Helicopter MD 500E. Flight Manual (1982-2011)

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

Overhead canopy

CHECK

Battery compartment vent

NO OBSTRUCTIONS

FUSELAGE - UNDERSIDE

Fuselage skin

CHECK

Fuel tank and other vents

NO OBSTRUCTIONS

Cargo Hook (if installed)

CHECK (REF.

SECTION IX)

Antennas

CHECK

INTERIOR

AFT COMPARTMENT

Impeller belt

CHECK

Fuel cell access doors

SECURED

Controls access door

SECURED

Loose equipment or cargo

SECURED

Seats, seat belts, and shoulder harness

CHECK

Compartment doors closed and latched

CHECK

NOTE: Refer to Paragraph 4-10 if planning doors off flight.

FORWARD COMPARTMENT

Battery compartment

CHECK

Fire extinguisher and first aid kit

CHECK

Loose equipment or cargo

CHECK

NOTE: Refer to Paragraph 4-10 if planning doors off flight.

Seats, seat belts, and shoulder harness

CHECK

Interior and exterior lights (all switches OFF after check)

CHECK

Compartment doors closed and latched

CHECK

FAA Approved

Revision 15

4-7

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

PREFLIGHT CHECKS

Perform these checks prior to subsequent flights of the same day.

^F Fluid levels

CHECK

^F Engine compartment - fluid leaks and

CHECK

bypass indicators

^F Air inlet screens/particle separator

CHECK

^F Fuel cap, access doors and panels

CHECK

^F Main rotor blades

CHECK

^F Tailboom and empennage

CHECK

^F Tail rotor rotor blades

CHECK

^F Cargo and loose equipment

CHECK

^F Crew and cabin doors

CHECK

FAA Approved

4-8

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

ENGINE OUT AUDIBLE

WARNING HORN

(SEE NOTE)

ENGINE OIL

TEMPERATURE

ALTIMETER

INDICATOR

AIRSPEED

INDICATOR

ENGINE OIL

PRESSURE

INDICATOR

VNE

FUEL

PLACARDS

QUANTITY

INDICATOR

AMMETER

CLOCK

DUAL TACHOMETER

TORQUE

INDICATOR

TURBINE OUTLET

TEMPERATURE

FUEL

PULL

VALVE

FOR

(TOT) INDICATOR

AIR

FRESH AIR

FUEL SHUTOFF

VENT

VALVE

TACHOMETER

KEY

SWITCH

EDGE LIGHTED SWITCH

PANEL: PRE AND LATE

GENERIC

EDGE LIGHTED CIRCUIT

BREAKER PANEL

EARLY GENERIC

ANTI-ICE

SWITCH

(250-C20R/2)

NOTE:

ON LATER MODEL 369E HELICOPTERS,

F03-014-1

ENGINE OUT AUDIBLE WARNING HORN

RELOCATED ADJACENT TO PILOT’S

UTILITY LIGHT ON MAP CASE PANEL

Figure 4-2. Instrument Panel, LH Command - Layout Typical

FAA Approved

Revision 13

4-9

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

TORQUE

INDICATOR

ENGINE OIL

AIRSPEED

TEMPERATURE

ALTIMETER

INDICATOR

ENGINE OIL

PRESSURE

INDICATOR

VNE

PLACARDS

FUEL

QUANTITY

INDICATOR

AMMETER

CLOCK

FUEL SHUTOFF

VALVE

PULL

AIR

DUAL TACHOMETER

FRESH AIR

VENT

KEY

SWITCH

TURBINE OUTLET

TEMPERATURE

EDGE LIGHTED SWITCH

(TOT) INDICATOR

PANEL

N1 TACHOMETER

EDGE LIGHTED CIRCUIT

BREAKER PANEL

ANTI-ICE

SWITCH

(250-C20R/2)

F03-014-2

Figure 4-3. Instrument Panel, RH Command - Layout Typical

FAA Approved

4-10

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

SWITCH HOUSING

LANDING LIGHT

SWITCH

IDLE RING

COPILOT’S

TWIST GRIP

PILOT’S THROTTLE

GOVERNOR

TWIST GRIP

INCREASE/DECREASE

SWITCH

THROTTLE

TWIST GRIP

FRICTION NUT

GOVERNOR

COPILOT’S

COLLECTIVE

INCREASE/DECREASE

COLLECTIVE

STICK FRICTION NUT

SWITCH

(OPTIONAL)

PILOT’S

COLLECTIVE STICK

CARGO HOOK

DWN

RELEASE (OPTION)

CYCLIC TRIM

SWITCH

ICS/COMM

TRIGGER

FLOAT INFLATE

SWITCH (OPTION)

START

BUTTON

PILOT’S

COLLECTIVE

F03-015

Figure 4-4. Cyclic and Collective Stick Grips

FAA Approved

Revision 13

4-11

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

4-2. ENGINE PRE-START COCKPIT CHECK

ELECTRICAL POWER - OFF

All cabin doors CLOSED AND SAFELOCKED

CHECK

Tail rotor pedals

ADJUST

NOTE: Adjust pedal position to insure that the pedals can be moved throughout the

entire range of travel.

Tail rotor pedal lock pins

SECURED

Seat belt and shoulder harness for proper fit and

FASTENED

engagement of buckle

NOTE: Insure center seat shoulder harness crosses over center of body.

Operation of shoulder harness inertia lock

CHECK

Cyclic, collective (friction off) and pedals

FULL TRAVEL

Cyclic stick

NEUTRAL, FRICTION

NOTE: Cyclic stick longitudinal neutral position is about 35 percent (1/3) travel from full

aft; lateral position may be determined by centering the friction control knob in

the guide link.

Tail rotor pedals

CENTERED

Collective stick

FULL DOWN

FRICTION ON

Landing light

OFF

Air filter bypass control handle (if installed)

CHECK SECURITY

AND POSITION

Rotor brake handle (if installed)

STOWED

Cabin heat (if installed)

OFF

Engine anti-ice (Allison 250-C20B)

OFF

Magnetic compass heading

CHECK

V_NE card

SELECT

Static position of all instruments

CHECK

FAA Approved

4-12

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

Altimeter

SET

All electrical switches

OFF

Radio switches

OFF

Circuit breakers

Fuel shutoff valve

OPEN (IN)

Attempting to start the engine with any bleed air devices ON, may

CAUTION

result in a ‘‘Hot start’’.

ELECTRICAL POWER - ON

Electrical power: Battery or external power start

F F

BAT/EXT switch: set to BAT for battery start; to EXT

AS REQUIRED

for external power start

F F

If used, connect GPU.

NOTE: Minimum capacity 20V dc with 500 amp load.

Maximum capacity 28.5V dc with 500 amp load.

Lights

AS REQUIRED

Key switch

Engine Out Warning System/Auto Reignition System Checks

F F

Pre-Generic and Late Generic Configurations:

NOTE: See Section I and Figure 4-2 to determine which version of the electrical system

is installed in the aircraft.

F F F

GEN switch ON then OFF to check audible engine out warnings (both

external horn in the cabin and internal within the ICS system).

