Army Rotary Wing P2 Evaluation

Front 1

System Limits
5-5 Instrument Markings & Placards

*NOTE

Back 1

The minimum & maximum limits & the normal & cautionary operating ranges for the helicopter & its subsystems are indicated by instrument markings & placards. The instrument markings & placards represent careful aerodynamic calculations that are substantiated by flight test data.
*NOTE: The color markings on the instrument faces are indicated in the adjacent boxes by the following: R=Red, G=Green, Y=Yellow, B=Blue.

Front 2

System Limits
5-6 Engine Oil Pressure

Back 2

50 psi minimum below 78% N1
90 psi minimum from 78-94% N1
115 psi minimum above 94% N1 (Double Wide Arc)
50 psi minimum 130 psi Maximum

Front 3

System Limits
5-6 Engine Oil Temp

Back 3

0c to 107c Continuous Operation
107c Maximum

Front 4

System Limits
5-6 Engine Oil Temp & Pressure

*NOTE

Back 4

*NOTE: During cold temperature operation the oil pressure may exceed the maximum of 130psi. Stabilize the engine at engine idle speed of 60-62% until the engine oil temperature is above 0c and the engine oil pressure is within normal limits.

Front 5

System Limits
5-7 Transmission Oil Pressure

Back 5

30 psi to 50 psi Continuous operation
30 psi minimum 70 psi Maximum

Pressure Lgt comes on < 30 psi

Front 6

System Limits
5-7 Transmission Oil Temperature

Back 6

15c to 110c Continuous Operation
110c Maximum

Temp Lgt comes on > 110c

Front 7

System Limits
5-8 Loadmeter and Fuel Pressure

Back 7

Load Meter: 70.0% Maximum
Fuel Pressure:
4.0 psi minimum
4.0 to 30 psi continuous operation
30 psi maximum
8 psi minimum
(Type A, A1, JP5, JP8 below) -18c to -32c.

Front 8

System Limits
5-14 Fuel Quantity Gauge
Fuel System Capacities

Back 8

Red Line on Empty
Fuel Low light on at approx 12 gals.

Total fuel capacity 84.1 gal
Unusable fuel is -1.5 gal
Useable fuel is 82.6 gal

Front 9

System Limits
5-9 Airspeed Indicator

*NOTE

Back 9

0 to 130 knots continuous operation
130 knots maximum
100 knots maximum for autos
VNE for internal Gross Weights above 3,200 lbs is:
78 KIAS, not to exceed placarded VNE.
*NOTE: Autorotations above 100kts will result in high rates of descent & low rotor RPM.

Front 10

System Limits
5-10 Turbine Outlet Temp Gauge
Normal Oeprations

Back 10

100c to 738c continuous operations
738c to 810 Take-off PWR Range (5 min limit)
810c Maximum
810c to 843c (6 sec transient) not to be used intentionally.

Front 11

System Limitations
5-10 Turbine Outlet Temp Gauge
Startup/Shut-Down Operations

Back 11

927c Max during start/shut-down
(10 seconds maximum)

Front 12

System Limits
5-10 Turbine Outlet Temp Gauge

*NOTE

Back 12

*NOTE: Red Warning lgt illuminates when either of the following conditions are exceeded:
810-927c for 10 seconds or higher than 927c.

Front 13

System Limits
5-11 Gas Producer Gauge

Back 13

60% to 105% Continuous operations
105% Maximum
105% to 106% Transient
(15 seconds Maximum)

Front 14

System Limits
5-12 Dual Tachometer
Power Turbine Indicator

Back 14

97% Minimum Operation
97% to 100% Continuous operations
100% Maximum
N2 75% to 88%
60 sec Maximum (time not cumulative)

Front 15

System Limits
5-12 Dual Tachometer
Rotor Indicator

Back 15

90% minimum operations
50 to 60% accelerate through this range
90-107% Normal Operation
107% Maximum
Power on Transient Rotor Droop limit is 95% (5 seconds maximum)

