Anytime an operating limitation is exceeded, an appropriate entry shall be made in helicopter logbook. Entry shall state which limit was exceeded, duration of time, extreme value attained, and any additional info.

Intentional use of transient limits is prohibited.

Landings and torque events (takeoffs) shall be recorded.

General

Continued

Minimum flight crew consists of one pilot who shall operate the helicopter from the right crew seat. Min pilot weight is 170 LBS

A functional map light is required for night flights.

Certified for land operation under day or night VFR non-icing conditions

AIRSPEEDS

0 TO 130 KIAS CONT OPS

Best Rate of Climb (Vy): 57KIAS

Min Rate of Descent: 52 KIAS

Max Glide Distance: 69

84 KIAS TORQUE between 75 and 100% (takeoff PWR)

100 KIAS MAX FOR AUTOROTATION

130 KIAS MAX Vne sea level to 3000FT DA

NEVER exceed the placarded Vne

PROHIBITED MANEUVERS

Aerobatic maneuvers

FAR 91.303

An intentional maneuver involving an abrupt change in an aircrafts attitude, an abnormal attitude, or abnormal acceleration, not necessary for normal flight

AMBIENT TEMPS

Min Temp is -50C at all ALTs

Max Temps are +51.7C at sea level and decrease with Hp (PA) at standard lapse rate of 2C per 1000 FT PA to 20,000 FT PA.

ENG ANTI ICE shall be on in visible moisture when the OAT is below 5C. MAX ambient temp for ANTI-ICE is 5C.

GENERATOR

0-90% Cont. Ops (0-180 AMPS)

90% Max (180 AMPS)

STARTER LIMITS

(EXTERNAL PWR)

NOTE

EXTERNAL PWR START

40 SEC ON

30 SEC OFF

40 SEC ON

30 SEC OFF

40 SEC ON

30 MINS OFF

NOTE

28 VDC GPU starting shall be limited to 500 amps due to risk of starter damage from overheating

STARTER LIMITS

(BATTERY START)

BATTERY START

60 SEC ON

60 SEC OFF

60 SEC ON

60 SEC OFF

60 SEC ON

30 MINS OFF

24V 28 AMP battery

POWER PLANT

Rolls Royce model 250-C30P

650 SHP derated to 490 SHP for 5min takeoff power and 370 SHP for CONT OPS (L4 75%)

NG

63 to 105% Cont OPS

105% MAX Cont OPS

106% 10 sec transient

NP POWER TURBINE

NP

71.8 TO 91.5% AVOID CONT OPS

99% MINIMUM

99 TO 101% CONT OPS

101% MAX CONT

104% 5 MIN TRANSIENT

TURBINE OUTLET TEMPERATURE

CONT OPS

100 TO 716C CONT OPS

716C MAX CONT

716 TO 768C TAKEOFF, 5 MIN

768C MAX FOR TAKEOFF

871C 10 SEC TRANSIENT

STARTING OPS

826C TRANSIENT, 10 SEC

927C MAX STARTING

do not exceed 10 sec above 826C or 1 sec at 927C

ENGINE TORQUE

NOTE

ENGINE TORQUE

0-75% CONT OPERATION

75% MAX CONT

75 TO 100% TAKEOFF, 5 MIN

100% MAX TAKEOFF

105% TRANSIENT, 5 SEC

NOTE

Use of takeoff power is limited to 84KIAS, not to exceed placarded Vne.

FUEL PRESSURE

8 PSI MIN

8-25 PSI CONT OPS

25 PSI MAX

ENGINE OIL PRESSURE

ENG OIL PRESSURE

50 PSI MIN BELOW 79% NG

90 PSI MIN FROM 79 TO 94% NG

115 PSI MIN ABOVE 94% NG

130 PSI MAX

ENGINE OIL TEMP

0 TO 107C CONT OPS

107C MAX

XSMN OIL PRESSURE

30 PSI MIN

40-70 PSI CONT

70 PSI MAX

XSMN OIL TEMP

15-110C CONT

110C MAX

The engine limitations consists of torque (ENG TRQ%), turbine outlet temperature (TOT), and RPM (NG and NP)

NR ROTOR (PWR ON)

NR ROTOR

POWER ON

95% 5 SEC TRANSIENT

99% MIN

99 to 101% CONT OPS

101% MAX CONT

104% 5 MIN TRANSIENT

NR ROTOR (PWR OFF)

