ Nr and ___ Np)
Green reference line:
Red lower limit line: 91%
Yellow minimum contionous: 95%
Yellow max continous: 101%
Red upper limit line: (110% Nr and 105% Np)
Green reference line: 100%
Rotor/Power Displays Nr/Np:
Note:
Avoid operations in _____% - _____% and _____% - _____%NP range except during start and shutdown.
Note:
Avoid operations in 20% - 40% and 60% - 90% NP range except during start and shutdown.
Gas Generator Speed Display:
NG tape range:
The NG tape Yellow maximum continous marking:
Red upper limit line marking:
- NG tape range: 0% to 110% on the EICAS display.
Yellow max continous marking: 104.6%
Red upper limit line marking: 106%
Torque Display:
- The Q tape range:
- Q tape yellow max continous limit line:
- Red upper danger limit line:
- Continuous torque limit indication above 80 KIAS:
- Q tape range: 0% to 150% on the EICAS display and PFD power pod.
- Q tape yellow max continous limit line: 100% or 120% based on airspeed or 135% if single engine
- Red upper danger limit line: 144%
- Continuous torque limit indication above 80 KIAS: Changes from 120% to 100%
Turbine Gas Temperature Displays:
- TGT tape range:
TGT 4 limit lines:
- Yellow maximum continuous
- 30 minute limit (yellow limit line):
- 10 minute limit (red limit line):
- 2.5 minute limit (red upper limit line):
- TGT tape range: 0C to 1000C
TGT 4 limit lines:
- Yellow maximum continuous: 793C
- 30 minute limit (yellow limit line): 846C
- 10 minute limit (red limit line): 879C
- 2.5 minute limit (red upper limit line): 903C
Engine Oil Displays:
Temperature
- Temperature (T ) Range:
- yellow maximum continuous limit:
- red upper danger limit line:
- Temperature (T ) Range: -20c to 180
- yellow maximum continuous limit: 135C
- red upper danger limit line: 150C
Engine Oil Displays:
Pressure
- Pressure (P ) tapes range:
- Yellow maximum continuous limit:
- Red upper danger limit:
- Red lower danger limit:
- Yellow minimum continuous limit:
- Pressure (P ) tape range: 0 to 170 psi
- Yellow maximum continuous limit: 100 psi
- Red upper danger limit: 120 psi
- Red lower danger limit: 22 psi
- Yellow minimum continuous limit: 26 psi
Transmission Oil Displays:
Temperature
- Temperature (T ) Range:
- yellow maximum continuous limit:
- red upper danger limit line:
- Temperature (T ) Range: -20C to 150C
- yellow maximum continuous limit: 105C
- red upper danger limit line: 140C
Transmission Oil Displays:
Pressure
- Pressure (P ) tapes range:
- Yellow maximum continuous limit:
- Red upper danger limit:
- Red lower danger limit:
- Yellow minimum continuous limit:
- Pressure (P ) tapes range: 0 to 150 psi
- Yellow maximum continuous limit: 65 psi
- Red upper danger limit: 130 psi
- Red lower danger limit: 20 psi
- Yellow minimum continuous limit: 30 psi
Fuel Display:
- MAIN FUEL and FUEL tape range:
- Digital readouts range:
- MAIN FUEL tapes low fuel caution line:
If a main tank level falls below the low fuel caution level, the tape and readout turn _____.
On the power pod FUEL display, the pointers turn _____ if a main tank level falls below the low fuel caution level (_____ lbs)
- MAIN FUEL and FUEL tape range: 0 to 1200 lbs on the EICAS display and PFD power pod.
- Digital readouts range: 0 to 1500 lbs on the EICAS display and are a total of both main fuel tanks on the power pod FUEL display
- MAIN FUEL tapes low fuel caution line: 200 lbs
If a main tank level falls below the low fuel caution level, the tape and readout turn Yellow.
On the power pod FUEL display, the pointers turn Yellow if a main tank level falls below the low fuel caution level (200 lbs)
ROTOR LIMITATIONS
- NP1 and NP2 speed split during autorotational descent when the engines are fully decoupled from the main rotor is _____ (normal/abnormal)
- Rotor Start and Stop Limits:
- Rotor Speed Limitations:
- Normal
- Start and stop: 45 knots from any direction.