Front 16

System Limits
5-13 Torque Meter

Back 16

0 to 85% continuous operation
>85 to 100% Take off power range
(5 minute limit)
100% Maximum
Transient TQ limit is: 100% to 110%
(5 seconds Maximum)
Intentional Use is Prohibited

Front 17

Mics Limits
5-21 Wind Limitations
Start up/Shutdown/Hover

Back 17

Start Up-
Max 45kts or 15kts gust spread
Hover (<3200lbs)
Max 35 crosswind/ Max 30kts Tail wind
Hover (>3200lbs)
IGE refer to Chp. 8/ OGE calm winds only

Front 18

Mics Limits
5-21 Wind Limitations
Control Movements Caution (Right Crosswind)

Back 18

1) Caution: For gross weights greater than 3000lbs and density altitudes greater than Sea Level, directional margin may be significantly reduced while hovering with winds from the right greater than (20kts) or for right sideward flight at speeds greater than (20kts).
2. Limitation: Abrupt control movements, including rapid & repetitive T/R reversals are prohibited to avoid excessive stresses in the structure. This restriction does not limit normal control inputs.

Front 19

Misc Limits
5-24
Engine Anti-Ice limits

Back 19

Anti-Ice shall not be used in ambient temp above 4c.
Anti-Ice shall be ON for flights in visible moisture and temp at or below 4c.

Front 20

Misc Limits
5-26 Engine Starter Limits
No-rise in TOT first 20 sec

Back 20

External Power Battery Power
25s on/30s off 40s on/60s off
25s on/30s off 40s on/60s off
25s on/30min off 40s on/40min off

Front 21

Misc Limits
5-26 Engine Starter Limits
Yes-rise in TOT first 20 sec

Back 21

External/Battery Power
1 min on/ 1 min off
1 min on/ 1 min off
1 min on/ 30 min off

Front 22

Mics Limits
5-27 Engine Starting Limitations

Back 22

During starting if the N1 does not reach 58% in a total time of 45 seconds (or 60 seconds below 10c FAT), close throttle & press starter button until TOT is below 200c. If engine fails to start on THIRD attempt abort start & make an entry on DA Form 2408-13-1
Engine Starter Limits do not apply to Engine Starting Limits should abort start procedures become necessary.

Front 23

Load Limits
5-32 Center Of Gravity Limitations

Back 23

Maintain the aircraft within limits in the center of gravity limitation chart in Chpt 6 and below.

Front 24

Load Limits
5-23 Longitudinal Center of Gravity Limits

Back 24

VMC Center of Gravity Limits are from station 106.0 to 114.2
Aft Limits are variable depending upon gross weight
Refer to Chp 6 (Center of Gravity Limits Chart)

Front 25

Load Limits
5-23 Lateral Center of Gravity Limits

Back 25

3.0 inches left/ 4.0 inches right of helicopter center line.
Lateral CG limits vary depending on the longitudinal CG location and Wt.
Refer to Chp 6. (Lateral vs Longitudinal CG limits chart.

Front 26

Load Limits
5-35 Weight Limitations

Back 26

Max allowable Gross Weight for Ramp/Hover/Flight is 3350lbs. Min front seat weight is 170lbs.

Front 27

Airspeed Limits
5-36 VMC Airspeed Limits

Back 27

At 3000lbs & below G/W: 130 kts at SL to 3000ft. the decreasing 3.5kts per/1000ft above 3000ft to a Max Alt of 20,000 Density Alt.
Above 3000 to 3200lbs G/W: 122 kts at SL to 3000ft, then decreasing 7.0kts per/1000ft above 3000ft to a Max alt of 13,500 Density Alt.
Above 3200bl G/W: 78kts VNE for G/W >3200lbs, not to exceed placard VNE.

Front 28

Airspeed Limits
5-38 Airspeed Restrictions for High Power Settings

Back 28

VNE 80 kts with >85% to 100% Torque applied

Front 29

Maneuvering
5-40 Aerobatic Maneuvers

Back 29

Aerobatic maneuvers are prohibited. Aerobatic flight is defined as any intentional maneuver involving an abrupt change in aircraft attitude with pitch angles >30 degress, roll angles >60 degrees or abnormal acceleration not needed for normal flight.