NR ROTOR

POWER OFF

90% MIN

90 to 107% CONT OPS

107% MAX

FUEL

50-75 LBS/10gals LOW FUEL

APPROVED FUELS: JET A, JET A-1, JET B, JP-4, JP-5, JP-8

Total: 112 gals

Useable: 110.7 gals

Unusable: 1.3 gals

ROTOR BRAKE

Use is approved after engine shutdown and NR is between 38%-30%

Engine starts with rotor brake engaged are prohibited

DO NOT stop the rotors at the 12 and 6 o'clock postitions due to heat from the exhaust

SLOPES

Nose Down-5 degrees

Left, Right, Nose Up-10 Degrees

MAX GROSS WEIGHT

BAGGAGE COMPARTMENT LIMIT

MAX GROSS WEIGHT

4450LBS 

BAGGAGE COMPARTMENT LIMIT

250 LBS

86 LBS per SQFT

75 LBS per SQFT Cabin

TAILBOOM

VERTICAL FIN

ENDPLATES (dynamic dihedrals)

LEADING EDGE SLATS

VERTICAL FIN

5.5 Degrees Right

Provides directional (yaw) stability

Reduces the required amount of tail rotor thrust

ENDPLATES (dynamic dihedrals)

 Provides dutch roll stability

Off set 5 degrees left to vane into rotor wash

LEADING EDGE SLATS

Improves pitch stability in high power climbs

FAIL SAFE SYSTEMS

Engine Anti-Ice

Hydraulic System

Particle Separator Purge

COMPONENTS DRIVEN BY Ng

Compressor

N1 Tach/Generator

Starter/Generator

Fuel Pump Assembly

N1 Fuel Control

Oil Pump Assembly

COMPONENTS DRIVEN BY Np

N2 Tach/Generator

N2 Governor

Torquemeter

Freewheeling Unit

POWER ASSURANCE CHECK

Bleed Air off (Heater and Anti-Ice)- Off

Level FLT

85-105 KIAS or Vne, whichever is lower

OR

At a Hover

COMBUSTION SECTION

Approx. 20%-25% of air delivered to this section required to burn the fuel. The other 75% to 80% is used to cool the liner and center the flame. 2% is used to seal oil passages.

MISC

M/R Blades: Max load applied to blade tips: 90lbs/34in, semi-rigid, seesaw, -11 degree twist, 37ft diameter, swept tips, 13 in chord line

T/R Blades: 4 degree twist, 5ft 5in

MAX END: 60KIAS

TRANS Tilted: 5 degrees FWD

Triple Stack: Trans oil pump, Rotor Tach, and Hydr pump

The corrective action procedures listed in Section 3 “Emergency/Malfunction Procedures” assume the pilot gives first priority to what?

The corrective action procedures listed in Section 3 “Emergency/Malfunction Procedures” assume the pilot gives first priority to what?

All corrective action procedures assume pilot gives first priority to helicopter control and a safe flight path.

AUTOROTATE

The term autorotate is defined as adjusting the flight controls as necessary to establish an auto-rotational descent and landing.

MINIMUM RATE OF DESCENT

MAXIMUM GLIDE DISTANCE

NOMINAL AUTOROTATIVE SPEED

MINIMUM RATE OF DESCENT

52 KIAS

MAXIMUM GLIDE DISTANCE

69 KIAS

NOMINAL AUTOROTATIVE SPEED

Airspeed between the 2 airspeeds is 61 KIAS

ENGINE FIRE ON GROUND

Throttle-Closed

Fuel Valve Switch-Off

Battery-Off

Rotor Brake-Pull

Exit Aircraft

ENGINE MALFUNCTION-

PARTIAL OR COMPLETE POWER LOSS

INDICATIONS

Left yaw

drop in ENG RPM (NP) and (NG)

Low rotor RPM

Low rotor warning light and audio (below 90% +-3%)

ENG out light (55+-3%)

ENG out audio

Change in eng noise

ENGINE FAILURE-HOVER

NOTE

1. Maintain heading and attitude control

2. Collective – Adjust to control NR and rate of descent. Increase prior to ground contact to cushion landing.

3. Shut down helicopter

NOTE

FWD A/S will aid in the ability to cushion landing

1. Autorotate

2. Attempt engine restart

3. Throttle - Closed

4. Fuel Valve Switch - Off

5. Accomplish Autorotation and Landing

6. Complete helicopter shutdown

ENGINE COMPRESSOR STALL

1 of 2

Indications:

