Ch 5 Flashcards
ROTOR limits
R 90 % Minimum Operation
Y 50 to 60 % Accelerate through this range
G 90 to 107 % Normal Operation
R 107 % Maximum
Power on Transient Rotor Droop Limit is 95% (5 seconds Maximum).
TURBINE OUTLET TEMPERATURE
100 to 738 C Continuous Operation
738 to 810 C Take-off Power Range (5 Minute Limit)
810 C Maximum
810 to 843 C, 6 second transient (Not to be used intentionally).
927 C Maximum during Starting and Shutdown (10 seconds Maximum)
NOTE
The Red Warning light illuminates when either of the following conditions are exceeded: 810 to 927 C for 10 Seconds, or higher than 927 C.
ENGINE OIL PRESSURE
Y 50 PSI Minimum below 78% N1
G 90 PSI Minimum from 78% to 94% N1
G 115 PSI Minimum above 94% N1 (double wide arc)
R 50 PSI Minimum, 130 PSI Maximum
NOTE
During cold temperature operation the oil pressure may exceed the maximum of 130 PSI. Stabilize the engine at idle speed of 60 to 62% until the engine oil temperature is above 0 C and the engine oil pressure is within normal limits.
GAS PRODUCER
G 60 TO 105% Continuous Operation
R 105% Maximum
105 to 106% Transient-(15 seconds Maximum)
TORQUE METER
G 0 to 85% Continuous Operation
Y > 85 to 100% Take-off Power Range (5 Minute Limit)
R 100% Maximum
Transient Torque Limit is 100 to 110% (5 second Maximum). INTENTIONAL USE IS PROHIBITED.
WIND LIMITATIONS
a. The helicopter can be started in a maximum wind velocity of 45 knots and a maximum gust spread of 15 knots.
NOTE
Gust spreads are not normally reported. To obtain spread, compare minimum and maximum velocities.
b. Maximum wind for hovering is 35 knots crosswind and 30 knots tailwind.
c. For hover operations at gross weights above 3200 lbs:
1. IGE maneuvers – refer to chapter 8.
2. OGE maneuvers – calm wind only.
ENGINE STARTING LIMITATIONS
During starting if N1 does not reach 58% in a total time of 45 seconds (or 60 seconds below 10 C FAT), close throttle and press starter button until TOT is below 200 C.
If engine fails to start on third attempt, abort start and make an entry on DA Form 2408-13-1. Starter engage time limits above do not apply to engine starting limitations should abort start procedures become necessary.
ENGINE OIL TEMPERATURE
0 C to 107 C Continuous Operation
107 C Maximum
TRANSMISSION OIL TEMPERATURE
15 C to 110 C Continuous Operation
110 C Maximum
TRANSMISSION OIL PRESSURE
30 to 50 PSI Continuous Operation
30 PSI Minimum, 70 PSI Maximum
LOADMETER
70.0% Maximum
FUEL PRESSURE
- 0 PSI Minimum
- 0 to 30 PSI Continuous Operation
30 PSI Maximum
8 PSI Minimum - Type A, A-1, JP-5, JP-8 fuel below -18 C (0 F) to -32 C (-25 F)
AIRSPEED INDICATOR
NOTE
Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM.
0 to 130 Knots Continuous Operation
130 Knots Maximum
100 Knots Maximum for Autorotation
VNE for internal Gross Weight above 3,200 pounds is 78 KIAS, not to exceed placarded VNE.
FUEL QUANTITY GAUGE
R On Empty
POWER TURBINE INDICATOR
97% Minimum Operation
97 to 100% Continuous Operation
100% Maximum
N2 75% to 88%, 60 Seconds Maximum (time not cumulative)
TURBINE OUTLET TEMPERATURE (TOT) LIMITS
Caution
Exceeding the limits of 810 C TOT or 100% torque may cause N1 topping with resultant rotor droop.
ENGINE RPM LIMITATIONS
Warning
Use of the throttle to control rpm is not authorized. (Refer to Chapter 9, Emergency Procedures and the USAAWC Flight Training Guide for exceptions.)
N2 TRANSIENT OVERSPEED LIMITS
N2 transient overspeed limit is 15 seconds maximum. Shaded area represents allowable overspeed.
Explanation:
N2 transient overspeed is dependant upon engine torque.
0 - 32% Engine torque: 107% Engine RPM.
32% - 100% Engine torque: gradually decreases to 103% Engine RPM.
WEIGHT LIMITATIONS
Maximum allowable ramp weight is 3,350 lbs.
Maximum allowable gross weight for hover/flight is 3,350 lbs.
Minimum front seat weight is 170 lbs.
NOTE
Use ballast as required to maintain basic weight CG within limits.