- Power off (autorotation) rotor speeds up to 120% NR are authorized for use by maintenance test flight pilots during autorotational RPM checks.
ROTOR BRAKE/GUST LOCK LIMITATIONS.
- Operating an engine against the gust lock is _____ (prohibited/not prohibited)?
- Prohibited
ROTOR BRAKE/GUST LOCK LIMITATIONS:
- Rotor brake shall not be applied with engine(s) operating and rotor turning except during an _____. Maximum rotor speed for emergency rotor brake applications is _____ NR .
- Emergency stop
- 76% NR
ROTOR BRAKE/GUST LOCK LIMITATIONS.
- Routine stops will be with engine(s) off, NR below _____ and with _____ to _____ psi applied to stop the rotor in not less than _____ seconds.
- Routine stops will be with engine(s) off, NR below 40% and with 150-180 psi applied to stop the rotor in not less than 12 seconds.
ROTOR BRAKE/GUST LOCK LIMITATIONS.
- Minimum rotor brake pressure for engine start:
- Maximum rotor brake pressure for engine start:
- Minimum rotor brake pressure for engine start: 450 psi.
- Maximum rotor brake pressure for engine start: 690 psi.
ROTOR BRAKE/GUST LOCK LIMITATIONS.
- Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at _____ only.
- Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at IDLE only.
ROTOR BRAKE/GUST LOCK LIMITATIONS.
- Single and dual engine starts and operation at IDLE with rotor brake on _____ (are/are not) time limited.
- Are not
GUST LOCK LIMITATIONS WITHOUT ROTOR BRAKE.
On helicopters without a rotor brake installed and using UH-60L gust lock linkage, the following limitations apply:
- Dual-engine operation with gust lock engaged is _____ (prohibited/not prohibited).
- Single-engine operation with gust lock engaged will
be performed by _____ pilot(s) at _____ only.
- Gust lock shall not be disengaged with engine _____ (running/not running).
- Dual-engine operation with gust lock engaged is prohibited
- Single-engine operation with gust lock engaged will
be performed by authorized pilot(s) at IDLE only.
- Gust lock shall not be disengaged with engine Running
MAIN TRANSMISSION MODULE LIMITATIONS.
- Momentary fluctuations in oil pressure may occur during _____ and _____:
- 3 criteria for the oil pressure when a entry in the approproate maintenance form shall be made:
- Momentary fluctuations in oil pressure may occur during transient maneuvers and pitch attitudes above +6*
- 3 criteria:
- If oil pressure is not steady during steady state forward flight or in a level hover
- If oil pressure is steady but under 45 psi
- Sudden pressure drop (more than 10 psi) without fluctuation
MAIN TRANSMISSION MODULE LIMITATIONS.
A demand for maximum power from engines with different engine torque factors (ETF) will cause a torque split when the low ETF engine reaches TGT limiting. This torque split is _____ (normal/abnormal). Under these circumstances, the high power engine _____ (may/may not) exceed the dual engine limit.
A demand for maximum power from engines with different engine torque factors (ETF) will cause a torque split when the low ETF engine reaches TGT limiting. This torque split is normal. Under these circumstances, the high power engine May ) exceed the dual engine limit.
(Example: #1 Q = 96% at TGT limiting, #2 Q is allowed to go up to 104%. Total helicopter torque = (96%+104%)/2 = 100%).
