205a1-fm-01-s05.pdf

IfsFAA APPROVED 205A-1 FLIGHT MANUAL Section 5October 18, 1968 SN 30001 THRU 30052

BHT-205A 1-FM-1

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ENGINE OPERATION CHECK CHART

A Maximum Power Check chart is provided to aid the pilot in determining enginecondition based on the relation of altitude/temperature and maximum power(maximum torquemeter pressure).

If this check is satisfactory, published Flight Manual performance can be equalled orbettered depending on how much the installed engine is better than the theoretical"specification engine" on which the published performance is based. Check caneasily be made by using normal cockpit instruments, and the methods describedherein.

Pages 5-2 - 5-5 deleted.

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Section 5 205A-1 FLIGHT MANUAL FAA APPROVEDSN 30001 THRU 30052 October 18, 1968

BHT-205A1-FM-1' MAXIMUM POWER (TORQUEMETER PRESSURE) CHECK

The purpose of this check is to determine whether or not theinstalled engine will deliver torquemeter pressure (power) equalto or greater than a minimum specification engine. Since theminimum specification engine is capable of delivering 1400 horse-power, and the engine as installed in the helicopter is deratedto 1250 horsepower, care must be taken not to exceed the powerlimitation (54.0 PSI torquemeter pressure). This "full throttle"power check, in order to be conclusive, must be made at conditionsof altitude and temperature at which full throttle will produceno more than 54.0 PSI torquemeter pressure. This check shouldbe accomplished in the following manner:

Initiate a climb at best climb speed and 100 percent NII.

Maintain climb and increase collective (not to exceed 54 PSIof torque) until the NII speed drops to 98 percent with thegovernor RPM switch "beeped" to full increase.

Note

Do not exceed 54 PSI torque at anytime.

Read and record the following:

Pressure altitude

Example

4000 ft

Ambient air temperature (OAT) 30°C

Torquemeter pressure 44.5 PSI

Gas producer speed (NI) 96.60/0

1 Enter chart at pressure altitude (Point A), proceed horizontally to ambient airtemperature (Point B), and then proceed vertically down and read charttorquemeter pressure (Point Q. Example: 43.1 PSI

Since the observed maximum torquemeter pressure of theexample (44.5 PSI) is no less than the chart maximum torque-meter pressure (43.1 PSI) the maximum torquemeter pressureavailable is satisfactory.

5-6 Rev. 11

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FAA APPROVED 205A-1 FLIGHT MANUALOctober 18, 1968 SN 30001 THRU 30052

Section 5

BHT-205A1-FM-1MAXIMUM POWER (TORQUEMETER PRESSURE) CHECK (Cont)

The recorded NI RPM shall be plus or minus 0.5 percent of theplacarded Maximum Gas Producer Speed for Takeoff Power. (Thisis NI topping.)

If this check is satisfactory, it can be concluded that the installedengine is at least as good as a minimum specification engine andthat full power can be obtained. If this check is not satisfactory,there is reason to believe that the engine has deteriorated I theextent that published performance may not be obtained. If thisoccurs, the cause of the deterioration should be determined.

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Rev. May 1, 1974 5-9

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Section 5

BHT-205A1-FM-1

205A-1 FLIGHT MANUAL FAA APPROVED,16 October 18, 1968

HOVERING CEILINGIN GROUND EFFECT

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FAA APPROVED 205A-1 FLIGHT MANUALOctober 18, 1968

Section 5

BHT-205A1-FM-1

HOVERING CEILINGIN-GROUND EFFECT

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Rev. May 1, 1974 5-11

Section 5 205A-1 FLIGHT MANUAL FAA APPROVED

BHT-205A1-FM-1

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October 18, 1968

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5-12 Rev. May 1, 1974


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5-14 Rev. May 1, 1974


Section 5

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Section 5 205A-1 FLIGHT MANUAL FAA APPROVEDSN 30001 THRU 30052

BHT-205A1-FM-1

TAKE-OFF DISTANCEOVER 50 FOOT OBSTACLE

TAKE-OFF POWER

GROSS WEIGHT 6500 LBS.

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October 18, 1968

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5-16 Rev. May 1, 1974


Section 5

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Rev. May 1, 1974 5-17


BHT-205A1-FM-1

October 18, 1968

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5-18 Rev. May 1, 1974

FAA APPROVED 205A-1 FLIGHT MANUAL Section 5October 18, 1968 SN 30001 THRU 30052

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5-20 Rev. May 1, 1974

FAA APPROVED Section 5205A-1 FLIGHT MANUALOctober 18, 1968

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Section 5

BHT-205A1-FM-1


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5-26 Rev. May 1, 1974


Section 5

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Rev. May 1, 1974 5-35

Section 205A-1 FLIGHT MANUAL FAA APPROVEDSN 30001 THRU 30052


POWER-OFF

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GROSS WEIGHT 8500 LBS. VCAL 60 KNOTS

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TAKE-OFF POWER


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Rev. May 1, 1974 5-37

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5-38 Rev. May 1, 1974

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BHT-205A1-FM-1

OPERATION VS ALLOWABLE WIND

Helicopter flight operations with wind from a direct forwardquarter are limited only by pilot proficiency; however, turbulentand variable wind conditions should a l s o be considered as alimiting factor in flight operations. Operations in crosswind anddownwind conditions have been demonstrated up to 20 knots (23MPH) but should not be considered as a limiting value since themaximum operating wind velocities for these conditions havenot been established.

AIRSPEED INSTALLATION CORRECTIONCHARTS- PILOT'S AND COPILOT'SSYSTEMS

Indicated Airspeed (IAS) corrected for position and instrumenterror equals Calibrated Airspeed (CAS). Determine correctedairspeed from the following charts:

5-44 Rev. May 1, 1974

CA

LIB

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Section 5

BHT-205A1-FM-1

PILOT'S AIRSPEEDSYSTEM CALIBRATION

CRUISECLIMB

AUTOROTATION

SKID GEAR

140

120

100

80

60

40

20

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IAS - ERROR = VCAL

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I.A.S. - KNOTS

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Rev. May 1, 1974 5-45

CALIBRATED AIRSPEED

KNOTS


BHT-205A1-FM-1

CO-PILOT'S AIRSPEEDSYSTEM CALIBRATION

CRUISECLIMB

AUTOROTATION

SKID GEAR

140

120

October 18, 1968

IAS - ERROR = VCAL

CLIMB

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20

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I.A.S. - KNOTS

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5-46 Rev, May 1, 1974

09

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896T FAA APPROVED 205A-1 FLIGHT MANUALOctober 18, 1968 30001 30052

Section

GLIDE DISTANCENAUTICAL MILES HEIGHT ABOVE GROUND

POWER-OFFROTOR RPM 100%

ALL GROSS WEIGHTS VCAL 60 KNOTS

'OAT

3 5

GLIDE DISTANCE- NAUTICAL MILES

Rev. May 1974 5-47/5-48

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205a1-fm-01-s05.pdf

Documents

psi torquemeter pressure

ctorquemeter pressure

pressure altitude point

check shouldbe

throttlepower check

theinstalled engine

takeoff power

flight manual performance