Front 30

Operating and Flight Characteristics
8-28 N2 Drrop

Back 30

A decrease in N2 RPM that exists between the time a demand for power is made (L-Pedal/Collective) and the time the power is delivered.
Considered Normal flight characteristic if:
1. N2 recovers to 100% w/in 5 sec
2. Low Rotor RPM light and audio is not activated
3. Further droop is not experienced for that PWR application.

Front 31

Operating and Flight Characteristics
8-32 Loss of Tailrotor Effectiveness
Definitition

Back 31

LTE is the occurrence of an uncommanded and rapid right yaw rate which does not subside of its own accord and if not quickly reacted to, can result in loss of aircraft control.

Front 32

Operating and Flight Characteristics
8-32 Loss of Tailrotor Effectiveness
Contributing Factors

Back 32

Increase in Gross Wt and DA
Low Indicated A/S
Power Droop

Front 33

Operating and Flight Characteristics
8-32 Loss of Tailrotor Effectiveness
When can LTE occur

Back 33

Can oly happen at or belwo ETL when the wind azimuths are between 120 and 330 degrees affecting the T/R.

Front 34

Operating and Flight Characteristics
8-32 Loss of Tailrotor Effectiveness
Prevention
*NOTE

Back 34

If Pilot is at low A/S in flight conditions listed above.
*NOTE: Pilot must anticipate these variations and concentrate on flying the aircraft and not allow a yaw rate to build.

Front 35

Emergency Procedures
Warning

Back 35

An operating procedure, practice, etc... which, if not correctly followed, could result in personal injury or loss of life.

Front 36

Emergency Procedures
Caution

Back 36

An operating procedure, practice, etc..., which, if not strictly observed, could result in damage to or destruction of equipment.

Front 37

Emergency Procedures
Note

Back 37

An operating procedure, condition, etc...., which is essential to highlight.

Front 38

Emergency Procedures
Land as soon as possible

Back 38

Land without delay to the nearest suitable area (ie open field) in which a safe approach and landing is reasonably assured. The Primary Consideration is the ensure the survival of the occupants.

Front 39

Emergency Procedures
Land as soon as practicable

Back 39

The landing site and duration of the flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended. The Primary Consideration is the urgency of the emergency.

Front 40

Emergency Procedures
Autorotate

Back 40

Adjusting the flight controls as necessary to establish an autorotational descent and landing.
Collective- Adjust as required to maintain rotor RPM (90-107%)
Pedals- Adjust Crab or Slip as required.
Throttle- Adjust as necessary. Close as required.
Airspeed- Adjust as required.

Front 41

Emergency Procedures
Emergency Shutdown

Back 41

Engine shutdown with out delay.

Throttle- Close
Fuel Valve Switch- Off
Batt Switch- Off as desired.

Front 42

Emergency Procedures
Emergency Shutdown
Three considerations

Back 42

Three considerations before turning the battery switch off:
Mayday Call, selecting emergency on the transponder, and the possible effects of total electrical failure.

Front 43

Emergency Procedures
Engine Malfunctions
WARNING

Back 43

WARNING: Do not respond to the RPM Warning System by entering Autorotation and reducing throttle without first confirming engine malfunction by one or more indications. Normal indications signify that the engine is functioning properly and that there is a tachometer generator failure or an open circuit to the warning system, rather than an actual engine malfunction.

Front 44

Emergency Procedures
Engine Failure Indications

Back 44

Left Yaw
Decrease in Rotor RPM
Decrease in Eng RPM
Change in Engine Noise
Low rotor Lft & audio (steady tone)
Engine out lgt & audio (warbling)

Front 45

Emergency Procedures
9-8 Engine Failure- Hover

Back 45

Autorotate
Emer Shutdown- accomplish after landing.

If at or below 15 feet AGL, it is recommended to maintain the collective setting until just prior to ground contact, then incrase collective as required to cushion landing.

Front 46

Emergency Procedures
9-9 Engine Failure- Low Alt/Airspeed/Cruise

Back 46

Autorotate
Emer Shutdown- Accomplish during descent if time permits.