NP1/NP2 Limitations:
12 - SECOND TRANSIENT:
TRANSIENT:
CONTINUOUS:
TRANSIENT:
12 - SECOND TRANSIENT: 105 - 107%
TRANSIENT: 101 - 105%
CONTINUOUS: 95 - 101%
TRANSIENT: 91 - 95%
NR power ON limitations:
TRANSIENT:
CONTINUOUS:
TRANSIENT:
TRANSIENT: 101 - 107%
CONTINUOUS: 95 - 101%
TRANSIENT: 91 - 95%
NR power OFF limitations (autorotation):
MAXIMUM:
TRANSIENT:
NORMAL:
UPPER RED RANGE BEGINS AT 110% TO CORRESPOND WITH THE POWER OFF LIMIT
MAXIMUM: 110%
TRANSIENT: 105 - 110%
NORMAL: 90 - 105%
GAS GENERATOR SPEED (NG) Limitations:
12 SECOND TRANSIENT:
CONTINUOUS:
12 SECOND TRANSIENT: 105 - 106%
CONTINUOUS: 0 - 105%
TORQUE (Q) Limitations:
10 SECOND TRANSIENT
- Dual engine above 80KIAS:
- Dual engine at 80KIAS or below:
- Single engine:
CONTINUOUS
- Dual engine above 80KIAS:
- Dual engine at 80KIAS or below:
- Single engine:
10 SECOND TRANSIENT
- Dual engine above 80KIAS: 100 - 144%
- Dual engine at 80KIAS or below: 120 - 144%
- Single engine: 135 - 144%
CONTINUOUS
- Dual engine above 80KIAS: 0 - 100%
- Dual engine at 80KIAS or below: 0 - 120%
- Single engine: 0 - 135%
TURBINE GAS TEMPERATURE (TGT) Limitations:
12 SECOND TRANSIENT:
2.5 MINUTE TRANSIENT (CONTINGENCY POWER):
START ABORT LIMIT:
10 MINUTE LIMIT:
30 MINUTE LIMIT:
NORMAL:
12 SECOND TRANSIENT: 903 - 949C
2.5 MINUTE TRANSIENT (CONTINGENCY POWER): 879 - 903C
START ABORT LIMIT: 851C
10 MINUTE LIMIT: 846 - 879C
30 MINUTE LIMIT: 793 - 846C
NORMAL: 0 - 793C
ENGINE T limits:
30 MINUTE LIMIT:
CONTINUOUS:
30 MINUTE LIMIT: 135 - 150C
CONTINUOUS: -20 - 135C
ENGINE P limits:
5 MINUTE LIMIT:
NORMAL:
IDLE:
5 MINUTE LIMIT: 100 - 120 PSI
NORMAL: 26 - 100 PSI
IDLE: 22 - 26 PSI
Transmission T limits:
PRECAUTIONARY:
CONTINUOUS:
PRECAUTIONARY: 105 - 140C
CONTINUOUS: -20 - 105C
Transmission P limits:
PRECAUTIONARY:
CONTINUOUS:
IDLE AND TRANSIENT:
PRECAUTIONARY: 65-130 PSI
CONTINUOUS: 30-65 PSI
IDLE AND TRANSIENT: 20-30 PSI
Fuel limitations:
NORMAL:
PRECAUTIONARY:
NORMAL: > 200 (EACH TANK)
PRECAUTIONARY: 0 - 200 (EACH TANK)
Engine Starting cycle
- Definition
- Delay between attempts
A starting cycle is the interval from start initiation and acceleration of the compressor, from zero rpm, to starter dropout.
The 60 second delay between start attempts applies when the first attempt is aborted for any reason, and it applies regardless of the duration of the first attempt.
Engine Starter cycle at ambient T below 15C (59F)
- Consecutive start cycles:
- Rest period:
- consecutive start cycles (after rest period):
- Aditional rest period before additional cycles:
- Consecutive start cycles: 2 cycles
- Rest period: 3 min
- consecutive start cycles (after rest period): 2 cycles
- Aditional rest period before additional cycles: 30 min
Engine Starter cycle at ambient T above 15C (59F) and up to 52C (126F)
- Consecutive start cycles:
- Rest period before any aditional cycles:
- Consecutive start cycles: 2 cycles
- Rest period before any aditional cycles: 30 min
PNEUMATIC SOURCE INLET LIMITS:
- The minimum ground-air source (pneumatic) required to start the helicopter engines:
- The maximum ground-air source to be applied to the helicopter:
- Measured where?
- Minimum: 40 psig and 30 ppm at 149C (300F).
- Maximum: 50 psig at 249C (480F)
- 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 hot start.
18.000 ft
ENGINE START LIMITS
Crossbleed starts shall not be attempted unless the _____ or _____ advisory does not appear, and operating engine must be at _____ NG or above and rotor speed at _____ NR .
Crossbleed starts shall not be attempted unless the ENG 1 ANTI-ICE ON or ENG 2 ANTI-ICE ON advisory does not appear, and operating engine must be at 90% NG or above and rotor speed at 100% NR.