LONGITUDINAL CENTER OF GRAVITY LIMITS
VMC Center of gravity limits are from station 106.0 to 114.2; however, the forward and aft limits are variable depending upon gross weight and aircraft configuration. Refer to Center of Gravity vs. Gross Weight Chart in Chapter 6.
NOTE
Station 0 (datum) is located 55.16 inches forward of forward jack point centerline.
IMC Longitudinal CG limits are from station 106 to 110 at GW of 2400 pounds to 3200 pounds and 106.9 to 110.0 at gross weights above 3200 pounds. Refer to Chapter 6.
DOOR(S) OFF
(1) No change from basic helicopter CG with only the aft cabin door(s) OFF.
(2) With one or both forward doors off, the longitudinal CG limits are the same as with doors on.
(3) Actual weight change shall be determined after doors, etc., have been removed and ballast readjusted, if necessary, to return basic weight center of gravity to within allowable limits.
LATERAL CENTER OF GRAVITY LIMITS
NOTE
Lateral CG limits vary depending on longitudinal CG location. Refer to Lateral vs. Longitudinal CG limits chart in Chapter 6.
a. 3.0 inches left of helicopter centerline.
b. 4.0 inches right of helicopter centerline.
FUEL BOOST PUMP LIMITATIONS
Fuel boost pumps shall be ON during normal operations.
ENGINE STARTER LIMITS
a. If there is no rise in TOT within the first 20 seconds of energizing starter, limit starter energizing time to the following:
External Power 25 seconds - ON 30 seconds - OFF 25 seconds - ON 30 seconds - OFF 25 seconds - ON 30 MINUTES - OFF
Battery 40 seconds - ON 60 seconds - OFF 40 seconds - ON 60 seconds - OFF 40 seconds - ON 30 MINUTES - OFF
b. If there is a rise in TOT within the first 20 seconds of energizing starter, limit starter energizing time to the following:
EXTERNAL/BATTERY POWER 1 Minute - ON 1 Minute - OFF 1 Minute - ON 1 Minute - OFF 1 Minute - ON 30 Minutes - OFF
Ch 5 LOW INLET PRESSURE
CAUTION
Takeoff with LOW INLET PRESSURE caution light illuminated is PROHIBITED.
ENGINE ANTI-ICE LIMITATIONS
a. Engine anti-ice shall not be used in ambient temperatures above 4 C.
b. Engine anti-icing shall be ON for flight in visible moisture in temperature 4 C or below.
FLIGHT RESTRICTIONS AT LOW “G”s
Flight at less than +0.5g is prohibited.
VMC AIRSPEED LIMITATIONS
NOTE
All airspeed values are Indicated Airspeed (IAS), except when Calibrated Airspeed (CAS) is specifically stated.
a. At 3,000 POUNDS GROSS WEIGHT AND BELOW:
VMC VNE 130 KIAS sea level to 3,000 feet density altitude. Decrease VNE 3.5 KIAS per 1,000 feet above 3,000 feet density altitude. Maximum density altitude - 20,000 feet.
b. ABOVE 3,000 POUNDS GROSS WEIGHT:
VMC VNE 122 knots sea level to 3,000 feet density altitude. Decrease VNE 7.0 KIAS per 1,000 feet above 3,000 feet density altitude. Maximum density altitude - 13,500 feet.
c. VNE for internal GW above 3200 lbs is 78 KIAS, not to exceed placarded VNE .
ALTITUDE LIMITATIONS
a. 3,000 POUNDS GROSS WEIGHT AND BELOW
Maximum operating - VFR 20,000 feet pressure altitude. - IFR 14,000 feet pressure altitude.
b. ABOVE 3,000 POUNDS GROSS WEIGHT
Maximum operating - VFR 13,500 feet pressure altitude. - IFR 8,000 feet pressure altitude.
FLIGHT RESTRICTION FOR HIGH POWER
VNE 80 knots with >85% TO 100% Torque applied.
SLOPE LANDING/TAKEOFF LIMITATIONS
Slope operations shall be limited to slopes of 8 degrees or less.
CAUTION
Caution is to be exercised for slopes greater than 5 degrees since rigging, loading; terrain and wind conditions may alter the slope landing capability.
AEROBATIC MANEUVERS
Aerobatic maneuvers are prohibited. Aerobatic flight is defined to be any intentional maneuver involving an abrupt change in aircraft attitude, an abnormal attitude, pitch angle greater than 30 degrees or roll angles greater than 60 degrees, or abnormal acceleration not necessary for normal flight.
CONTROL MOVEMENTS
CAUTION
For gross weights greater than 3000 LBS and density altitudes greater than sea level, the directional control margin may be significantly reduced while hovering in winds from the right greater than 20 knots or for right sideward flight at speeds greater than 20 knots.
Abrupt control movements, including rapid and repetitive anti-torque pedals reversals are prohibited to avoid excessive stresses in the structure. This restriction in no way limits normal control application.
