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TitleHughes 369 Pilots Manual
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Total Pages284
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Page 1

MD Helicopters, Inc.
ROTORCRAFT FLIGHT MANUAL

MD HELICOPTERS INC.

CSP−HE/HS−1

Rotorcraft Flight Manual

FOR

MDHI 500C (369HE and 369HS) HELICOPTERS
13 JULY 1998

NOTE
This manual has been reprinted and now contains

Revisions 1 through 10

Page 142

Performance Data
CSP−HE/HS−1 ROTORCRAFT FLIGHT MANUAL MD 500

(Models 369HE/HS/HM)

Revision 5
FAA Approved

5−12

Use of Chart:

The following example explains the correct use of the chart as in
Figure 5-6. To determine the maximum hover ceiling at 3.0 ft. skid height,
the pilot must know the gross weight and the outside air temperature.

Example:

Helicopter configuration:

Short landing gear
Standard engine air inlet
Engine bleed air devices OFF
250C-18 engine

Wanted: Maximum gross weight for hover at 3.0 feet skid height at
takeoff power

Known: Gross weight = 2190; Ambient Temperature = 25°C

Method: Select the appropriate chart (Figure 5-6 for this example). Enter
the chart at 25°C on the ambient temperature scale and move ver­
tically to 2190 LB (interpolation is required) and move directly to
the left to read 8000 PA as the maximum hover ceiling.

Page 143

Performance Data
CSP−HE/HS−1ROTORCRAFT FLIGHT MANUALMD 500

(Models 369HE/HS/HM)

FAA Approved

Revision 5 5−13

AMBIENT TEMPERATURE − DEGREES C

P
R

E
S

S
U

R
E

A
L
T

IT
U

D
E


F

E
E

T

20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

OAT °C

WT

−5 15 35

2 5 7

REDUCE WEIGHT CAPABILITIES LBS AS FOLLOWS

PRESSURE
ALT, FT

5000
10000
15000

CABIN ANTI−
ICE

204
160
130

BOTH

405
295
255

HEAT

162
125
105

20000 90 110 210

P
R

E
S

S
U

R
E

A
L
T

IT
U

D
E


M

E
T

E
R

S

F01−024

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-
ICE OFF, ELECTRIC LOAD 30 AMPERE, APPLICABLE
TO 369H8094 ENGINE AIR INLET SCREEN, 250-C18
ENGINE

REDUCE HOVER WEIGHT CAPABILITY
1. 33 LB WITH PARTICLE SEPARATOR
2. 33 LB WITH SCAVENGE AIR ON
3. 11 LB WITH ENGINE AIR INLET SCREEN 369H8086
4. 50 LB WITH MAIN ROTOR ABRASION TAPE
INSTALLED

6,000

5,000

4,000

3,000

2,000

1,000

0

SEAL LEVEL TO

INCREASE (OR DECREASE
WEIGHT CAPABILITY LBS
(ABOVE CRITICAL ALTITUDE)
PER 10 AMPERE REDUCTION
(OR INCREASE) IN
ELECTRICAL LOAD

GROSS WEIGHT ABOVE
2550 LB MUST BE EXTER­
NAL AND JETTISONABLE

NOTE: SOLID LINES REPRESENT HOVER CAPABILITY WITHIN THE LIMITATIONS OF 20 KNOT SIDE WIND. DASHED LINES ARE REPRESENTED FOR IN­
FORMATION ONLY AND REPRESENT PERFORMANCE CAPABILITY IN ZERO WIND CONDITIONS.

−30 −10 0 10 20 30 40−40 −20

Figure 5−6. Hover Ceiling vs Temperature, IGE, 3−Foot Skid Clearance,
Short Landing Gear, Takeoff Power

<<<< Allison 250−C18 >>>>

Page 283

CSP−HE/HS−1
Optional Equipment

369HM Configuration

ROTORCRAFT FLIGHT MANUALMD 500
(Models 369HE/HS/HM)

Revision 6 9−61

FAA Approved

PART IV
NORMAL PROCEDURES

F01−078

Figure 9−13. Type “T” Instrument Panel − Layout Typical

Page 284

Optional Equipment
369HM Configuration

ROTORCRAFT FLIGHT MANUAL MD 500
(Models 369HE/HS/HM)

CSP−HE/HS−1

Revision 69−62

FAA Approved

F01−079

CIRCUIT
BREAKER PANEL

PILOT'S
COLLECTIVE

ASH TRAY AND LIGHTER

SWITCH CONTROL PANEL

LIGHTS CONTROL PANEL

Figure 9−14. Electrical Controls Console − Layout Typical

CYCLIC TRIM

DWN

UP

L

R
CARGO HOOK
RELEASE

HOIST
GUILLOTINE

FLOATS
INFLATION

Figure 9−15. Cyclic Grip

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