F F F

Hold RE-IGN TEST switch in the TEST position. Verify the RE-IGN

caution light illuminates and the sound of the engine ignitor firing is heard.

Release the RE-IGN TEST switch.

F F F

Press the RE-IGN caution light to reset (extinguish) the light. (Pre-generic

configuration only)

FAA Approved

Revision 13

4-13

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

F F

Early Generic Configuration:

F F F

Place the Reignition Test switch in the GND TEST position (full up). Verify

that the ENGINE OUT warning and RE-IGN caution lights illuminate, the

audible engine out warnings activate (both external horn in the cabin and

internal within the ICS system), and the sound of the ignitor firing is heard.

F F F

Return test switch to OFF

Fuel gauge

CHECK READING

All other instruments

CHECK

XMSN OIL PRESS, ENG OUT, and GEN warning/caution

lights

Press-to-test caution and warning lights

CHECK

F F

Caution light dim switch

CHECK

NOTE: BAT 140° and RE-IGN P RST caution lights do not dim. All other caution lights

will return to bright when power is removed and restored by cycling the BAT

switch or pulling and resetting the PNL LT circuit breaker.

Cyclic trim control check:

F F

Momentarily motor cyclic trim control forward, left,

OPERATE

right, aft (listen for motor actuation)

Twistgrip to FULL OPEN, return to GROUND IDLE STOP, CHECK

then to CUTOFF position.

FAA Approved

4-14

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

4-3. ENGINE START

Cyclic stick - trimmed neutral; friction ON

RECHECK

Do not attempt engine start with cyclic stick in positions other than

CAUTION

neutral. Damage to rotor head and controls will result.

Collective stick - full down; friction on

RECHECK

Twistgrip - CUTOFF position

RECHECK

Generator switch OFF

RECHECK

A hot start may result if the GEN switch is left in the ON position.

CAUTION

(Early Generic Configuration Only)

Start pump

AS REQUIRED

NOTE: Start pump required when using alternate or emergency fuel (Ref. to Section II).

Rotors

CLEARED

Start/ignition button

PRESS AND HOLD

NOTE: Starter time limits are: 1 minute ON, 1 minute OFF; 1 minute ON, and 23 minutes

OFF.

Rotate twistgrip to ground idle for ignition when N₁ indicates 12 to 15 percent (see

Section II, Minimum N₁ Speed Starting Recommendations Placard).

NOTE: Peaking of N₁ below 15 percent may occur during cold weather starting

conditions. Under these conditions, a start may be attempted at a minimum of

12 percent N₁. GPU starts are recommended when normal cranking speed

cannot be obtained by using the battery.

FAA Approved

Revision 13

4-15

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

During starts, overtemperatures above 810°C for 10 seconds or

CAUTION

less with a momentary peak at 927°C for not more than 1 second are

permitted. Consult Rolls Royce Operation and Maintenance Manu-

al if these limits are exceeded.

ABORT START IF:

1. An immediate temperature rise is not observed on the TOT indi-

cator.

2. No indication of engine oil pressure is observed.

3. Main rotor is not rotating by 25 percent N₁ (Refer to Allison Op-

eration and Overhaul Manual.)

4. A zero or positive indication is observed on ammeter (this may

indicate a failure in the starting circuit that may de-energize the

starter creating conditions favorable for a hot start).

Abort start procedures:

F F

Close twistgrip to the cutoff position.

F F

Use starter to continue motoring engine for at least ten seconds or until TOT

decreases below 150°C.

Start/ignition button - release at 58 to 60 percent N₁

RELEASE

Engine oil pressure 50 to 130 psi

CHECK

NOTE: During cold weather operation, 150 psi oil pressure is allowable following an

engine start. Remain at ground idle RPM until normal oil pressure limits are

attained.

All caution and warning indicators out

CHECK

NOTE: Transmission oil pressure warning (XMSN OIL PRESS) indicator will go out

within 30 seconds from engine light-off for 369D25100 series transmissions, or

within 60 seconds for 369F5100 transmissions. The auto reignition ARMED light

ON; GEN OUT indicator will remain on until the generator switch is moved to the

GEN position.

The reignition indicator may illuminate when the transmission warning light goes

out. After ground idle RPM is attained, press the RE-IGN light to reset.

Engine idle speed - 64 to 65 percent N₁

CHECK

During engine operation at ground idle, keep pedals centered. Ped-

CAUTION

al bungee will tend to depress left pedal, thereby decreasing N₂/N_R

speed.

FAA Approved

4-16

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

All other engine instruments

CHECK

F F

N₂ engine and rotor rpm indicators for superimposed needles.

Malfunctions are indicated if rotor and engine rpm indicator

CAUTION

needles are not superimposed. Shut down engine if this condition

exists.

NOTE: ‘‘Superimposed’’ means within 1/2 a needle width. The relative positions of the

superimposed needles should remain constant during powered flight.

Start pump

AS REQUIRED

4-4. ENGINE RUN UP

NOTE: Refer to Section II “Power turbine (N₂) speed avoid range”.

Avoid continuous operation of engine between 90 and 98 percent N₂ if Allison

AD 83-03-02 has not been complied with (250-C20B only).

NOTE: Checks with an asterisk (:) need only be performed prior to the first flight of the

day. Insure that an “Auto Reignition Check” is performed prior to flying into falling

or blowing snow.

Electrical power

SELECT

F F

BAT/EXT switch

SELECT ‘‘BAT’’

F F

External power start

DISCONNECT GPU

Set generator (GEN) to ON (GEN OUT caution light out;

OPERATE AND

ammeter will show charge)

CHECK

NOTE: Monitor N₁ and TOT when turning generator switch ON.

If N₁ decays below 60 percent or TOT approaches 810°, turn generator OFF and

increase N₁ speed with twistgrip to 70 percent, then reset generator to ON.

During the initial recharging period after a battery start, electrical loads may

exceed 150 amps for a short period of time (2 minute limit). The electrical load

should be less than 150 amps prior to takeoff or activation of any additional

electrical equipment.

Avionics (as required)

ON AND CHECK

Cyclic friction

RELEASE AND SET

AS DESIRED

FAA Approved

Revision 16

4-17

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

Twistgrip

FULL OPEN

Check for unusual aircraft vibration or noise while accelerating

CAUTION

from ground idle to flight idle. If any unusual vibration or noise oc-

curs, this may be an indication of a loose or defective tailrotor dirve-

shaft damper. Shut aircraft down and advise maintenance.

CAUTION

Avoid rapid acceleration when parked on slippery surfaces.

NOTE: If the engine has been shut down for more than 15 minutes, stabilize at idle for

1 minute before increasing power.

:ENGINE CONTROLS/ENGINE OUT AND

LOW ROTOR WARNING/AUTO REIGNITION CHECKS

NOTE: Whenever there is transmission oil pressure the auto-reignition system is

armed.

Press reignition (RE-IGN P RST) light

LAMP OUT

N₂ high beep range - 104% to 105%

CHECK

N₂ low beep range - 98% or less

CHECK

Low rotor warning - on at 98 ± 1%

CHECK

NOTE: ENGINE OUT light only - no audio horn (early generic configuration).

ENGINE OUT light and audio horn (pre-generic and late generic).

