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ENGINE % RPM 1-2 NP
12 sec transient  105-107% Transient             101-105% Continuous         95-101% Transient           91-95% Avoid operations in 20% - 40% and 60% - 90% range except for starting and shutdown.
ROTOR START AND STOP LIMITS
Maximum wind velocity for rotor start and stop is 45 kts from any direction.
ENGINE % TRQ
10 sec transient
DUAL 100-125%
SINGLE 110-135%

Continuous

DUAL 0-100%
SINGLE 0-110%
MAIN ROTOR % RPM R
POWER ON
Transient               101-107%
Continuous              95-101%
Transient                   91-95%

MAIN ROTOR % RPM R
POWER OFF (AUTOROTATION)
Maximum                   110%
Transient                105-110%
Normal 90-105%
TGT LIMITATIONS
12 sec transient    850-886ºC
Start abort             850ºC

30 min limit          775-850ºC
Normal                  0-775ºC

ENGINE NG
12 sec transient    102-105%
30 min limit          99-102%

Continuous           0-99%
ENGINE OIL TEMP
30 min limit          135-150ºC
Continuous           -50-135ºC
TRANSMISSION OIL TEMP
Precautionary       105-120ºC
Continuous           -50-105ºC
ENGINE OIL PRESSIRE
Continuous           20-100 psi
35 psi min at 90% Ng and above

TRANSMISSION OIL PRESSURE
Precautionary       65-130 psi
Continuous           30-65 psi
Idle & transient     20-30 psi
ENGINE STARTER LIMITS
At ambient temperatures of 15ºC and below, two consecutive start cycles may be made, followed by a 3 min rest period, followed by two additional start cycles.  A 30 min rest period then is required. At ambient temperatures above 15ºC and up to 52ºC, two consecutive start cycles may be made followed by a 30 min rest period is then required before additional starts.    
PNEUMATIC SOURCE INLET LIMITS
The minimum air source required to start the helicopter is 40 psig, and 30 ppm at 149ºC. The maximum is 50 psig at 249ºC.
ENGINE OVERSPEED CHECK LIMITATIONS
Engine overspeed check in flight is prohibited.  Engine overspeed checks, on the ground, are authorized by designated maintenance personnel only
ENGINE START LIMITS
Cross bleed start shall not be attempted unless the #1 eng anti-ice on or #2 eng anti-ice on advisory does not appear, and operating engine must be at 90% NG speed or above and rotor speed at 100% RPM R
LOADING LIMITS
Maximum capacity for each storage compartment is 125 pounds.
Maximum cargo hook capacity for UH-60A with either cargo hook is 8000 pounds.
Max weight is further limited by cargo floor maximum capacity of 300lbs per sq foot.
Max weight with 7 lug wheels is < 20,500 pounds.
14 lug wheels shall be utilized during ground operations when operating at or above gross weights of 20,500 pounds.
Rescue hoist max weight is 600 pounds.
PROHIBITED FLIGHT MANEUVERING LIMITS
Hovering turns of >30º per second are prohibited.   Intentional maneuvers beyond attitudes of   +/- 30º in pitch or over 60º in roll are prohibited.   Simultaneous moving of both eng power cont levers to idle or off in flight is prohibited.   Rearward ground taxi is prohibited
RESTRICTED FLIGHT MANEUVERING LIMITS
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 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.
NOTE: Maneuvers entered from a low power setting may result in transient droop of 5 % RPMR or greater
FLIGHT WITH CABIN DOOR(S)/WINDOWS(S) OPEN
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.   Gunner’s window(s) may be fully open up to 170 kias.   Cockpit doors sliding window will not be opened or closed during flight except during hover.   Flight with cockpit door(s) removed is prohibited.
AIRSPEED LIMITATIONS Maximum forward touchdown speed is limited to __kias ground speed on level terrain.   Max airspeed for one engine operations is ___kias.   Max autorotational airspeed at gross weights of 16,825 or less is ___kias.   Max autorotational airspeed at gross weights more than 16,825 is ___kias.   Sideward and rearward flight into the wind, when combined with wind speed shall not exceed ___kias.   One sas inoperative air speed is ___kias.   Two sas inoperative air speed is ___kias.   Two sas inoperative during imc air speed is ___kias.   One hydraulic system inoperative air speed is ___kias.   Two hydraulic systems inoperative air speed is ___kias.   Two hydraulic systems inoperative during imc air speed is ___kias.   Max air speed to extend the landing light is ___kias.   Max air speed to extend the search light is ___kias.   Max air speed with the landing light extended is ___kias.   Max air speed with the search light extended is ___kias.   Manual control of stabilator is available. Stabilator shall be full down at speeds below ___kias.   Stabilator shall be set at zero degrees for speeds above_ __kias.   Autorotation air speed shall be limited to ___kias at all gross weights.   Manual control of stabilator is not available.   Placard air speed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed ___kias.
Maximum forward touchdown speed is limited to 60kts ground speed on level terrain.   Max airspeed for one engine operations is 130kias.   Max autorotational airspeed at gross weights of 16,825 or less is 150kias.   Max autorotational airspeed at gross weights more than 16,825 is 130kias.   Sideward and rearward flight into the wind, when combined with wind speed shall not exceed 45kts.   One sas inoperative air speed is 170kias.   Two sas inoperative air speed is 150kias.   Two sas inoperative during imc air speed is 140kias.   One hydraulic system inoperative air speed is 170kias.   Two hydraulic systems inoperative air speed is 150kias.   Two hydraulic systems inoperative during imc air speed is 140kias.   Max air speed to extend the landing light is 130kias.   Max air speed to extend the search light is 100kias.   Max air speed with the landing light extended is 180kias.   Max air speed with the search light extended is 180kias.   Manual control of stabilator is available.
Stabilator shall be full down at speeds below 40kias.   Stabilator shall be set at zero degrees for speeds above 40kias.   Autorotation air speed shall be limited to 120kias at all gross weights.
Manual control of stabilator is not available.   Placard air speed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed 120kias.
HIGH SPEED YAW FLIGHT MANEUVERING LIMITS
Above 80 kias avoid abrupt full pedal inputs to prevent excess tail rotor system loading.  
SLING LOAD FLIGHT MANEUVERING LIMIITS
Maneuvering limits with a sling load is limited to a maximum of 30º angle of bank in forward flight.   Side flight is limited by bank angle and is decreased as airspeed increases.
Rearward flight with a sling load is limited to 35kts
BANK ANGLE LIMITATIONS

