Operating Limitations & Pre-flight Procedures

Question 1

Wind Limitations

Answer 1

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 gust spread, compare minimum and maximum velocities.

b. Maximum wind for hovering is 35 knots crosswind and 30 knots tailwind.

For hover operations at gross weights above 3200 pounds:

a. IGE maneuvers - refer to chapter 8
b. OGE maneuvers - calm wind only

Question 2

Torque Meter

Answer 2

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 seconds maximum).
INTENTIONAL USE IS PROHIBITED

Question 3

N2 Transient Overspeed Limits

Answer 3

From 0 to 32% torque, Maximum 107% Engine RPM for 15 seconds. Decrease to 103% Engine RPM at 100% torque for 15 seconds. For torque settings between 32 and 100%, refer to the chart.

Question 4

Control Movements

Answer 4

CAUTION: For gross weights greater than 3000 pounds 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.

Question 5

Engine Limitations

Answer 5

WARNING: Use of the throttle to control RPM is not authorized. (Refer to chap. 9, Emergency Procedures and the USAAWC Flight Training Guide for exceptions.)

Question 6

Engine Starter Limitations

Answer 6

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. Battery
25 seconds - ON. 40 seconds - ON
30 seconds - OFF. 60 seconds - OFF
25 seconds - ON. 40 seconds - ON
30 seconds - OFF. 60 seconds - OFF
25 seconds - ON. 40 seconds - ON
30 minutes - OFF. 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

Question 7

Turbine Outlet Temperature (TOT) Limits Caution

Answer 7

CAUTION: Exceeding the limits of 810*C TOT or 100% Torque may cause N1 topping with resultant rotor droop.

Question 8

Aerobatic Maneuvers

Answer 8

Aerobatic Maneuvers are prohibited. Aerobatic flight is defined to be any intentional maneuver involving and abrupt change in aircraft attitude, and abnormal attitude, pitch angle greater than 30 degrees or roll angles greater than 60 degrees, or abnormal acceleration not necessary for normal flight.

Question 9

VMC Airspeed Limitations

Answer 9

a. At 3000 pounds gross weight and below

 VMC VNE 130 KIAS sea level to 3000 feet density altitude.  Decrease VNE 3.5 KIAS per 1000 feet above 3000 feet density altitude.  Maximum density altitude is 20,000 feet.

b. ABOVE 3000 pounds gross weight:

 VMC VNE 122 knots sea level to 3000 feet density altitude.  Decrease VNE 7.0 KIAS per 1000 feet above 3000 feet density altitude.  Maximum density altitude 13,500 feet.

Question 10

Flight Restrictions for High Power

Answer 10

VNE is 80 Knots with >85% to 100% Torque applied.

Question 11

Fuel Pressure

Answer 11

R: 4.0 PSI Minimum
G: 4.0 to 30 PSI Continuous Operation
R: 30 PSI Maximum

R: 8 PSI Minimum - Type A, A-1, JP-5, JP-8 fuel below -18C to -32C

Question 12

Flight Restrictions for High Power

Answer 12

VNE is 80 knots with >85% to 100% torque applied.

Question 13

Transmission Oil Temperature

Answer 13

G: 15C to 110C Continuous Operation
R: 110*C Maximum

Question 14

Rotor Indicator

Answer 14

R: 90% Minimum Operation
Y: 50 to 60% Accelerate through this range
G: 90 - 107% Normal operation
R: 107% Maximum

Power on Transient Rotor Droop Limit is 95% (5 seconds Maximum)
N2 75% to 88%, seconds maximum (time is not cumulative)

Question 15

Altitude Limitations

Answer 15

a. 3000 pounds gross weight and below:
Maximum operating
VFR 20,000 feet pressure altitude
IFR 14,000 feet pressure altitude

b. ABOVE 3000 pounds gross weight
Maximum operating
VFR 13,500 feet pressure altitude
IFR 8,000 feet pressure altitude

Question 16

Engine Anti-Ice Limitations

Answer 16

a. Engine anti-ice shall not be used in ambient temperatures above 4C.
b. Engine anti-ice shall be ON for flight in visible moisture in temperature 4C or below

Question 17

Turbine Outlet Temperature (TOT)

Answer 17

G: 100 to 738C Continuous
Y: 738 to 810C Take-off Power Range (5 minute limit)
R: 810*C Maximum

810C to 843C, 6 second transient (not to be used intentionally).

R: 927*C Maximum during starting and shutdown (10 seconds maximum)

NOTE: The Red Warning light illuminates when either of the following conditions are exceeded 810C to 927C for 10 seconds, or higher than 927*C.

Question 18

Airspeed

Answer 18

NOTE: Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM.

G: 0 to 130 Knots Continuous Operation
R: 130 Knots Maximum
B: 100 Knots Maximum for Autorotation

VNE for internal gross weight above 3200 pounds is 78 KIAS, not to exceed placards VNE.

Question 19

Engine Starting Limitations

Answer 19

During starting if N1 does not reach 58% in a total time of 45 seconds (or 60 seconds below 10C FAT), close throttle and press started button until TOT is below 200C. If engine fails to start on third attempt, abort start and make an entry on DA Form 2408-13-1. Starter engage time limits do not apply to engine starting limitations should abort start procedures become necessary.

Question 20

Gas Producer

Answer 20

G: 60 to 105% Continuous operation
R: 105% Maximum

105 to 106% Transient (15 seconds Maximum)

Question 21

Lateral Center of Gravity Limits (Chapter 5)

Answer 21

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

Lateral Center of Gravity Limits (Chapter 6): Lateral CG limits are -1.0 inch left and +2.0 inches right at any approved longitudinal center of gravity for gross weights above 3200 pounds.

Question 22

Engine Oil Pressure

Answer 22

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 operations the oil pressure may exceed the maximum of 130 PSI. Stabilize the engine at idle speed of 60 to 64% until the engine oil temperature is above 0*C and the engine oil pressure is within normal limits.

Question 23

Flight Restrictions at Low “Gs”

Answer 23

Flight at less than +0.5g is prohibited.

Question 24

Power Turbine Indicator

Answer 24

R: 97% Minimum operation
G: 97 to 100% Continuous operation
R: 100% Maximum

Question 25

Longitudinal Center of Gravity Limit Chart

Answer 25

The forward CG limit is always 106.0 from 2000 pounds gross weight up to 3200 pounds gross weight. Above 3200 pounds gross weight the forward CG limit moves aft to 106.9.

The aft CG limit from 2000 pounds gross weight up to 2425 pounds gross weight is 114.2. At 2425 pounds gross weight the CG decreases to 112.3 at 3000 pounds gross weight, 111.6 at 3200 pounds gross weight, and 110.8 at 3350 pounds gross weight.

Question 26

Transmission Oil Pressure

Answer 26

G: 30 to 50 PSI continuous operation
R: 30 PSI Minimum. 70 PSI Maximum

Question 27

Engine Oil Temperature

Answer 27

G: 0C to 107C Continuous Operation
R: 107*C Maximum

Question 28

Load meter

Answer 28

R: 70% Maximum