RE-IGN P RST indicator light

Set N₂ to 102%

ESTABLISH

Press reignition (RE-IGN P RST)

LAMP OUT

Pulling the engine out warning system circuit breaker will disarm

CAUTION

the auto reignition and engine out/low rotor warning systems.

FAA Approved

4-18

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

:ENGINE BLEED AIR SYSTEMS CHECKS

CABIN HEAT (if installed) - ON - Observe 30-40°C

CHECK TOT

increase in TOT, then OFF.

INCREASE/

DECREASE

Engine ANTI-ICE ON - Observe increase 10-20°C in TOT, CHECK TOT

then OFF.

INCREASE/

DECREASE

SCAV-AIR Switch ON (if installed) observe slight rise in

CHECK TOT

TOT (about 5°C).

INCREASE AND SET

SWITCH AS DESIRED

NOTE: If no increase in TOT is observed, operation of the scavenge air system may be

checked by verifying that the flapper door (scavenge air outlet) is open.

:THROTTLE RIGGING CHECK

NOTE: If the flight will involve rolling the twistgrip to the ground idle position while

airborne (Autorotation training, maintenance test flight, etc.) this check must be

performed even thought it may not be the first flight of the day.

N2 102%

RECHECK

Pilot's twistgrip

SNAP TO IDLE

If engine flames out, do not try to recover by opening twistgrip.

CAUTION

Close twistgrip to CUTOFF and monitor TOT.

If engine flames out, refer to the HMI for proper throttle control rigging.

If dual controls are installed, repeat procedure using

RECHECK

copilot's twistgrip.

Twistgrip

FULL OPEN

N₂ - 102%

RECHECK

FAA Approved

Revision 13

4-19

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

4-5. BEFORE TAKEOFF

All caution and warning lights out

RECHECK

Engine oil pressure - 90 to 130 psi

RECHECK

Ammeter

CHECK READING

NOTE: Ammeter reading will fluctuate slightly when anti-collision lights are on.

All cabin doors closed and safelocked

RECHECK

Cabin heat

AS DESIRED

NOTE: Hover performance is reduced with cabin heat ON (Ref. Sections V and VIII).

Collective control friction

RELEASE AND

SET AS DESIRED

When removing collective friction, be alert for abnormal collective

WARNING

loads that would cause the collective to raise by itself.

Cyclic response check:

F F

With collective pitch full down, gently move cyclic stick

CHECK

and observe rotor tip for correct movement and track

All instruments in the green

CHECK

Position and anti collision lights

AS REQUIRED

SCAV AIR (if installed)

AS DESIRED

NOTE: Air filtration is improved with SCAV-AIR on, however, hover performance is

reduced (Ref. Sections V, and VIII).

Pitot Heat (if installed)

AS REQUIRED

FAA Approved

4-20

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

Engine ANTI-ICE:

AS REQUIRED

F F

Use engine ANTI-ICE when OAT is below 5°C (41°F) and visible moisture is

present.

F F

Check for TOT increase when turning anti-ice ON

NOTE: Hover performance is reduced with ANTI-ICE ON (Ref. Sections V and VIII).

Optional inflight test of the auto-reignition/engine out warning

system: (Early Generic Configuration Only):

NOTE: See Section I and Figure 4-2 to determine which version (‘‘early generic” / ‘‘late

generic”) of the generic wire harness is installed in the aircraft.

This check may be performed at the pilot’s discretion.

F F

Prior to takeoff:

F F F

While on the ground at 102-103% N2, place RE-IGN test switch in the FLT

(middle) position. RE-IGN and ENGINE OUT lights should illuminate.

F F F

Bring the aircraft to a hover and observe actuation of the engine out audible

warnings.

NOTE: If audible warnings are not heard, this indicates a possible rigging problem with

the air/ground switch. Refer to applicable maintenance instructions for

adjustment.

F F F

Land helicopter and return RE-IGN test switch to OFF and press RE-IGN

light to reset system.

FAA Approved

Revision 13

4-21

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

F F

While in cruise:

F F F

Place RE-IGN test switch in FLT position.

F F F

RE-IGN and ENGINE OUT lights should illuminate along with the

ENGINE OUT audible warning.

F F F

Return RE-IGN test switch to OFF.

F F F

Press RE-IGN light to reset system.

4-6. TAKEOFF

NOTE: For takeoff in noise-sensitive areas, refer to paragraph 4-17 for noise impact

reduction procedures.

F Determine that hover area and takeoff path are clear.

F Follow normal helicopter takeoff procedure with N₂ set at 103 percent.

NOTE: Governed N₂ rpm should increase 1/2 to 1 percent on takeoff - adjust as

necessary to maintain N2 at 103 percent.

F Follow recommended takeoff profile shown in Height Velocity Diagram (Ref.

Section V).

If sudden unusual or excessive vibrations should occur during

WARNING

flight, a precautionary landing should be made. No further flights

shall be attempted until the cause of the vibration has been

identified and corrected.

NOTE: Momentary fluctuation in indicated airspeed may occur during acceleration and

climbout. This fluctuation is characterized by a rapid rise in indicated air speed

to approximately 40 knots, followed by a drop back to 30 knots and then normal

increase as determined by the rate of acceleration. Maintain recommended

takeoff profile to minimize fluctuation. Indicated airspeed is unreliable when

climbing at less than 40 knots IAS.

F Use Cyclic trim as desired to minimize stick forces.

NOTE: Proper longitudinal trim is established when small fore and aft cyclic movements

require the same force.

FAA Approved

4-22

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

4-7. CRUISE

F Cyclic trim: use proper trimming procedures described for climbout.

SCAV AIR (if installed)

AS DESIRED

F Above 50 knots and 50-foot altitude above terrain, select N2 between 102

and 103 percent for best comfort level.

F Use engine anti-icing when OAT is below 5°C (41°F) and visible moisture

conditions prevail.

4-8. LOW SPEED MANEUVERING

F Maneuvers that exceed thrust capability of the tail rotor should be avoided.

NOTE: Conditions where thrust limits may be approached are: High density altitude,

high gross weight, rapid pedal turns, and placing the helicopter in a down wind

condition. These conditions may exceed the thrust capability of the tail rotor.

F Extreme aircraft attitudes and maneuvers at low speeds should be avoided.

Uncoordinated turns/maneuvers may cause fuel starvation with

WARNING

less than 35 pounds of fuel on board.

Observe the cross-hatched regions of Height Velocity Diagram

WARNING

(Ref. Section V). These represent airspeed/altitude combinations

from which a successful autorotation may be difficult to perform.

Operation within the cross hatched area in not prohibited, but

should avoided.

FAA Approved

Revision 13

4-23

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

4-9. PRACTICE AUTOROTATION

Perform throttle rigging check prior to attempting practice

WARNING

autorotations (paragraph 4-4). Misrigging of the throttle control

may result in inadvertent flameout during rapid closing of the

twistgrip to the ground idle position.

Uncoordinated turns/maneuvers may cause fuel starvation with

less than 35 LBS of fuel. Do not practice autorotations if the FUEL

LEVEL LOW caution indicator is ON.

