Bell 407 Limitations

Front 1

TYPES OF OPERATION
PASSENGERS

Back 1

Basic configured helicopter is approved for
seven place seating and is certified for land operation under day or night VFR non-icing
conditions.

Front 2

CARGO LIMITS

Back 2

The maximum allowable cabin deck loading for cargo is 75 pounds per square foot (3.7 kg per 100 cm2). The maximum allowable
baggage compartment deck loading is 86 pounds per square foot (4.2 kg per 100 cm2) with a maximum allowable weight of
250 pounds (113.4 kg). Refer to BHT-407-MD-2 for cargo restraint and tie-down locations.

Front 3

FLIGHT CREW

Back 3

Minimum flight crew consists of one pilot who shall operate helicopter from right crew seat.
Left crew seat may be used for an additional pilot when approved dual controls are installed.

Front 4

REQUIRED EQUIPMENT

Back 4

An operative headset is required for each pilot.
A functional flashlight is required for night flights.

Front 5

1-5-C. DOORS REMOVED

Back 5

Indicated altitude may be up to 100 feet lower than actual altitude with crew door(s) removed.
Flight with any combination of doors removed is approved. With litter door removed, left passenger door shall be removed. Refer to airspeed limitations.
With door(s) removed, determine weight change and adjust ballast if necessary. Refer to Section 5

Front 6

1-6-A. WEIGHT

Back 6

Maximum approved internal GW for takeoff and landing is 5250 pounds( FMS 28).

Minimum GW for flight is 2650 pounds.

Maximum external 6000 pounds.

Front 7

1-7. AIRSPEED- VNE's

Back 7

Basic VNE 140KT up to 3000FT HD
then use VNE table.

VNE at 93.5 to 100% torque (takeoff power) is 100 KIAS, not to exceed placarded VNE.

VNE is 100 KIAS or placarded VNE, whichever is less, when takeoff loading is in shaded area of the Gross Weight Lateral Center of Gravity Limits (Figure 1-2).

VNE is 100 KIAS with any door(s) removed, not to exceed placarded VNE.

VNE is 100 KIAS or placarded VNE, whichever is less for steady state autorotation.

Front 8

1-9-C. SLOPE LANDING

Back 8

Slope landings are limited to 10° side slopes, 10° nose up slope, or 5° nose down slope

Front 9

1-11. AMBIENT TEMPERATURES

Back 9

Maximum sea level ambient air temperature for operation is 51.7°C (125°F) and decreases with HP at standard lapse rate of 2°C (3.6°F) per 1000 feet. Refer to Ambient Air Temperature Limitations chart (Figure 1-4).
Minimum ambient air temperature for operation at all altitudes is -40°C (-40°F).

Front 10

1-12-A. GENERATOR

Back 10

1-12. ELECTRICAL
1-12-A. GENERATOR
Continuous operation, up to 10,000 feet Hp: 0 to 180 amps

Maximum continuous up to 10,000 feet Hp: 180 amps

Continuous operation, above 10,000 feet Hp 0 to 170 amps

Maximum continuous above 10,000 feet Hp.: 170 amps

Transient, 2 minutes180 to 300 amps
Transient, 5 seconds300 to 400 amps

Front 11

1-13. POWER PLANT

Back 11

Rolls-Royce model 250-C47B.

674 HP at 100% Tq

630 HP at 93.5% Tq

Front 12

1-13-A. GAS PRODUCER RPM (NG)

NOTE
FADEC will limit NG when operating above 10,000 feet HP and with OAT below -30°C (-22°F). NR decay will result if power demand exceeds NG limit. Condition annunciated with NG OAT LIMIT message.

Back 12

Front 13

1-13-B. POWER TURBINE RPM (NP)

Back 13

Avoid continuous 68.4 to 87.1%
operations

Minimum 99%

Continuous operation 99 to 100%

Maximum continuous 100%

Maximum transient, 102.1 to 107.3% 15 seconds

NOTE
ENGINE OVSPD warning message
will illuminate when Np is greater
than 102.1% for 2.5 seconds or
107.3% immediately.

NOTE
When operating in MANUAL mode,
Np should be maintained between 95 and 100%.

Front 14

1-13-C. MEASURED GAS TEMPERATURE (MGT)

Back 14

Continuous operation 100 to 727° C

Maximum continuous 727° C

Takeoff, 5 minutes 727 to 779° C

Maximum for takeoff 779° C

Transient, 12 seconds 780 to 905° C

Maximum starting 927° C,
do not exceed 10 seconds above 843° C or 1 second at 927° C.

Front 15

1-13-D. ENGINE TORQUE

Back 15

Continuous operation 0 to 93.5%

Maximum continuous 93.5%

Takeoff, 5 minute 93.5 to 100%

Transient, 5 seconds 105%

NOTE
Use of takeoff power is limited to
100 KIAS, not to exceed placarded
VNE.

Front 16

1-13-E. FUEL PRESSURE

Back 16

Minimum 8 PSI

Continuous operation 8 to 25 PSI

Maximum 25 PSI

Front 17

1-13-F. ENGINE OIL PRESSURE

Back 17

Minimum below 79% NG 50 PSI

Minimum from 79 to 90 PSI
94% NG

Minimum above 94% NG 115 PSI

Maximum 130 PSI

Maximum cold starts only 200 PSI

NOTE

When 130 PSI is exceeded during
start, operate engine at idle until oil
pressure drops below 130 PSI.

Front 18

1-13-G. ENGINE OIL TEMPERATURE

Back 18

Continuous operation 0 to 107° C

Maximum 107° C

NOTE
If hovering with a tailwind greater
than 10 knots at OAT above 37.8° C
(100° F), closely monitor engine oil
temperature. The oil temperature
may be reduced by either turning into wind, reducing power, or transition to forward flight.

Front 19

1-14-A. TRANSMISSION OIL PRESSURE

Back 19

Minimum 30 PSI

Idle operation only 30 to 40 PSI

Continuous operation 40 to 70 PSI

Maximum 70 PSI

Front 20

1-14-B. TRANSMISSION OIL TEMPERATURE

Back 20

Continuous operation 15 to 110° C

Maximum 110° C

Front 21

1-15-A. ROTOR RPM-POWER ON

Back 21

Continuous operation 99 to 100%

Maximum continuous 100%

NOTE
When operating in MANUAL mode,
NR should be maintained between
95% and 100%.

Front 22

1-15-B. ROTOR RPM-POWER OFF

Back 22

Minimum 85%

Continuousoperation 85 to 107%

Maximum 107%

CAUTION

FOR AUTOROTATIVE TRAINING,
MAINTAIN STEADY STATE NR
ABOVE 90%.

Front 23

1-18. ROTOR BRAKE

Back 23

Rotor brake (if installed) application is limited to ground operation after engine has been shut down and NR has decreased to 40% or lower.

For emergency stops, apply rotor brake any time after engine is shut down.

Engine starts with rotor brake engaged are prohibited.