Engine Pops

High or erratic TOT

Decreasing or erractic Ng or Np

Torque oscillations

1. Collective – Reduce power, maintain slow cruise flight.

2. TOT and Ng – Check for normal indications.

3. ENG ANTI ICE switch – ON.

4. PART SEP switch (if installed) – ON.

5. HEATER switch (if installed) – ON

ENGINE COMPRESSOR STALL

2 of 2

If pilot elects to continue flight:

6. Collective – Increase slowly to achieve desired power level.

7. TOT and N1 – Monitor for normal response.

8. Land as soon as practical.

If pilot elects to shut down engine:

9. Enter autorotation.

10. Throttle – Closed.

11. FUEL VALVE switch – OFF.

12. Accomplish autorotative descent and landing

 ENGINE OVERSPEED

(No caution/warning/advisory lights illuminated)

Increase in NR, NP, NG,TOT, and a right yaw

1. Throttle – Retard

2. NG or NP – Attempt to stabilize with throttle and collective

3. TOT - Monitor

4. NR - Maintain 90-107% with throttle and collective

If unable to maintain Nr, Np, Ng, TOT

5. Enter Autorotation

6. Throttle - Closed

7. Fuel Valve Switch - Off

8. Accomplish Autorotation and Landing

ENGINE UNDERSPEED

(No caution/warning/advisory lights illuminated)

Indications: Decrease in NG, NP, TRQ, a possible decrease in NR, and a left yaw

1. Collective – Adjust as required to maintain 90 to 107% NR

2. Throttle – Confirm full open

3. If unable to maintain Nr, establish autorotative descent

4. Prepare for power-off landing

ENGINE HOT START/SHUTDOWN

ENGINE HOT START/SHUTDOWN

1. Throttle – Closed

2. FUEL VALVE switch – OFF

3. STARTER switch – Ensure starter is motoring engine until TOT stabilizes at normal temperature

4. Shut down helicopter

ENGINE OIL PRESSURE LOW, HIGH, OR FLUCTUATING

Indications:

ENG oil pressure below minimum

ENG oil pressure fluctuating abnormally

1. Engine oil pressure and temperature – Monitor.

2. Land as soon as possible.

ENG oil pressure above max or fluctuating abnormally

1. Engine oil pressure and Temperature - Monitor.

2. Land as soon as practical.

ENGINE OIL TEMPERATURE HIGH

Indications:

Eng oil temp increasing above normal

Eng oil temp above maximum

1. Land as soon as practical.

DRIVESHAFT FAILURE

NOTE

DRIVESHAFT FAILURE

Left yaw, decrease in NR, increase in NP, low rotor audio and light

1. Autorotative descent and landing

NOTE

To maintain tail rotor effectivness don't shutdown engine in FLT

2. Complete helicopter shutdown (EMER SHUTDOWN) after landing

ENGINE FIRE DURING FLIGHT

1. In-flight – Immediately enter autorotation

2. Throttle – Closed

3. FUEL VALVE switch – OFF

4. If time permits, L/R FUEL BOOST circuit breaker switches – OUT

5. Execute autorotative descent and landing

6. BATT switch – OFF

 CABIN SMOKE OR FUMES

1. In-flight – Start descent

2. HEATER switch (if installed) – OFF

3. All vents – Open

4. Side windows – Open

If time and altitude permits:

5. Source – Attempt to identify and secure

6. If source is identified and smoke and/or fumes still persist – Land as soon as possible

7. If source is identified and smoke and/or fumes are cleared – Land as soon as practical

CLUTCH FAILS TO DISENGAGE

Rotor RPM will decay with the engine RPM as the throttle is reduced when entering an autorotation. This will result in a total loss of autorotational capability.

1. Throttle - Open

2. Land as soon as Possible

CLUTCH FAILS TO RE-ENGAGE

During recovery from an autorotation will be indicated by a decrease in NR as NP remains constant.

1. Autorotate

2. Emergency Shutdown

LOSS OF HYDRAULIC PRESSURE

1 of 2

LOSS OF HYDRAULIC PRESSURE

Indications:

Hydraulic System caution light on

Grinding noise from pump

Increased force required to move flight controls

Feedback may be evident during FLT control movement

Do not confuse HYD failure (all controls) with a FLT control failure (1 control). Leave HYD system switch off for duration of FLT. Don't exceed 45 degrees of bank.