Do not perform intentional full touchdown autorotation with blade

CAUTION

tracking reflectors installed on blade tips.

Make practice autorotation landings as follows:

For autorotation descent, the twistgrip should be in the full open or ground

idle position. However, if a practice autorotation landing (minimum engine

power) is desired, rotate the twistgrip to the ground idle position.

Increase collective pitch after establishing autorotation to prevent rotor

overspeed if flight is at high gross weight or high density altitude. To re-

duce rate of descent or to extend gliding distance, operate at minimum rotor

rpm. Restore ROTOR RPM (N_R) by lowering collective prior to flareout.

If a power recovery is desired, lower collective to full down, rotate the

twistgrip to the full open position, verify that N2 is between 102 and 103

percent and that full engine power is available prior to increasing collective.

Conduct practice autorotation at 130 knots IAS or below (see V_NE placards).

Maintain rotor between 420 and 523 by use of the collective control.

NOTE: Keeping the rotor above 420 RPM will place the engine above the N₂ speed

avoid range.

Refer to Section II “Power turbine (N₂) speed avoid range”.

CAUTION

Maximum gliding distance is obtained at 80 knots and 410 rotor rpm.

Minimum rate of descent is obtained at 60 knots and 410 rotor rpm.

NOTE: Glide distances attained during an actual engine out autorotation may be less

than the glide distances achieved during practice autorotations when operating

at reduced RPM (N₂/N_R needles joined).

Touchdown in a level attitude.

Avoid use of aft cyclic control or rapid lowering of collective pitch during

initial ground contact or during ground slide.

FAA Approved

4-24

Revision 17

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

Autorotation RPM:

Normal rotor RPM (collective fully down) is 485±5 RPM at 2250 pounds

gross weight at sea level, 60 knots. Rotor speed will decrease approximately

10 RPM for each 100 pound reduction in gross weight and increase approxi-

mately 6.5 RPM for each 1000 foot increase in density altitude. For gross

weights greater than 2250 pounds, increase collective control as required to

maintain approximately 485 RPM.

4-10. DOORS OFF FLIGHT

Doors off flight is permitted in accordance with the restrictions noted in Sec-

tion II.

Any object that is not properly secured may exit the aircraft

WARNING

during flight.

Items secured with Velcro (i.e., first aid kit, seat cushions) should

not be considered properly secured.

Secure or stow in the baggage compartment all loose equipment.

Secure or remove unoccupied seat cushions.

Use ear protection.

4-11. LANDING APPROACH

Set N₂ at 103 percent.

Set SCAV-AIR (if installed) as desired.

4-12. RUNNING LANDING

Maximum recommended ground contact speed is 30 knots for smooth hard sur-

face.

Avoid rapid lowering of the collective after ground contact.

Avoid the use of aft cyclic after ground contact.

FAA Approved

Revision 13

4-25

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

4-13. ENGINE/AIRCRAFT SHUTDOWN

Care should be taken when rotating the twistgrip to the ground idle

CAUTION

position and from ground idle to the cutoff position if the helicopter

is parked on a icy or slippery surface (helicopter may spin in direc-

tion of main rotor blade rotation).

NOTE: Shut down the engine before exiting the helicopter unless safety or operational

considerations dictate otherwise.

Pilot's twistgrip

PERFORM

DECELERATION

CHECK

NOTE: To insure proper engine performance, perform the deceleration check during

shut down after the last flight of the day (see paragraph 4-15).

Twistgrip to GROUND IDLE detent - hold for 2 minutes

SET

Collective stick

FULL DOWN

FRICTION ON

Cyclic stick (neutral position - approximately

TRIM TO NEUTRAL

1/3 from full aft)

APPLY FRICTION

All unnecessary bleed air and electrical

OFF

equipment

Pedals (maintain until rotor has stopped)

CENTERED

Twistgrip from GROUND IDLE to CUTOFF position

SET

NOTE: Immediately after closing twistgrip to the CUTOFF position, a dual tachometer

needle split should occur with NR lagging behind N₂. If no needle split occurs,

check overrunning clutch for proper operation per HMI.

To ensure throttle cutoff, hold twistgrip in cutoff position until N₁ decelerates to

zero and TOT is stabilized. Check for TOT decrease.

An afterfire (recognized by a rapid increase in TOT) can occur dur-

CAUTION

ing shutdown if fuel cutoff is not complete. If an afterfire occurs, im-

mediately engage the starter and motor the engine to minimize the

temperature encountered. To extinguish the fire, continue motor-

ing the engine with the twistgrip in the CUTOFF position and pull

out the fuel shutoff valve. Observe TOT limits.

FAA Approved

4-26

Revision 13

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

NOTE: If thumping or a rapping sound is heard from the drive train during the final

revolution of the main rotor, inspect the tail rotor drive shaft couplings in

accordance with the HMI.

Engine out warning at 55 percent N₁

CHECK

NOTE: Early Generic Configuration: ENG OUT light only - no audio .

Pre-Generic and Late Generic Configuration: ENGINE OUT light and audio

horn .

See Section I and Figure 4-2 to determine which version of the generic wire

harness is installed in the aircraft.

Auto reignition light

Do not use collective pitch to slow rotor.

CAUTION

Generator switch

OFF

NAV/COM switches

OFF

All other switches

OFF

Rotor brake (if installed) - apply at 205 rpm or less,

APPLY

release during last rotor revolution

Care should be taken when applying the rotor brake if the helicopter

CAUTION

is parked on slippery or icy surface. The tail rotor has little effect

controlling torque at less than normal operating RPM when the en-

gine is not driving the rotor system. Full control of the helicopter

during these conditions may be limited.

Damage to the rotor blades and strap pack can result from sudden

stopping of rotor.

Rotor brake handle stowed (up)

CHECK

BAT/EXT switch

OFF

Key switch

OFF

FAA Approved

Revision 13

4-27

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

Normal Procedures

(Model 369E)

4-14. POST FLIGHT

Aircraft-investigate any suspected damage

CHECK

Fuel and oil leaks

CHECK

Engine oil tank for correct oil level

REPLENISH IF LOW

NOTE: Oil level should be checked within 15 minutes after shutdown.

Logbook entries

COMPLETE

NOTE: Record total number of Torque Events (TE’s). Ref. HMI-2, Section 04-00-00.

Flight manual and equipment

STOWED

Aircraft tiedowns, covers

SECURED

4-15. DECELERATION CHECK

Generator (GEN) switch

OFF

Pilot's twistgrip

FULL OPEN

Pilot's collective control

FULL DOWN

FRICTION ON

Stabilize N2 at exactly 103 percent (BEEP as required) for

SET

15 seconds

Pilot's twistgrip

SNAP TO IDLE

Begin time check with stop watch. Stop time as N₁ passes through 65 per-

cent. Observe elapsed time. Minimum allowable lapsed time is 2 seconds.

NOTE: Practice or retakes may be required before proficiency can be obtained in

deceleration timing.

If deceleration time is less than two seconds, make two more checks to con-

firm time. If confirmed time is less than the allowable minimum, refer to

the applicable Allison Operation and Maintenance Manual

If engine flames out, do not try to recover by opening twistgrip.

