UH-60M - Ops Limits (Ch. 5) Flashcards
MAIN TRANSMISSION MODULE LIMITATIONS
If oil pressure is not steady during steady state forward flight or in a level hover, or if oil pressure is steady but under __ psi, make an entry on DA Form 2408-13-1. Sudden pressure drop (more than __ psi) without fluctuation requires an entry on DA Form 2408-13-1.
If oil pressure is not steady during steady state forward flight or in a level hover, or if oil pressure is steady but under 45 psi, make an entry on DA Form 2408-13-1. Sudden pressure drop (more than 10 psi) without fluctuation requires an entry on DA Form 2408-13-1.
GAS TURBIN TEMPERATURE
__ Sec. Transient ____________
__ Min. Transient (cont. pwr) ____
__ Min. Limit ______________
__ Min. Limit ______________
Normal ___________________
Start abort limit ______________
12 Sec Trans. 903 - 949°C
- 2.5 Min Trans. 879 - 903°C
- 10 Min. Limit 846 - 879°C
- 30 Min. Limit 793 - 846°C
- Normal 0 - 793°C
Start abort Limit 851°C
TRANSMSN OIL TEMPERATURE
Precautionary ____________
Continuous ____________
- Precautionary 105 − 140°C
- Continuous −20 − 105°C
TRANSMISSION OIL PRESSURE
Precautionary _____________
Continuouse ______________
Idle and Transient ___________
- Precautionary 65-130 PSI
- Continuouse 30-65 PSI
1. Idle and Transient 20-30 PSI
TORQUE % Q
___-Second Transient
Dual-Engine
Above __ KIAS __________
__ KIAS or Below ___________
Single-Engine ____________
Continuous
Single-Engine _____________
Dual-Engine
Above __ KIAS ____________
__ KIAS or Below ___________
TORQUE % Q
10 -Second Transient
Dual-Engine
Above 80 KIAS 100% − 144% (4)
80 KIAS or Below 120% − 144%
Single-Engine 135% − 144%
Continuous
Single-Engine 0% − 135% (3)
Dual-Engine
Above 80 KIAS 0% − 100% (1)
80 KIAS or Below 0% − 120% (2)
ENGINE OIL TEMPERATURE
__ Min Limit _____________
Continuous _____________
ENGINE OIL TEMPERATURE
30 Min Limit 135 - 150°C
Continuous -20 - 135°C
ENGINE OIL PRESSURE
__ Min Limit _______________
Normal Operation ______________ PSI
Idle ______________________ PSI
- 5 Min Limit 100 − 120 PSI
- Normal Operation 26 − 100 PSI
- Idle 22 − 26 PSI
ENGINE Ng
___ Sec. Transient __________
Continuous ______________
ENGINE Ng
- 12 Sec. Transient 105% − 106%
- Continuous 0 − 105%
ENGINE NP 1−2
__ Sec. Transient ____________
Transient _________________
Continuous _______________
Transient _________________
Avoid Operation in the _____ − _____ and _____ − _____ range except during start and shutdown
ENGINE NP 1−2
12 Sec. Transient 105% − 107%
- Transient 101% − 105%
- Continuous 95% − 101%
- Transient 91% − 95%
- *Avoid Operation in the 20% − 40% and**
- *60% − 90% range except during start and shutdown**
MAIN ROTOR % RPM
Power on
Transient _____________
Continuous ___________
Transient ____________
Power off (Autorotation)
Maximum ______________
Transient ____________
Normal _______________
- *Power on**
3. Transient 101% − 107%
2. Continuous 95% − 101%
1. Transient 91% − 95%
Power off (Autorotation)
Maximum 110%
Transient 105% − 110%
Normal 90% − 105%
FUEL QUANTITY
Normal ______________
Precautionary _____________
FUEL QUANTITY
- Normal > 200 (EACH TANK)
- Precautionary 0 − 200 (EACH TANK)
ENGINE START LIMITS
Cross bleed starts shall not be attempted unless the __________________________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. When attempting single-engine starts at pressure altitudes above 14,000 feet, 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 STARTER LIMITS
At ambient temperatures of _\_°C and below, __\_ consecutive start cycles may be made, followed by a _\_minute rest period, followed by __\_ additional start cycles. A __ minute rest period is then required before any additional start cycles.