LOSS OF HYDRAULIC PRESSURE

2 of 2

LOSS OF HYDRAULIC PRESSURE

1. Reduce AIRSPEED to 60 – 80 KIAS

2. HYD SYSTEM circuit breaker – Out. If hydraulic power is not restored, push breaker in.

3. HYD SYS switch – HYD SYS OFF if hydraulic power is not restored.

4. Land as soon as practical.

5. A run-on landing at approx. 9 KIAS or effective translational lift speed (approximately 15 knots) is recommended.

FLIGHT CONTROL ACTUATOR MALFUNCTION

Indications:

Uncommanded FLT control movements

High FLT control forces to oppose the movement

Feedback only affect FLT control axis

FLT control forces normal in unaffected axis

1.  Attitude – Maintain

2.  HYD SYS switch – OFF

3.  AIRSPEED – Set to 60 to 80 KIAS

4.  Land as soon as possible as if hydraulics

GENERATOR FAILURE

NOTE

GENERATOR FAILURE

Gen Fail Light, DC Loadmeter indicates 0%

1. GENERATOR FIELD and GENERATOR RESET circuit breakers – Check in

2. GEN Switch – RESET; then GEN

3. If power is not restored, place GEN switch to OFF

4.  land as soon as practical

NOTE

With generator off, a 80% charged battery will operate left fuel boost pump for approx. 3hrs. For night ops, approx. 1hr

EXCESSIVE ELECTRICAL LOAD

 WARNING

EXCESSIVE ELECTRICAL LOAD

WARNING

Prior to Batt depletion, altitude shall be reduce below 6000 FT PA

Indications:

DC load excessive load

Smoke or fumes

1. GEN switch – OFF.

2. BATT switch – OFF.

3. Left Fuel Boost CB - Check in

FUEL TRANSFER FAILURE

Indication: At total FUEL QTY of approx. 86.3lbs and below, Fuel QTY in FWD cells remain constant

1. Determine FUEL QTY in forward cell

2. Subtract quantity of fuel trapped in forward cell from total to determine usable fuel remaining.

3. Plan landing accordingly

LITTER DOOR OPEN

BAGGAGE DOOR

LITTER DOOR OPEN

BAGGAGE DOOR

Close door securely before FLT

If light illuminates during FLT, land as soon as practical.

ROTOR LOW RPM

Audio comes on below 90%(+/-3%) NR

Reduce collective

Ensure throttle is full open

XMSN OIL PRESS CAUTION LIGHT ILLUMINATED

Transmission oil pressure (30 psi +-2 psi) is below minimum. Extinguishes at 36 psi

Reduce power

Verify fault with gage

Land as soon as possible

XMSN OIL TEMP CAUTION LIGHT ILLUMINATED

Transmission oil temp is at or above red line (At or above 110C +-5.5C).

Reduce PWR

Verify fault with gage

Land as soon as Possible

ENGINE, T/R, or XMSN CHIP caution light illuminates in flight

Land as soon as possible

FUEL FILTER

Airframe fuel filter in impending bypass

Land as soon as practical

Clean filter before next FLT

R or L FUEL PUMP

Boost pump assembly has failed

Descend below 6000FT Hp (PA)

LAND AS SOON AS PRACTICAL

If both pump assemblies have failed

Land as soon as POSSIBLE

FUEL LOW

WARNING

FUEL LOW

Approximately 50-75 lbs (10 gals) remaining 

Verify Fuel QTY

LAND AS SOON AS PRACTICAL

WARNING

Avoid uncoordinated flight as fuel starvation may occur

A ir Worthiness

R egistration

R FM

O perations Manual (GOM)

W eight and balance

B riefing cards (7)

A FD

M EL

M aintenance Log

F lashlight (115 lumens)

F ire Extinguisher

P ubs

LANDING IN TREES

1. Select a landing area containing the least number of trees of minimum height

2. Decelerate to minimum forward speed to treetop level and descend vertically

3. Apply all remaining collective prior to main rotor contacting the trees

DITCHING-PWR ON

1. Doors-Open at a hvr

2. Passengers-Exit

3. HVR a safe distance away

4. Autorotate. 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

5. Pilot- Exits when the M/R stops

DITCHING - PWR OFF

1. Autorotate-Decelerate to MIN FWD A/S as the 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 direction of roll.

2. Doors - Open as the helicopter enters the water.

3. Pilot and passengers - Exit when the main rotor stops.

LIGHTNING STRIKE

&

IN-FLIGHT WIRE STRIKE

LIGHTNING STRIKE

&

IN-FLIGHT WIRE STRIKE

Land as soon as Possible