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Limits
E P's
Therapist
CH-9 Warnings
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100
Engine Torque
0-100% continuous. 100-112% 30 min limit. 112-121% 10 sec transient. 121-131% 2 sec transient.
100
ENGINE COMPRESSOR STALL
1. Collective — Reduce. 2. ENG ANTI ICE and HTR switches — ON. 3. LAND AS SOON AS POSSIBLE.
100
Flight with Doors Removed
a. The helicopter shall not be flown with only one crew door removed. b. The helicopter shall not be flown with either avionics compartment access door removed. c. For flight with crew doors removed, maximum permissible speed (Vne) is 110 KIAS (fig. 5-2).
100
ROCKET/MISSILE – HANGFIRE
Activation of Jettison switch during missile hangfire may cause missile launcher package to veer off course, possibly into the aircraft or rotor disk.
100
RUNAWAY GUN
1. Orient gun in a safe direction. 2. MASTER switch — STBY. 3. Allow gun to fire out. 4. Gun switch — SAFE
200
%RPM - NP (Power Turbine)
100% Normal. 107% Maximum. 107-112% 15 Sec Transient. 71-91% Transient operation only.
200
ENGINE OVERSPEED
1. Collective — Increase to load the rotor and sustain engine/rotor RPM below the maximum operating limit. 2. FADEC MANUAL Operation — Perform.
200
Starter Limits.
Starter engagement shall not exceed the times specified in the following schedule: External 40 sec ON 30 sec OFF 40 sec ON 30 sec OFF 40 sec ON 30 min OFF (cool down) Battery Starts 60 Sec ON 60 sec OFF 60 Sec ON 60 sec OFF 60 Sec ON 30 min OFF (cool down)
200
ENGINE MALFUNCTION – PARTIAL OR COMPLETE POWER LOSS
Do not respond to the RPM audio and/or display on MFD and/or MPD without first confirming engine failure by observing one or more of the other indications. Normal indications signify that the engine is functioning properly and that there is a malfunction in the engine or rotor sensing system(s).
200
ELECTRICAL FIRE – FLIGHT
1. AC and DC GEN switches — OFF. 2. LAND AS SOON AS POSSIBLE. 3. EMER SHUTDOWN after landing.
300
TGT (Turbine Gas Temperature)
Starting 843-927* C 10-Sec transient. 927* C Maximum momentary peak no more than 1 second. Normal Operations 0-716* C Continuous. 716-802* C 30-Min limit. 802-905* C 12-Sec transient.
300
COMPLETE LOSS OF ELECTRICAL POWER
1. LAND AS SOON AS POSSIBLE. If RPM cannot be controlled manually: 2. AUTOROTATE when over a safe landing area. 3. EMER SHUTDOWN. Accomplish during descent if time permits.
300
Turbulence
a. Intentional flight into severe or extreme turbulence is prohibited. b. Intentional flight into moderate turbulence is prohibited when the weather report or forecast is based on fixed wing aircraft above 12,500 pounds gross weight. c. Intentional flight into moderate turbulence is permitted when the weather report or forecast is based on rotary-wing aircraft or fixed wing aircraft under 12,500 pounds gross weight.
300
HYDRAULICS X 2
1=Bank angles exceeding 45° without hydraulic boost may cause roll rates to exceed controllable limits 2=Do not return the HYD SYS switch to the HYD SYS position for the remainder of the flight. This prevents any possibility of a surge in the hydraulic system creating sudden, unexpected control movements
300
DITCHING – POWER OFF
1. AUTOROTATE — Decelerate to minimum forward speed as helicopter nears the water. Apply all remaining collective as the helicopter enters the water. Maintain a level attitude as the helicopter sinks and until it begins to roll. Apply cyclic in the direction of roll. 2. Doors — Jettison as the helicopter enters the water. 3. CPG or passenger and pilot — Exit when main rotor stops
400
Engine Limits
The engine limitations consists of torque (ENG TRQ %), turbine gas temperature (TGT), and rpm (NG and NP).
400
EGI FAILURE
1. EGI DC circuit breaker — Out. 2. EGI DC circuit breaker — In. 3. Last known present position — Enter. 4. If in flight — Input aircraft heading. 5. Execute a MANUAL EGI alignment. If EGI functionality is not restored or fails again: 6. EGI DC circuit breaker — Out. 7. LAND AS SOON AS PRACTICABLE
400
Wind Limitations
a. Engine starting — 45 knots maximum. b. Maximum crosswind and tailwind for hover is 35 knots, however this may be reduced by lateral CG imbalances. c. Maximum tailwind for hover without inlet blast shields installed is 20 knots. d. Heading hold engaged — 20 knots maximum.
400
COMPLETE LOSS OF TAIL ROTOR THRUST
Helicopter sideslip may become uncontrollable and will begin to spin on its vertical axis at airspeeds below 40 knots. Degree of roll and sideslip may be varied by varying throttle and/or collective. Autorotation may be the only option.
400
WARNING MESSAGES and Actions
ENGINE OUT Verify condition, Autorotate. LOW RPM ROTOR Verify condition, Adjust collective. LOW FUEL PRES LAND AS SOON AS POSSIBLE. FADEC FAIL Refer to emergency procedure. HIGH RPM Verify condition, Adjust collective. XMSN OVER TRQ Verify condition, LAND AS SOON AS POSSIBLE. ENG OVER TRQ Verify condition, LAND AS SOON AS POSSIBLE. TGT OVER TEMP Verify condition, LAND AS SOON AS POSSIBLE. ENG OVER SPD Verify condition, LAND AS SOON AS POSSIBLE. CHECK THROTTLE * Adjust throttle. LOW ALTITUDE
500
Rotor Limitations
Autorotation limitations are based on collective full down, throttle at idle, or below. After autorotation touchdown, the pilot shall smoothly center the cyclic and reduce the collective to the full down position. The pilot shall avoid abrupt, large aft cyclic movements which can cause unnecessary high main rotor yoke flapping loads with low rotor speed on the ground.
500
MAIN DRIVESHAFT FAILURE
1. AUTOROTATE — Throttle full open. If FADEC failure is annunciated: 2. Throttle — Reduce to idle detent. 3. AUTO/MAN switch — MAN. 4. Throttle — Adjust to maintain 100% NP, if time permits. After landing: 5. EMER SHUTDOWN
500
Prohibited Maneuvers
a. Flight maneuvers causing a negative “g” load are prohibited. b. The speed for any and all maneuvers shall not exceed the level flight velocities as stated on the airspeed operating limits chart (fig. 5-2). c. Aerobatic maneuvers intentionally exceeding pitch or roll angles greater than ±30° or ±60° respectively are prohibited. d. Mast torque is limited to 95% in forward flight above 60 Kts. airspeed.
500
Fadec x 3
1=If the throttle is not closed, excessive left and right yaws may cause loss of aircraft control just prior to touchdown. 2=Regardless of annunciator indication, the FADEC AUTO/MAN switch shall be placed in the manual mode. 3=Failure to switch to manual mode will cause main rotor RPM to droop/overspeed as collective is increased/decreased.
500
LOSS OF TAIL ROTOR COMPONENTS
(1) Enter autorotative descent (power off). (2) Maintain airspeed above minimum rate of descent airspeed. (3) If run-on landing is possible, complete autorotation with a touchdown airspeed as required for directional control. (4) If run-on landing is not possible, start to decelerate from about 100 feet altitude so that forward groundspeed is at a minimum when the helicopter reaches 10 to 20 feet: execute the termination with a rapid collective pull just prior to touchdown in a level attitude with minimum ground speed.