At ambient temperatures above _\_° up to __°C, __\_ consecutive start cycles may be made. A __ minute rest period is then required before any additional start cycles.
At ambient temperatures of 15°C and below, two consecutive start cycles may be made, followed by a 3 minute rest period, followed by two additional start cycles. A 30 minute rest period is then required before any additional start cycles.
At ambient temperatures above 15° up to 52°C, two consecutive start cycles may be made. A 30 minute rest period is then required before any additional start cycles.
PNEUMATIC SOURCE INLET LIMITS.
The minimum air source required to start the helicopter engines is __ psig and __ ppm at ___°C.
The maximum is __ psig at ___°C.
The minimum air source required to start the helicopter engines is 40 psig and 30 ppm at 149°C.
The maximum is 50 psig at 249°C, measured at the external air connector on the fuselage.
AIRSPEED LIMITS
Maximum airspeed for one engine inoperative is __ KIAS.
Maximum airspeed for autorotation at a gross weight of 16,825 lbs or less is __ KIAS.
Maximum airspeed for autorotation at a gross more than 16,825 lbs is __ KIAS.
Sideward/rearward flight into the wind, when combined with wind speed, shall not exceed ___ KTS.
Maximum airspeed for one engine inoperative is 130 KIAS.
Maximum airspeed for autorotation at a gross weight of 16,825 lbs or less is 150 KIAS.
Maximum airspeed for autorotation at a gross more than 16,825 lbs is 130 KIAS.
Sideward/rearward flight into the wind, when combined with wind speed, shall not exceed 45 KTS (35 knots with external fuel tanks).
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.
LOADING LIMITS
Maximum capacity for each storage compartment is ____ pounds.
Maximum cargo hook capacity (UH-60M) _____ pounds.
Maximum weight is further limited by cargo floor maximum capacity of __\_ lbs per square foot.
Max weight UH60 with seven lugs wheels _____\_ pounds.
Maximum capacity for each storage compartment is 125 pounds.
Maximum cargo hook capacity (UH-60M) 9.000 pounds.
Maximum weight is further limited by cargo floor maximum capacity of 300 lbs per square foot.
Max weight UH60 with seven lugs wheels 20,500 pounds.
Fourteen-lug wheels shall be used at or above gross weights of 20,500 pounds.
UH-60M 22,000
UH-60M external lift mission 23,500
Ferry (Airworthiness release) 24.500
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 - max 120 KIAS
The four cabin ceiling tiedown fittings have a limited load capability of 4,000 pounds.
The maximum weight that may be suspended from the rescue hoist is 600 pounds.
SAS Inoperative Limits KIAS
One SAS _________
Two SAS _________
Two SAS & IMC _____
One SAS 170 KIAS
Two SAS 150 KIAS
Two SAS & IMC 140 KIAS
Hydraulic System Inoperative Limits
One hydraulic system _________
Two hydraulic systems _________
Two hydraulic systems & IMC ________
One hydraulic system 170 KIAS
Two hydraulic systems 150 KIAS
Two hydraulic systems & IMC 140 KIAS
Searchlight and Landing Light
Maximum airspeed for Extending KIAS
Landing Light __________
Searchlight __________
Maximum airspeed for Extended KIAS
Landing Light __________
Searchlight __________
Maximum airspeed for Extending KIAS
Landing Light 130
Searchlight 100
Maximum airspeed for Extended KIAS
Landing Light 180
Searchlight 180
Max autorotation A/S Volcano installed 100 KIAS
Max airspeed with skis installed 155 KIAS
Vne EIBF installed 184 KIAS, and
external tanks installed 162 KIAS
BACKUP HYDRAULIC PUMP HOT WEATHER LIMITATIONS with the rotor system ________
FAT Degree C Operating Time Cool down Time
__________ __________ __________
__________ __________ __________
__________ __________ __________
BACKUP HYDRAULIC PUMP HOT WEATHER LIMITATIONS with the rotor system static.
FAT _°_C Oprerating T. Cool down Time
-54°-32°C__Unlimited - - - -
33°-38°C__24__72
39°-52°C__16__48
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.