CAUTION

Close twistgrip to the CUTOFF position and monitor TOT.

If engine flames out, refer to the HMI.

Generator switch

FAA Approved

4-28

Revision 17

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Normal Procedures

4-16. NORMAL ENGINE RESTART

Do not exceed 150°C residual TOT when ignition is attempted.

Reduce TOT by motoring engine with starter. Speeds in excess of 15 percent

N1 may be experienced.

4-17. NOISE IMPACT REDUCTION PROCEDURES

Safe operation of the helicopter always has the highest priority. Uti-

CAUTION

lize the following procedures only when they will not conflict with

safe helicopter operation.

Certain flight procedures are recommended to minimize noise impact on sur-

rounding areas. It is imperative that every pilot subject the public to the least

possible noise while flying the helicopter.

Takeoff:

Takeoff using maximum takeoff power at the speed for best rate of climb

(Ref. Section V).

Proceed away from noise sensitive areas.

If takeoff must be made over noise sensitive area, distance (altitude) is best

form of noise suppression.

Cruise:

Maintain 1000 feet minimum altitude where possible.

Maintain speed of no more than 110 knots over populated areas.

Keep noise sensitive areas to left side of helicopter.

Coordinated turns at around the speed for best rate of climb cause no ap-

preciable change in noise.

Sharper turns reduce area exposed to noise.

Approach:

Use steepest glideslope consistent with passenger comfort and safety.

Keep noise sensitive areas to left side of helicopter.

FAA Approved

Revision 17

4-29

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

S E C T I O N V

PERFORMANCE DATA

TABLE OF CONTENTS

PARAGRAPH

PAGE

5-1.

General

5-1

5-2.

Density Altitude

5-2

Figure 5-1. Density Altitude Chart

5-3

5-3.

Airspeed Calibration

5-4

Figure 5-2. Airspeed Calibration Curve

5-5

5-4.

Speed For Best Rate of Climb

5-6

Figure 5-3. Speed for Best Rate of Climb

5-7

5-5.

Hover Ceiling VS Gross Weight - In ground Effect (IGE)

5-8

Figure 5-4. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard Landing Gear, Rolls Royce 250-C20B

5-9

Figure 5-5. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Extended Landing Gear, Rolls Royce 250-C20B

5-10

Figure 5-6. Hover Ceiling VS Gross Weight, IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 2 or 4-Bladed Tail Rotor,

Rolls Royce 250-C20B

5-11

Figure 5-7. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard or Extended Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20B

5-12

Figure 5-8. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Utility Floats Installed, Rolls Royce 250-C20B

5-13

Figure 5-9. Hover Ceiling VS Gross Weight, IGE, 5 Foot Skid Clearance,

Utility Floats Installed, Rolls Royce 250-C20B

5-14

Figure 5-10. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard Landing Gear, Rolls Royce 250-C20R/2

5-15

Figure 5-11. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Extended Landing Gear, Rolls Royce 250-C20R/2

5-16

Figure 5-12. Hover Ceiling VS Gross Weight IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 2-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

5-17

Figure 5-13. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard or Extended Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

5-18

FAA Approved

Revision 14

5-i

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

PARAGRAPH

PAGE

Figure 5-14. Hover Ceiling VS Gross Weight, IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

5-19

5-6. Height Velocity Diagram/Gross Weight Limits For Height Velocity Diagram

5-20

Figure 5-15. Height Velocity Diagram

5-21

Figure 5-16. Gross Weight Limits for Height Velocity Diagram

5-22

5-7. Power Check - Rolls Royce 250-C20B Engine

5-23

Figure 5-17. Power Check Chart - Rolls Royce 250-C20B Engine

5-25

5-8. Power Check - Rolls Royce 250-C20R/2

5-27

Figure 5-18. Power Check Chart - Rolls Royce 250-C20R/2 Engine

5-29

FAA Approved

5-ii

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

SECTION V

PERFORMANCE DATA

5-1. GENERAL

This section contains baseline helicopter performance information as defined

within certain conditions such as airspeed, weight, altitude, temperature, wind

velocity and engine power available. Data is applicable to the basic helicopter

without any optional equipment installed unless otherwise noted.

NOTE: Unless otherwise stated, the performance data put forth in this section applies

to MD 500E (Model 369E) Helicopters equipped with either the Rolls Royce

250-C20B or 250-C20R/2 engines.

Select the appropriate power check, and hover performance charts for type of

engine installed. (See Engine or Airframe Log Book.)

Select the appropriate hover performance charts for type of optional equipment

and engine installed.

FAA Approved

Revision 14

5-1

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

5-2. DENSITY ALTITUDE

Description:

The chart allows a quick estimation of the density altitude when pressure

altitude and OAT are known. This chart should be used for determining

density altitude for use with gross weight limits for the HV Diagram and

speed for Best Rate of Climb Chart. This chart can also be used to deter-

mine true airspeed.

Use of Chart:

To determine density altitude, the pilot must know pressure altitude and

outside air temperature. Enter bottom of chart with known or estimated

OAT, move up to known pressure altitude line, move to left and note densi-

ty altitude.

NOTE: Pressure altitude is found by setting 29.92 (1013 mb) in kolsman window ±

altimeter error.

To determine true airspeed convert indicated airspeed (IAS) to calibrated

airspeed (CAS) utilizing the Airspeed Calibration Curve (Figure 5-2). Read

value on right of chart opposite known density altitude. Multiply CAS by

this value to determine true airspeed.

Examples:

Wanted

Find density altitude

Known

OAT= -15°C

H_P= 6,000

Method

Follow -15°C line to 6,000 ft pressure altitude line; read density altitude

(3800 ft).

Wanted

Find TAS

Method

Read directly across from density altitude: (3800 ft). Note density factor

of 1.058.

1. Find calibrated airspeed (Ref. Figure 5-2)

2. Find true airspeed

130 KIAS = 130.5 KCAS

130.5 KCAS

1.058 = 138.1; round to 138 knots true airspeed.

FAA Approved

5-2

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

20000

1.36

1.34

18000

1.32

1.30

16000

1.28

1.26

14000

1.24

1.22

12000

1.20

1.18

10000

1.16

1.14

8000

1.12

1.10

6000

1.08

4000

1.06

1.04

2000

1.02

1.00

0.98

-2000

-40

-30

-20

-10

TEMPERATURE - °C

-40

-30

-20

-10

100

110

120

130

140

TEMPERATURE - °F

F03-020

Figure 5-1. Density Altitude Chart

FAA Approved

Revision 14

5-3

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

5-3. AIRSPEED CALIBRATION

Description:

The chart shows the difference between indicated and calibrated airspeeds.

Indicated airspeed (IAS) corrected for position and instrument error equals

calibrated airspeed (CAS).

Use of Chart:

To determine calibrated airspeed, the pilot must know the indicated air-

speed.

Example

WANTED: Calibrated airspeed

KNOWN: Indicated airspeed = 120 knots

METHOD: Enter the bottom of the chart at the indicated airspeed of 120

knots. Move up to the airspeed calibration line; move left and read 120.5

knots, calibrated airspeed.