ENGINE START LIMITS
- Start procedure at 14,000 PA or higher:
Press the start switch with the ENG POWER CONT lever OFF , until the maximum motoring speed (about 24%) is reached, before going to IDLE
ENGINE START LIMITS
Engine starts using APU source may be attempted when within the range of FAT and pressure altitude of Figure _____ ?
Figure 5-2. (Engine start envelope)
ENGINE OVERSPEED CHECK LIMITATIONS.
Engine overspeed check in flight is _____. Engine overspeed checks, on the ground, are authorized by _____ only.
Engine overspeed check in flight is prohibited. Engine overspeed checks, on the ground, are authorized by designated maintenance personnel only.
FUEL LIMITATIONS
Fuel boost pumps shall be _____ (on/off) except as required by emergency procedures and the following limitations. Fuel boost pumps shall be _____ (on/off) when operating with JP-4 or equivalent (as specified in Operator’s Manual):
- -
- -
Fuel boost pumps shall be OFF except as required by emergency procedures and the following limitations. Fuel boost pumps shall be ON when operating with JP-4 or equivalent (as specified in Operator’s Manual):
- At 5000 feet pressure altitude and above
- When operating in crossfeed with JP-4 at any altitude.
FUEL LIMITATIONS
Caution:
Due to fuel volatility, when converting from JP-_____ to JP-_____/JP-_____, _____ (how many) 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
FUEL LIMITATIONS
When a helicopter operating with JP-4 is restarted within 2 hours of engine shutdown and the air temperature is above 21C (70F), a minimum of _____ minutes of dual engine ground operation at _____ 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 21C (70F), 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.
WEIGHT LIMITATIONS
- UH-60M Max weight:
- UH-60M external lift mission:
- ESSS/ERFS helicopter on ferry mission (Airworthiness release required):
- UH-60M Max weight: 22,000 lbs
- UH-60M external lift mission: 23,500 lbs
- ESSS/ERFS helicopter on ferry mission (Airworthiness release required): 24,500 lbs
WEIGHT LIMITATIONS
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.
WEIGHT LIMITATIONS
Maximum weight is further limited by cargo floor maximum capacity of _____ pounds per square foot. Refer to Chapter 6.
Maximum weight is further limited by cargo floor maximum capacity of 300 pounds per square foot. Refer to Chapter 6.
STOWAGE PROVISIONS
Maximum capacity for each storage compartment is
_____ pounds.
125 pounds
CABIN CEILING TIEDOWN FITTINGS
- The four cabin ceiling tiedown fittings have a limited load capability of _____ pounds.
- The 17 tiedown fittings (Figure 6-13) installed on the cargo floor can restrain a _____ pound load in any direction.
- The eight net restraint rings in the cargo compartment are rated at _____ pound capacity in any direction.
The four cabin ceiling tiedown fittings have a limited load capability of 4,000 pounds.
The 17 tiedown fittings (Figure 6-13) installed on the cargo floor can restrain a 5,000 pound load in any direction.
The eight net restraint rings in the cargo compartment are rated at 3,500 pound capacity in any direction.
CARGO HOOK WEIGHT LIMITATION
The maximum weight that may be suspended from the cargo hook is _____ pounds. The external load limit of the airframe will not be exceeded when using cargo hook
The maximum weight that may be suspended from the cargo hook is 9,000 pounds. The external load limit of the airframe will not be exceeded when using cargo hook
AIRSPEED OPERATING LIMITS
Maximum airspeed with external cargo hook loads up to 8,000 pounds is _____.
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 _____.
Maximum airspeed with external cargo hook loads up to 8,000 pounds is 140 KIAS.
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.
AIRSPEED OPERATING LIMITS
- Vne for OEI:
- Vne for Autorotation at or below 16,825 pounds:
- Vne for Autorotation above 16,825 pounds:
- Vne for OEI: 130 KIAS
- Vne for Autorotation at or below 16,825 pounds: 150 KIAS
- Vne for Autorotation above 16,825 pounds: 130 KIAS
AIRSPEED OPERATING LIMITS
Sideward/rearward flight limits. Hovering in winds greater than _____ knots (_____ 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 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 45 knots (35 knots with ESSS).
