Chapter 5 (Chg 8) 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 45 psi
make
an entry on appropriate maintenance form..
Sudden pressure drop (more than 10 psi) without fluctuation requires an entry on appropriate maintenance form.
Rotor Start and Stop Limits
45 knots - Maximum wind velocity for rotor start and stop from any direction.
Engine Starter Limits
a. …… 60 seconds between start attempts ……
b. 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 start cycles. A 30-minute rest period is the required before any additional starts.
c. At ambient temperatures above 15°C up to 52°C (59°F up to 126°F), two consecutive start cycles may be made. A 30-minute rest period is the required before any additional cycles.
Pneumatic Source Inlet Limits
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 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 starts 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 compartent is 125 pounds.
Maximum cargo hook capacity (UH-60M) is 9000 pounds.
Max weight for UH-60M s is 22000 pounds.
Max weight is futher limited by cargo floor maximum capacity of 300 lbs per square foot.
Airspeed Operating Limits
130 KIAS = Maximum airspeed for one engine inoperative.
130 KIAS = Maximum airspeed for autorotation at a gross weight of greater than 16,825 pounds.
150 KIAS = Maximum airspeed for autorotation at a gross weight of 16,825 pounds or less.
Sideward/rearward flight into the wind, when combined with windspeed, shall not exceed 45 knots.
Hydraulic system inoperative airspeed limits
170 KIAS = One Hydraulic system inoperative
150 KIAS = Two Hydraulic systems inoperative
140 KIAS = Two Hydraulic systems inoperative in IMC
SAS inoperative airspeed limits
170 KIAS = One SAS inoperative
150 KIAS = Two SAS inoperative
140 KIAS = Two SAS inoperative in IMC
Maximum airspeed for Landing Light
130 KIAS = Maximum forward airspeed for extending
180 KIAS = Airspeed limit if extended
Maximum airspeed for Searchlight
100 KIAS = Maximum forward airspeed for extending
180 KIAS = Airspeed limit if extended
Airspeed Limitations Following Failure Of The Automatic Stabilator Control System
Manual control is available:
(1) Below 40 KIAS: The stabilator shall be set full down
(2) Above 40 KIAS: The stabilator shall be set at 0°
(3) 120 KIAS: Autorotation airspeed shall be limited at all gross weights.
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
Prohibited Maneuvers
a. Hovering turns greater than 30° per second are prohibited. Intentional maneuvers beyond attitudes of +/- 30° in pitch or over 60° in roll are prohibited.
b. Simultaneous moving of both ENG POWER CONT levers to IDLE or OFF (throttle chop) in flight is prohibited.
c. Rearward ground taxi is prohibited.
Restricted Maneuvers
Manual Operation of the Stabilator
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 of AUTO mode malfunctions.
Downwind Hovering
Prolonged rearward flight and downwind hovering are to be avoided to prevent exhaust fumes in the helicopter and heat damage to windows on open cargo doors.
Maneuvering Limitations
(note)
Maneuvers entered from a low power setting may result in transient droop of 5% RPM R or greater.
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
Maximum 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 os limited to 35 knots.
Bank Angle Limitation
Bank angles shall be limited to 30° when either PRI SERVO PRESS caution appears.
Landing Gear Limitation
Landing Gear Limitations
Do not exceed a touchdown sink rate:
Gross weights of up to 16,825 pounds
540 fpm = on level terrain
360 fpm = on slopes
Gross weights above 16,825 pounds
300 fpm = on level terrain
180 fpm = on slopes
Landing Speed Limitations
Maximum forward touchdown speed is limited to 60 knots ground speed on level terrain.
Slope Landing Limitations
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.
b. 6° nose downslope. Landing in down slope conditions with tail winds greater than 15 knots shall not be conducted.
c. The main gearbox may be operated up to 30 minutes at a time with pressure fluctuations when the helicopter os known to be at a nose-up attitude.