Bank angle shall be limited to 30º when either PRI SERVO PRESS caution light appears.
LANDING GEAR LIMITATIONS
Do not exceed a touchdown sink rate of 540 feet per minute on level terrain and 360 feet per minute on slopes with gross weight up to 16,825 pounds.   Do not exceed a touchdown sink rate of 300 feet per minute on level terrain and 180 feet per minute on slopes with gross weight above 16,825 pounds.
SLOPE LANDING LIMITATIONS
15º nose up, right wheel up or left wheel upslope, reduced by 2º for every 5kts of wind.   6º nose down slope.  Landing in nose down slope conditions with tail winds greater than 15kts 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.
ENVIRONMENTAL RESTRUCTIONS
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace or light icing conditions.   1.windshield anti-ice 2.pitot heat 3.engine anti-ice 4. engine inlet anti-ice modulating valve 5. insulated ambient air sensing tube
Flight into moderate icing conditions all equipment and the blade deice kit must be installed, operational, and turned on. Flight into heavy or severe icing is prohibited.
BACKUP HYDRAULIC PUMP HOT WEATHER LIMITS WITH THE ROTOR SYSTEM STATIC.
OPERATION/COOL DOWN -54-32 ºC   UNL       N/A 33-38 ºC   24min   72min 39-52 ºC   16min   48min
APU OPERATING LIMITS
To prevent APU overheating at ambient temperature of 43ºC and above with the engine and rotor operating is limited to 30 minutes.   With the engine and rotor not operating, the APU can be operated continuous up to a temperature of 51ºC.
WINDSHEILD ANTI-ICE LIMITATIONS
Windshield anti-ice check shall not be done when FAT is over 27ºC
TURBULANCE AND THUNDERSTORM OPERATIONS
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
GUST LOCK LIMITATIONS
Dual-engine operations with the gust lock engaged is prohibited.
Single-engine operations 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
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 drops (more than 10 psi) without fluctuations require an entry on DA form 2804-13-1.
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