AIRSPEED OPERATING LIMITS
- One SAS inoperative:
- Two SAS inoperative:
- Two SAS inoperative in IMC:
- One SAS inoperative: 170 KIAS
- Two SAS inoperative: 150 KIAS
- Two SAS inoperative in IMC: 140 KIAS
AIRSPEED OPERATING LIMITS
- One hydraulic system inoperative:
- Two hydraulic system inoperative:
- Two hydraulic system inoperative in IMC:
- One hydraulic system inoperative: 170 KIAS
- Two hydraulic system inoperative: 150 KIAS
- Two hydraulic system inoperative in IMC: 140 KIAS
AIRSPEED OPERATING LIMITS
- Landing light. 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.
- Searchlight. 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.
- Landing light. 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.
- Searchlight. 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.
AIRSPEED OPERATING LIMITS
The maximum airspeed for autorotation shall be limited to _____ KIAS with Volcano installed.
100 KIAS
AIRSPEED OPERATING LIMITS
Maximum airspeed with skis installed is _____.
155 KIAS
FLIGHT WITH CABIN DOOR(S)/WINDOW(S) OPEN.
- Cabin door(s) may be fully open up to _____ KIAS.
- The cabin door(s) _____ (will/will not) be intentionally moved from the fully open or closed position in flight.
- The cabin door(s) _____ (may/may not) be opened or closed during hovering flight.
- The cabin door(s) must be closed or fully opened and latched before forward flight. Should the door(s) inadvertently open in flight, the door(s) _____ (may/may not) be secured fully open or closed.
- Cabin door(s) may be fully open up to 145 KIAS.
- The cabin door(s) will not be intentionally moved from the fully open or closed position in flight.
- The cabin door(s) may be opened or closed during hovering flight.
- The cabin door(s) must be closed or fully opened and latched before forward flight. Should the door(s) inadvertently open in flight, the door(s) may be secured fully open or closed.
FLIGHT WITH CABIN DOOR(S)/WINDOW(S) OPEN.
Gunner window(s) may be fully open up to _____ KIAS.
170 KIAS
FLIGHT WITH CABIN DOOR(S)/WINDOW(S) OPEN
- Flight with cockpit door(s) removed is _____ (prohibited/ not prohibited)
- Flight with cabin door(s) open is _____ (authorized /not authorized) with Volcano installed.
- Flight with cockpit door(s) removed is prohibited
- Flight with cabin door(s) open is not authorized with
Volcano installed.
AIRSPEED LIMITATIONS FOLLOWING FAILURE OF THE AUTOMATIC STABILATOR CONTROL SYSTEM.
Vne becomes variable to indicate the airspeed limit applicable for the current stabilator position, except in no case shall the autorotation limit exceed _____ KIAS.
120 KIAS
AIRSPEED LIMITATIONS FOLLOWING FAILURE OF THE AUTOMATIC STABILATOR CONTROL SYSTEM.
Manual control available. If the automatic stabilator control system fails in flight and operation cannot be restored:
- The stabilator shall be set full down at speeds below _____ KIAS.
- The stabilator shall be set at _____* at speeds above _____ KIAS.
- 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:
- The stabilator shall be set full down at speeds below 40 KIAS.
- The stabilator shall be set at 0* at speeds above 40 KIAS.
- Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
AIRSPEED LIMITATIONS FOLLOWING FAILURE OF THE AUTOMATIC STABILATOR CONTROL SYSTEM
Manual control not available. If the stabilator stops operating in the automatic mode, the Vne becomes _____ (variable/stationary) to indicate the airspeed limit by extending the red arc in a counter-clockwise direction to the applicable airspeed for the current stabilator position. Pointer and readout turn red with a black outline when the airspeed is at or above the Vne.
Manual control not available. If the stabilator stops operating in the automatic mode, the Vne becomes variable to indicate the airspeed limit by extending the red arc in a counter-clockwise direction to the applicable airspeed for the current stabilator position. Pointer and readout turn red with a black outline when the airspeed is at or above the Vne.