Flight in Ice
a. …… 4°C or below…… visible liquid moisture……
b. Helicopter 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 Modulation Valve
(5) Insulated Ambient Air Sensing Tube
c. Flight into moderate icing contions, all equipment in paragraph 5.30 b. and blade deice.
Flight into heavy or severe icing is prohibited.
d. Helicopters equipped with blades coated with Advanced Erosion Protection Coating (HONTEK) are autorized for flight into icing conditions.
Backup Hydraulic Pump Hot Weather Limitations
Backup hydraulic pump hot weather limits with the rotor system static.
FAT °C Operating Time Cool down time
-54°-32° UNLIMITED ——–
33°-38° 24 MINUTES 72 MINUTES
39°-52° 16 MINUTES 48 MINUTES
APU Operating Limitations
To prevent APU overheating, the APU operation at ambient temperature of 43°C and above with engine and rotor operating, is limited to 30 minutes.
With the 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 27°C (80°F)
Turbulence and Thunderstorm operation
a. Intentional flight into thunderstorms is prohibited.
b. Intentional flight into severe turbulence is prohibited.
c. Intentional flight into turbulence with a sling load attached and an inoperative collective pitch control friction is prohibited.
Blue Force Tracker Temperature Limits
Normal operating temperatures range: -26°C to +71°C
Caution: Operating the BFT system outside this range may cause failure or erratic operation.
EICAS and PFD Power Pod Color Codes
Red and Yellow striped tapes and red readouts indicate the limit above or below which continued operation is likely to cause damage or shorten component life.
Yellow tapes and readouts indicate the range when special attention should be given to the parameter the instruments represents.
Green tapes and readouts indicate the normal operating range of the parameter the instrument represents.
Rotor Brake/Gust Lock Limitations
a. Operating an engine against the gust lock is prohibited on rotor brake equipped helicopters.
b. 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 76 %NR
.
c. 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.
d. Minimum rotor brake pressure for engine start is 450 psi. Maximum rotor brake pressure for engine start is 690 psi.
e. Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at IDLE only.
f. Single and dual engine starts and operation at IDLE with rotor brake on are not time limited.
Engine Torque Limits
10-Second Transient
Dual-Engine
Above 80 KIAS: 100%-144%
80 KIAS or Below: 120%-144%
Single-Engine: 135%-144%
Continuous
Single-Engine: 0%-135%
Dual-Engine
Above 80 KIAS: 0%-100%
80 KIAS or Below: 0%-120%
Turbine Gas Temperature Limits
12-Second Transient: 903-949°C
2.5 Minutes Transient (Contingency Power): 879-903°C
10-Minute Limit: 846-879°C
Start Abort Limit: 851°C
30-Minute Limit: 793-846°C
Normal: 0-793°C
Engine Ng
12-Second Transient: 105%-106%
Continuous: 0-105%
Engine %RPM 1-2 Limits
12-Second Transient: 105%-107%
Transient: 101%-105%
Continuous: 95%-101%
Transient: 91%-95%
Avoid operations in 20%-40% and 60%-90% range except during start and shutdown
Engine Oil Pressure
5-Minute Limit: 100 - 120 PSI
Normal Operation: 26 - 100 PSI
Idle: 22-26 PSI
Engine Oil Temperature
30-minute Limit: 135 - 150°C
Continuous: -20 - 135°C
Main Transmission Oil Pressure Limits
Precautionary: 65 - 130 PSI
Continuous: 30 - 65 PSI
Idle and Transient: 20 - 30 PSI
Main Transmission Oil Temperature Limits
Precautionary: 105 - 140°C
Continuous: -20 - 105°C
Main Rotor %RPM R
POWER ON
Transient: 101%-107%
Continuous: 95%-101%
Transient: 91%-95%
POWER OFF (AUTOROTATION)
Maximum: 110%
Transient: 105%-110%
Normal: 90%-105%
Fuel Quantity Gauge Limits
Normal: > 200 LBS
Precautionary: 0 - 200 LBS