By entering the chart from the opposite direction, calibrated airspeed

may be converted to indicated airspeed.

FAA Approved

5-4

Revision 14

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

5-4. SPEED FOR BEST RATE OF CLIMB

Description:

This chart shows the indicated airspeed to use for the best rate of climb at

any given density altitude.

Use the chart as illustrated by the example below.

Example:

WANTED: Speed for best rate of climb

KNOWN: Density altitude = 5000 feet

METHOD: Enter the left side of chart at the known density altitude of

5000 feet. Move to the right along line and read 62 KIAS as the speed for

best rate of climb.

FAA Approved

5-6

Revision 14

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

5-5. HOVER CEILING VS GROSS WEIGHT - IN GROUND EFFECT (IGE)

Description:

The hover ceiling charts show the maximum hover weight capability in

ground effect (IGE) for known conditions of pressure altitude and outside

air temperature (OAT), or alternately, the maximum hover ceiling for a

known gross weight and outside air temperature.

Ensure that the appropriate hover ceiling chart for type of engine

WARNING

and optional equipment installed is selected prior to determining

IGE hover performance.

The Hover Ceiling vs Gross Weight charts are based on:

1. Takeoff power at 103 % N₂

2. Cabin heat and engine anti-ice OFF

3. Electrical load of 10 amps

NOTE: Controllability during downwind hovering, sideward and rearward flight has been

demonstrated to be adequate in winds up to 17 knots.

Use of Chart:

The following example explains the correct use of the chart in Figure 5-4.

To determine the maximum gross weight for hovering at 3.5 ft skid height,

the pilot must know the pressure altitude and the outside air temperature.

Example

WANTED: Maximum gross weight for hover at 3.5 feet skid height at

takeoff power.

KNOWN:

PA = 8000 feet; OAT = 25°C

METHOD:

Select the appropriate chart and enter the chart at 8000 PA.

Move horizontally across to the 25° OAT line. At this point, move direct-

ly down to the bottom of the chart and read off the gross weight scale:

2700 pounds.

If mist eliminator is installed, reduce weight capability by 40 LBS, or

2660 LBS.

This chart may also be used to determine maximum pressure altitude for

hovering at 3.5 feet skid height if the gross weight and the outside air tem-

perature are known. Enter the bottom of the chart at the known gross

weight, move up to the known OAT, move left and read the maximum hov-

er ceiling pressure altitude.

FAA Approved

5-8

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

16000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

14000

DWT

12000

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

220

232

469

8000

152

157

306

12000

111

117

227

16000

172

2000

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

<<<< ROLLS ROYCE 250-C20B >>>>

F03-017-1

Figure 5-4. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard Landing Gear,

Rolls Royce 250-C20B

FAA Approved

Revision 14

5-9

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

16000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

14000

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

12000

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

220

232

469

8000

152

157

306

12000

111

117

227

16000

172

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-036-1

<<<< ROLLS ROYCE 250-C20B >>>>

Figure 5-5. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Extended Landing Gear,

Rolls Royce 250-C20B

FAA Approved

5-10

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

16000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

14000

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

12000

MAXIMUM INTERNAL

GROSS WEIGHT

GROSS WEIGHTS ABOVE

3000 LB MUST BE EXTERNAL

10000

AND JETTISONABLE

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

2000

ALT. FT.

HEAT

ICE

SL TO 4000

220

232

469

8000

152

157

306

12000

111

117

227

16000

172

2000

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-037-1

NOTE: FOR EXTENDED LANDING GEAR SKID HEIGHT IS 5 FEET.

<<<< ROLLS ROYCE 250-C20B >>>>

Figure 5-6. Hover Ceiling VS Gross Weight, IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 2 or 4-Bladed Tail Rotor,

Rolls Royce 250-C20B

FAA Approved

Revision 14

5-11

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PAR-

TICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

INCREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON MAIN

REDUCE WEIGHT:

ROTOR BLADES ONLY

1) 55 LB WITH SCAVENGE ON

DECREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON TAIL

2) 40 LB WITH MIST ELIMINATOR INSTALLED

ROTOR BLADES ONLY

16,000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

14,000

OAT°C

-5

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

12,000

-25 °C

10,000

-15 °C

-5 °C

8000

5 °C

15 °C

6000

25 °C

35 °C

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

45 °C

2000

SL TO 4000

220

232

469

8000

152

157

306

12000

111

117

227

16000

172

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT-POUNDS

F03-041-1

<<<< ROLLS ROYCE 250-C20B >>>>

Figure 5-7. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard or Extended Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20B

FAA Approved

5-12

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

18000

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

16000

INCREASE (OR DECREASE) WT. CAPABILITY LBS

(ABOVE CRITICAL ALTITUDE) PER

10 AMP

REDUCTION (OR INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

DWT

14000

12000

MAXIMUM INTERNAL

GROSS WEIGHT

GROSS WEIGHTS ABOVE

3000 LB MUST BE EXTERNAL

AND JETTISONABLE

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

220

232

469

8000

152

157

306

12000

111

117

227

16000

172

2000

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-045-1

<<<< ROLLS ROYCE 250-C20B >>>>

Figure 5-8. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Utility Floats Installed,

Rolls Royce 250-C20B

FAA Approved

Revision 14

5-13

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

18000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

16000

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

DWT

14000

MAXIMUM INTERNAL

GROSS WEIGHT

12000

GROSS WEIGHTS ABOVE 3000

LB MUST BE EXTERNAL AND

JETTISONABLE

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

SL TO 4000

220

232

469

8000

152

157

306

2000

12000

111

117

227

16000

172

2000

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-045-2

<<<< ROLLS ROYCE 250-C20B >>>>

Figure 5-9. Hover Ceiling VS Gross Weight, IGE, 5 Foot Skid Clearance,

Utility Floats Installed,

Rolls Royce 250-C20B

FAA Approved

5-14

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT: 50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION

(OR INCREASE) IN ELECTRICAL LOAD

16000

OAT°C

-5

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

14000

12000

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

289

396

639

8000

256

316

557

12000

176

217

381

16000

129

157

278

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-017-2

<<<< ROLLS ROYCE 250-C20R/2 >>>>

Figure 5-10. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard Landing Gear,

Rolls Royce 250-C20R/2

FAA Approved

Revision 14

5-15

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

INCREASE (OR DECREASE) WT. CAPABILITY LBS

(ABOVE CRITICAL ALTITUDE) PER

10 AMP

REDUCTION (OR INCREASE) IN ELECTRICAL LOAD

16000

OAT°C

-5

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

14000

12000

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

289

396

639

8000

256

316

557

12000

176

217

381

16000

129

157

278

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-036-2

<<<< ROLLS ROYCE 250-C20R/2 >>>>

Figure 5-11. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Extended Landing Gear,

Rolls Royce 250-C20R/2

FAA Approved

5-16

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT:

50LB WITH ABRASION STRIPS ON MAIN

ROTOR BLADES ONLY

1. 55LB WITH SCAVENGE ON

2. 40LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50LB WITH ABRASION STRIPS ON TAIL

ROTOR BLADES ONLY

MAXIMUM INTERNAL

INCREASE (OR DECREASE) WT.