Prohibited maneuvers:
- Hovering turns greater than 30* per second
- Intentional maneuvers beyond attitudes of +/- 30* pitch or over 60* roll
- Simultaneous moving of both ENG POWER CONT levers to IDLE or OFF (throttle chop) in flight
- Rearward ground taxi
- Restricted maneuvers other than Manuvering limitations :
- Manual Operation of the Stabilator. (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 exhaust fumes in the helicopter and heat damage to windows on open cargo doors)
-
Maneuvering Limitations
The maneuvering limits of the helicopter other than as limited by paragraphs within this section (5.25.3) are always defined by _____:
Main rotor blade stall
Maneuvering Limitations
Maneuvering flight which results in _____ and significant increase in _____ vibration is prohibited
Maneuvering flight which results in severe blade stall and significant increase in 4-per-rev vibration is prohibited
High-Speed Yaw Maneuver Limitation:
- Above 80 KIAS:
Avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.
Limitations for Maneuvering With Sling Loads/rescue hoist:
Maneuvering limitations with a sling load/rescue hoist (Figure 5-7) are limited to a maximum of _____ angle of bank in forward flight. Side flight is limited by _____ and is decreased as airspeed increases. Rearward flight with sling load is limited to _____ knots.
Additional for rescue hoist: Rate of descent is limited to _____ feet-per-minute.
Maneuvering limitations with a sling load (Figure 5-7) are limited to a maximum of 30* angle of bank in forward flight. Side flight is limited by bank angle and is decreased as airspeed increases. Rearward flight with sling load is limited to 35 knots.
Additional for rescue hoist: Rate of descent is limited to 1,000 feet-per-minute.
Bank Angle Limitation
When a PRI SERVO FAIL caution appears:
Bank angles shall be limited to 30*
High Acceleration Takeoff, Hover and Dive Limitations:
Warning:
It has been demonstrated that if approaching ____ degrees nose _____ (up/down) attitude, during any _____, or when performing an aggressive _____, normal operation of stabilator position can lag Flight Control Computer (FCC) desired position and the FCC will command _____.
Warning:
It has been demonstrated that if approaching 30 degrees nose down attitude, during any high acceleration takeoff, or when performing an aggressive diving maneuver from a high hover, normal operation of stabilator position can lag Flight Control Computer (FCC) desired position and the FCC will command Auto Mode Failure.
LANDING GEAR LIMITATIONS.
touch down sink rate with;
Gross mass below 16,825 lbs in:
- Level terrain:
- Slope terrain:
Gross mass above 16,825 lbs:
- Level terrain:
- Slope terrain:
touch down sunk rate with;
Gross mass below 16,825 lbs in:
- Level terrain: 540 FPM
- Slope terrain: 360 FPM
Gross mass above 16,825 lbs:
- Level terrain: 300 FPM
- Slope terrain: 180 FPM
LANDING SPEED LIMITATIONS
Maximum forward touchdown speed on level terrain:
60 knots ground speed
SLOPE LANDING LIMITATIONS
- Nose-up, right wheel up or left wheel upslope:
- Downslope:
- Skis installed:
- Nose-up, right wheel up or left wheel upslope: 15*, the slope limitations shall be further reduced by 2* for every 5 knots of wind
- Downslope: 6*. Landing in downslope conditions with tail winds greater than 15 knots shall not be conducted. A low frequency oscillation may occur when landing nose down on a slope with the cyclic near the aft stop.
- With skis installed: Limited to 10* nose-up and right wheel or left wheel upslope.
Gearbox operating time with pressure fluctiations in known upslope condition:
30 minutes at a time
SLOPE LANDING LIMITATIONS
When attempting a nose upslope landing at gross weights in excess of _____ pounds with skis installed, the parking brake _____ (may/may not) hold the helicopter in position.
- What should the pilot then be prepared for?
When attempting a nose upslope landing at gross weights in excess of 16,000 pounds with skis installed, the parking brake may not hold the helicopter in position.
- What should the pilot be prepared for? The pilot should be prepared to use the toe brakes.
FLIGHT IN ICING CONDITIONS
- TRACE or LIGHT icing requirements:
- MODERATE icing requirements:
- HEAVY or SERVERE icing requirements:
TRACE or LIGHT icing
- Windshield Anti-ice.