FLIGHT WITH CABIN DOOR(S)/WINDOW(S) OPEN
Cabin doors
Cabin doors may be fully open up to ___ KIAS with soundproofing installed aft of station 379.
Cabin doors may be fully open up to ___ KIAS with soundproofing removed aft of station 379 or with soundproofing secured properly.
Windows
Gunner’s window(s) may be fully open up to ___ KIAS
Cockpit doors sliding windows will not be _____ or _____ during flight except during _____.
Flight with cockpit door(s) removed is ________.
Cabin doors
Cabin doors may be fully open up to 100 KIAS with soundproofing installed aft of station 379.
Cabin doors may be fully open up to 145 KIAS with soundproofing removed aft of station 379 or with soundproofing secured properly.
Windows
Gunner’s window(s) may be fully open up to 170 KIAS
Cockpit doors sliding windows will not be opened or closed during flight except during hover.
Flight with cockpit door(s) removed is prohibited.
Flight with cabin door(s) open is not authorized with Volcano installed.
BAM window(s) shall not be transitioned open or closed above 120 KIAS.
AIRSPEED LIMITATIONS FOLLOWING FAILURE OF THE AUTOMATIC STABILATOR CNTR SYSTEM
Manual control is available:
Stabilator shall be full down at speeds below __ KIAS
Stabilator shall be set at zero degree for speeds above __ KIAS.
Autorotation airspeed shall be limited to __ KIAS at all gross weights.
Manual control not available:
Placard airspeed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed ___ KIAS.
Manual control is available:
Stabilator shall be full down at speeds below 40 KIAS
Stabilator shall be set at zero degree for speeds above 40 KIAS.
Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
Manual control not available:
Placard airspeed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed 120 KIAS.
PROHIBITED MANEUVERS
a. Hovering turns greater than __° per second are prohibited. Intentional maneuvers beyond attitudes of __° in pitch or over __° in roll are prohibited.
b. Simultaneous moving of ___________________ to ____ or ___ in flight is prohibited.
c. ________ ground taxi is prohibited.
a. Hovering turns greater than 30° per second are prohibited. Intentional maneuvers beyond attitudes of 30° in pitch or over 60° roll are prohibited.
b. Simultaneous moving of both ENG POWER CONT (EPC) levers to IDLE or OFF in flight is prohibited.
c. Rearward ground taxi is prohibited.
RESTRICTED MANEUVERS
Manual operation of the stabilator in flight is ______, except as required by formal training and _________________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 __________ to windows on ______________.
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 exhaust fumes in the helicopter and heat damage to windows on open cargo doors.
High-Speed Yaw Maneuver Limitation
Above __ KIAS avoid _____________ to prevent excess tail rotor system loading.
High-Speed Yaw Maneuver Limitation
Above 80 KIAS avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.
Bank Angle Limitation
Bank angles shall be limited to __° when either
PRI SERVO PRESS caution appears.
Bank angles shall be limited to 30° when either
PRI SERVO PRESS caution appears.
LANDING GEAR LIMITATIONS
Do not exceed a touchdown sink rate (feet-per-minute) of:
Gross weight Level Terrain Slopes
Blw 16,825 lb _____ ____
Abv 16,825 lb _____ ____
Do not exceed a touchdown sink rate (feet-per-minute) of:
Gross weight Level Terrain Slopes
Blw 16,825 lb 540 360
Abv 16,825 lb 300 180
LANDING SPEED LIMITATIONS
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.
SLOPE LANDING LIMITATIONS
__° nose-up, right wheel up or left wheel upslope. The slope limitations shall be further reduced by _° for every _ knots of wind.
__° nose downslope. Landing in downslope conditions with tail winds greater than __ 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 ____________
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.
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 30 minutes at a time with pressure fluctuations when the helicopter is known to be at a nose-up attitude (i.e., slope landings or hover with extreme aft CG).
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. The pilot should be prepared to use the toe brakes.
Slope landings with skis installed are limited to 10° nose-up and right wheel or left wheel upslope. The slope limitation shall be further reduced by 2° for every 5 knots of wind above 12 knots.
CAUTION - When performing slope landings with external fuel tanks, ensure tank to ground clearance.
FLIGHT IN ICING CONDITIONS
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into ____ or _____ icing conditions.