GROSS WEIGHT

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

GROSS WEIGHTS ABOVE

INCREASE) IN ELECTRICAL LOAD

3000 LB MUST BE EXTERNAL

16000

OAT°C

-5

AND JETTISONABLE

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

14000

12000

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

2000

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

SL TO 4000

289

396

639

8000

256

316

557

12000

176

217

381

16000

129

157

278

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

F03-037-2

NOTE: FOR EXTENDED LANDING GEAR SKID HEIGHT IS 5 FEET.

<<<< ROLLS ROYCE 250-C20R/2 >>>>

Figure 5-12. Hover Ceiling VS Gross Weight IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 2-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

FAA Approved

Revision 14

5-17

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICA-

BLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

INCREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON

REDUCE WEIGHT:

MAIN ROTOR BLADES ONLY

1) 55 LB WITH SCAVENGE ON

DECREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON

2) 40 LB WITH MIST ELIMINATOR INSTALLED

TAIL ROTOR BLADES ONLY

16,000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

14,000

INCREASE) IN ELECTRICAL LOAD

ISA

OAT°C

-5

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

12,000

ISA + 20

OAT °C

10,000

-25

-15

8000

-5

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

ALT. FT.

HEAT

ICE

2000

SL TO 4000

289

396

639

8000

256

316

557

12000

176

217

381

16000

129

157

278

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT-POUNDS

F03-041-2

NOTE: SKID CLEARANCE 4.5-FEET FOR STANDARD LANDING GEAR.

<<<< ROLLS ROYCE 250-C20R/2 >>>>

Figure 5-13. Hover Ceiling VS Gross Weight, IGE, 3.5 Foot Skid Clearance,

Standard or Extended Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

FAA Approved

5-18

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO

PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET

REDUCE WEIGHT:

INCREASE WEIGHT: 50lb WITH ABRASION STRIPS ON

1. 55lb WITH SCAVENGE ON

MAIN ROTOR BLADES ONLY

2. 40lb WITH MIST ELIMINATOR INSTALLED:

DECREASE WEIGHT: 50lb WITH ABRASION STRIPS ON

TAIL ROTOR BLADES ONLY

16000

MAXIMUM INTERNAL

GROSS WEIGHT

GROSS WEIGHTS ABOVE

3000 LB MUST BE EXTERNAL

AND JETTISONABLE

14000

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

OAT°C

-5

12000

DWT

NOT VERIFIED WHEN MAIN ROTOR

BLADES HAVING ABRASION STRIPS

ARE INSTALLED

10000

8000

6000

4000

REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:

(APPLICABLE TO ALL TEMPERATURES)

PRESSURE

CABIN

ANTI-

BOTH

2000

ALT. FT.

HEAT

ICE

SL TO 4000

289

396

639

8000

256

316

557

12000

176

217

381

16000

129

157

278

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

NOTE: FOR EXTENDED LANDING GEAR SKID HEIGHT IS 5 FEET.

F03-037-3

<<<< ROLLS ROYCE 250-C20R/2 >>>>

Figure 5-14. Hover Ceiling VS Gross Weight, IGE, 6 Foot Skid Clearance,

Standard Landing Gear, 4-Bladed Tail Rotor,

Rolls Royce 250-C20R/2

FAA Approved

Revision 14

5-19

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

5-6. Height Velocity Diagram/Gross Weight Limits For Height Velocity

Diagram

Description:

Airspeed/altitude combinations to be avoided in the event of an engine fail-

ure during takeoff are shown in the Height Velocity diagram (Ref.

Figure 5-15).

Conditions:

The height velocity diagram is based on sea level, standard day conditions,

over a smooth hard surface at 3000 pounds gross weight.

Use of Chart:

Observe the cross-hatched regions of the Height Velocity Diagram.

CAUTION_{These represent airspeed/altitude combinations from which a}

successful autorotation landing would be difficult to perform.

Operation within the cross-hatched area is not prohibited, but

should be avoided.

The recommended takeoff profile line shows the airspeed/altitude combina-

tions recommended for takeoff.

The unmarked region represents the area in which safe autorotational land-

ings may be performed with average pilot skill and reaction time.

Gross Weight Limits for Height Velocity Diagram (Ref. Figure 5-16)

Description

The gross weight limits for this chart show the reduction in gross weight

required as a function of density altitude in order for the Height Velocity

curve to apply.

Use of Chart

Use chart to determine gross weight at which Height Velocity curve will

apply for other density altitudes above sea level.

Example

WANTED: Gross weight for Height Velocity Diagram

KNOWN: Density altitude = 2000 feet

METHOD: Enter left side of chart at 2000 feet density altitude. Move

right to the line; move down and note 2900 pounds gross weight.

FAA Approved

5-20

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

⁵⁰⁰ Ç

ÇÇ

ÇÇÇ

⁴⁰⁰ ÇÇÇÇ

ÇÇÇÇ

SMOOTH HARD SURFACE, WIND CALM

ÇÇÇÇ

AVOID OPERATION IN CROSS HATCHED AREAS

ÇÇÇÇ

300

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

200

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

RECOMMENDED

ÇÇÇÇ

ÇÇ

TAKEOFF PROFILE

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

100

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇ

ÇÇ

ÇÇÇÇÇÇÇÇ

ÇÇ

ÇÇÇ

ÇÇ

ÇÇÇÇÇÇÇÇ

ÇÇ

ÇÇÇ

ÇÇ

100

120

140

INDICATED AIRSPEED - KNOTS

F03-016-1

Figure 5-15. Height Velocity Diagram

FAA Approved

Revision 14

5-21

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

5-7. POWER CHECK - ROLLS ROYCE 250-C20B ENGINE

Description:

The Power Check Chart shows the relationship of engine torque, turbine

outlet temperature, and horsepower at various conditions of pressure alti-

tude and OAT for an Rolls Royce 250-C20B engine producing specification

power as installed in the MD 500E helicopter. The primary purpose of this

chart is its use as an engine performance trending tool to aid in determin-

ing whether the engine is producing specification power, or if engine power

deterioration has occurred.

NOTE: Power check data taken at regular intervals should be plotted to monitor trends

in engine condition. See Rolls Royce 250-C20 Series operational and

Maintenance Manual for additional information on trend analysis.

The power check chart is based on the following conditions:

103 percent N₂ .

Cabin heat and engine anti-ice OFF.

Particle separator SCAV AIR OFF.

10 amperes electrical load.

Engine bleed valve closed.

Use Of Chart:

The primary use of the chart is illustrated by the example below and by

the sample arrows shown on the chart. To determine power check values, it

is necessary to read and record engine TORQUE PRESSURE, TURBINE

OUTLET TEMPERATURE, PRESSURE ALTITUDE, and OAT while the he-

licopter is flown in level flight at 103 percent N₂.

Do not exceed engine/aircraft limits.

WARNING

Accessories required for safe flight should be operated during each

check.

Maintain separation from objects in air or on the ground.

WARNING

Reset altimeter if required after obtaining pressure altitude.