- Pitot Heat.
- Engine Anti-ice.
- Engine Inlet Anti-ice Modulating Valve.
- Insulated Ambient Air Sensing Tube.
MODERATE icing
- All of the above
- And blade deice must be installed, operational, and turned on
HEAVY or SERVERE icing
- Prohibited
FLIGHT IN ICING CONDITIONS
- When equipped with blade erosion kit tape, flight into icing conditions are _____ (prohibited/not prohibited)
- When equipped with blades coated with Advanced Erosion Protection Coating (HONTEK) are _____ (prohibited/not prohibited)
- When equipped with blade erosion kit tape, flight into icing conditions are prohibited
- When equipped with blades coated with Advanced Erosion Protection Coating (HONTEK) are not prohibited
ENGINE AND ENGINE INLET ANTI-ICE LIMITATIONS
At engine power levels of _____% Q per engine and below, full anti-ice capability _____ (can/cannot) be provided, due to _____ limitations. Avoid operation under conditions of _____ such as _____, or ground bleed air HEATER operation below _____% NR , during icing conditions. The cabin heating system should be turned _____ (on/off) before initiating a high rate of descent.
At engine power levels of 10% Q per engine and below, full anti-ice capability cannot be provided, due to engine bleed limitations. Avoid operation under conditions of extreme low power requirements such as high rate of descent (1900 fpm or greater), or ground bleed air HEATER operation below 100% NR , during icing conditions. The cabin heating system should be turned off before initiating a high rate of descent.
BACKUP HYDRAULIC PUMP HOT WEATHER LIMITATIONS.
During prolonged ground operation of the backup pump using MIL-H-83282 or MIL-H-5606 with the rotor system static, the backup pump is limited to the following temperature/time/cooldown limits because of hydraulic fluid overheating:
APU OPERATING LIMITATIONS
To prevent APU overheating, APU operation at ambient temperature of _____*C (_____*F) 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 (_____*F). 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 continuously 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 LIMITATIONS
Windshield anti-ice check shall not be done when FAT is over _____*C (_____*F).
27*C (80*F)
TURBULENCE AND THUNDERSTORM OPERATION
3 prohibited flights regarding Thunderstorms and Turbulence:
- 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.
BLUE FORCE TRACKER TEMPERATURE LIMITS
Normal operating temperature range:
-15*F (-26*C) to +160*F (+71*C).
CRASHWORTHY EXTERNAL FUEL SYSTEM CONFIGURATIONS
Caution:
CEFS tanks fuel level should be kept approximately _____ inches below the forward edge of the filler port bottom lip to ensure _____.
Caution:
CEFS tanks fuel level should be kept approximately 3 inches below the forward edge of the filler port bottom lip to ensure sufficient expansion space.
CRASHWORTHY EXTERNAL FUEL SYSTEM CONFIGURATIONS
The CEFS shall only be utilized in what approved configurations?
- A 200 gallon CEFS tank installed on each inboard vertical stores pylon.
- A 200 gallon CEFS tank installed on each outboard vertical stores pylon.
- Four 200 gallon CEFS tanks installed, one on each inboard and each outboard vertical stores pylon.
JETTISON LIMITS
- The jettisoning of fuel tanks in other than _____ is prohibited.
- Jettisoning with Volcano installed, if necessary, shall be accomplished at airspeeds not to exceed _____ KIAS and rates of descent not to exceed _____ fpm.
- The jettisoning of fuel tanks in other than an emergency is prohibited.
- Jettisoning with Volcano installed, if necessary, shall be accomplished at airspeeds not to exceed 110 KIAS and rates of descent not to exceed 500 fpm.
USE OF SKIS
- Water buckets _____ (shall/shall not) be used when skis are installed
Shall not
Any time an operational limit is exceeded, in what form should an entry be made, and what should it contain?
- DA Form 2408-13-1
- State what limit or limits were exceeded, range, time beyond limits, and any additional data that would aid maintenance personnel in the maintenance action that may be required
Ice dection system is calibrated for _____ kts. When flying above _____ kts, the system will indicate _____ (higher/lower) LWC than actual.
- 100 kts
- 100 kts
- Higher
Vne
193 KIAS