- _____________
- _____________
- _____________
- _____________
- _____________
Flight into moderate icing conditions, ___________________________ must be installed, operational, and turned on.
Flight into heavy or severe icing is _________.
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace or light icing conditions.
- Windshield Anti-ice.
- Pitot Heat.
- Engine Anti-ice.
- Engine Inlet Anti-ice Modulating Valve.
- Insulated Ambient Air Sensing Tube.
Flight into moderate icing conditions, all equipment in paragraph 5.28 b. and blade deice kit must be installed, operational, and turned on.
Flight into heavy or severe icing is prohibited.
Helicopters equipped with blade erosion kit tape are prohibited from flight into icing conditions.
Flight into known or forecast icing conditions with EIBF installed is prohibited.
NOTE - The ice detecting system is calibrated for 100 KIAS. When flying at airspeeds above 100 KIAS, the ice rate meter will indicate higher LWC than the actual conditions.
ROTOR START AND STOP LIMITS
Maximum wind velocity for rotor start and stop is __ KTS from any direction.
Maximum wind velocity for rotor start and stop is 45 KTS from any direction.
MANEUVERING LIMITATIONS
NOTE - Maneuvers entered from a low power setting may result in ___________ of ___% RPM R or greater.
NOTE - Maneuvers entered from a low power setting may result in transient droop of 5 % RPM R or greater.
APU OPERATION LIMITS
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 __________\_up to an ambient temperature of _\_°C.
To prevent APU overheating, APU operation at ambient temperature of 43°C 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.
WINDSHIELD ANTI-ICE LIMITATIONS
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.
TURBULENCE AND THUNDERSTORM OPERATION
Intentional flight into thunderstorms is _______\_.
Intentional flight into ____\_ turbulence is prohibited.
Intentional flight into turbulence with a sling load attached and an inoperative ______________\_ is prohibited.
Intentional flight into thunderstorms is prohibited.
Intentional flight into severe turbulence is prohibited.
Intentional flight into turbulence with a sling load attached and an inoperative collective pitch control friction is prohibited.
Limitations for Maneuvering With Sling Loads
Maneuvering limitations with a sling load are limited to a maximum of __° angle of bank in forward flight.
Side flight is limited by ________ and is decreased as __________.
Rearward flight with sling load is limited to __ knots.
Limitations for Maneuvering With Sling Loads
Maneuvering limitations with a sling load 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.
ROTOR BRAKE/GUST LOCK LIMITATIONS
Operating an engine against the gust lock is _______.
Rotor brake shall not be applied with engine(s) operating and rotor turning except during an emergency stop. Maximum rotor speed for emergency rotor brake applications is __% NR.
Routine stops will be with engine(s) off, NR below __% and with ____ psi applied to stop the rotor in not less than __ seconds.
Minimum rotor brake pressure for engine start is ___ psi. Maximum rotor brake pressure for engine start is ___ psi.
Use of the rotor brake with engine(s) operating is restricted to ___ and ___ engine starts and operations at ____ only.
Single and dual engine starts and operation at ____ with rotor brake on are not time limited.
Operating an engine against the gust lock is prohibited.
Rotor brake shall not be applied with engine(s) operating and rotor turning except during an emergency stop. Maximum rotor speed for emergency rotor brake ap- plications is 76% NR.
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.
Minimum rotor brake pressure for engine start is 450 psi. Maximum rotor brake pressure for engine start is 690 psi.
Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at IDLE only.
Single and dual engine starts and operation at IDLE with rotor brake on are not time limited.
TORQUE-Q
10 SECOND TRANSIENT
Dual-Engine
Above 80 KIAS _______-______%
80 KIAS or below _______-______%
Single-Engine _______-______%
CONTINUOUS
Dual-Engine
Above 80 KIAS _______-______%
80 KIAS or below _______-______%
Single-Engine _______-______%
10 SECOND TRANSIENT
Dual-Engine
Above 80 KIAS 100-144% 4
80 KIAS or below 120-144%
Single-Engine 135-144%
CONTINUOUS
Dual-Engine
Above 80 KIAS 0-100% 1
80 KIAS or below 0-120% 2
Single-Engine 0-135% 3