NOTE: Best power check data is obtained at 87.2 psi torque or 810°C TOT, this will

ensure engine operation with bleed valve closed. Allow engine to stabilize at

least one minute at the test power setting before recording data.

FAA Approved

Revision 14

5-23

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

Example:

WANTED Check engine performance

DATA OBTAINED DURING FLIGHT:

Torque = 87.2 psig

TOT = 780°C

PA = 1000 feet

OAT = 20°C

METHOD

1. Enter the bottom right of the chart at 87.2 psig torque. Move up

along the 87.2 psig torque line to the 1000 foot pressure altitude curve,

move left to the 20°C OAT curve; now move down and read specification

TOT of 790°C.

2. Compare the specification TOT of 790°C with the TOT observed dur-

ing flight (780°C for this example). The TOT that was observed is lower

than the specification TOT. If the TOT observed had been higher than

the specification TOT read from the chart, some power deterioration will

have occurred and the performance data given in this manual may not

be obtained.

3. When trend check procedures indicate engine power deterioration, re-

fer to the Rolls Royce Operation and Maintenance Manual for corrective

action.

NOTE: Data obtained during engine engine operation with the bleed valve not fully

closed will result in incorrect comparisons of actual versus specification TOT.

If a mist eliminator is installed, subtract 5°C from the TOT read during flight

before comparing it with the specification TOT.

4. Actual engine horsepower may be obtained by entering the bottom of

the chart at the observed engine torque pressure, moving up along the

torque line to the Sea Level Pressure Altitude curve, and then moving

right to read the engine shaft horsepower.

FAA Approved

5-24

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

DEGREES FAHRENHEIT

1000

1100

1200

1300

1400

1500

AMBIENT TEMPERATURE

2000 FT

PRESSURE ALTITUDE

400

SEA

LEVEL

350

300

TO READ POWER

REFLECT OFF

250

SEA LEVEL LINE

N₂ 103%, CABIN HEAT & ANTI-ICE OFF

SCAVENGE BLEED-OFF ELECTRICAL

200

LOAD 10 AMPS

150

AREA OF ENGINE

TORQUE LIMIT 87.2 PSI

OPERATION WITH

BLEED VALVE OPEN

100

510

550

600

650

700

750

800

MAX

TORQUE

TURBINE OUTLET TEMPERATURE

TORQUE (PSI)

DEGREES CELSIUS

F03-021-1

MODIFIED 250-C20B ENGINE POWER CHECK CHART

WITH BLANKED OUT AREA FOR ENGINE OPERATION WITH BLEED VALVE OPEN

Figure 5-17. Power Check Chart - Rolls Royce 250-C20B Engine

FAA Approved

Revision 17

5-25

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

5-8. POWER CHECK - ROLLS ROYCE 250-C20R/2

The Power Check Chart shows the relationship of engine torque, turbine outlet

temperature, and horsepower at various conditions of pressure altitude and

OAT for an Rolls Royce 250-C20R/2 engine producing specification power as

installed in the MD 500E helicopter. The primary purpose of this chart is its

use as an engine performance trending tool to aid in determining whether the

engine is producing specification power, or if engine power deterioration has

occurred.

NOTE: Power check data taken at regular intervals should be plotted to monitor trends

in engine condition. See Allison 250-C20 Series operational and Maintenance

Manual for additional information on trend analysis.

The C20R/2 Power Check Chart is based on the same conditions as the C20B

Power Check Chart. First, an adjustment to the OAT should be made before

entering the chart (add 2.5°C if the data was taken in a hover or 1°C if the

data was taken in forward flight). The second change is the addition of ``Accel-

eration Bleed Valve Open'' lines to the chart; any reflection of data that falls

below the appropriate dashed altitude reference line should be disregarded as

it may involve a partially open engine accelerating bleed valve.

NOTE: If a mist eliminator is installed, subtract 5°C from the TOT read during flight

before comparing it with the specification TOT.

Example 1:

WANTED: Check engine performance

DATA OBTAINED DURING FLIGHT:

Torque

= 87.2 psig

TOT

= 750°C

= 1000 feet

OAT

= 19°C

Specification TOT (from chart): 755°C

Compare the specification TOT of 755°C with the TOT observed during

flight (750°C for this example). The TOT that was observed is lower than

the specification TOT. If the TOT observed had been higher than the speci-

fication TOT read from the chart, some power deterioration will have oc-

curred and the performance data given in this manual may not be obtained.

FAA Approved

Revision 14

5-27

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Performance Data

Example 2:

WANTED: Check engine performance

DATA OBTAINED DURING HOVERING:

Torque = 42.0 psig

TOT = 650°C

PA = 8000 feet

OAT = 7.5°C

NOTE: Be sure to add 2.5°C to the observed OAT before continuing.

Specification TOT (from chart): 645°C

Compare the specification TOT of 645°C with the TOT observed during

flight (650°C for this example). The TOT that was observed is higher than

the specification TOT. However, note that the junction of the 10°C curve

with the 645°C TOT line lies below the 8000 foot (PA) bleed line (dashed

line). Thus it is an inappropriate region in to which to determine power.

The higher-than-spec TOT is probably due to the accelerating bleed valve

being partially opened rather than the engine having some power deteriora-

tion. IF POSSIBLE, START OVER AND CHECK THE ENGINE PER-

FORMANCE AT A HIGHER POWER SETTING (ie., powered flight).

FAA Approved

5-28

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Performance Data

ADD TO AMBIENT TEMPERATURE

CABIN HEAT, ANTI-ICE OFF

2 1/2°C (4 1/2°F) IN HOVER

SCAVENGE BLEED OFF

1°C (2°F) IN FORWARD FLIGHT

ELECTRICAL LOAD 10 AMPS

400

350

300

TO READ POWER

250

REFLECT OFF

ACCELERATING BLEED VALVE OPEN

SEA LEVEL LINE

AVOID ENGINE CHECK IN REGION

BELOW APPROPRIATE ALTITUDE LINE

200

500

525

550

575

600

625

650

675

700

725

750

775

800

TURBINE OUTLET TEMPERATURE

TORQUE (PSI)

(DEGREES CELSIUS)

F03-021-2

Figure 5-18. Power Check Chart - Rolls Royce 250-C20R/2 Engine

FAA Approved

Revision 17

5-29

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

S E C T I O N VI

WEIGHT AND BALANCE DATA

TABLE OF CONTENTS

PARAGRAPH

PAGE

6-1.

Weight and Balance Characteristics

6-1

Table 6-1. Center of Gravity Limits

6-1

Figure 6-1. Longitudinal Center of Gravity Limits

6-2

Figure 6-2. Reference Coordinates (Sheet 1 of 2)

6-3

Figure 6-2. Reference Coordinates (Sheet 2 of 2)

6-4

Figure 6-3. Station Diagram

6-5

6-2.

Weight and Balance Criteria

6-6

6-3.

Equipment Removal or Installation

6-6

Figure 6-4. Sample Weight and Balance Report (Sheet 1 of 2)

6-7

Figure 6-4. Sample Weight and Balance Report (Sheet 2 of 2)

6-8

Figure 6-5. Sample Surplus and Missing Items

6-9

Figure 6-6. Sample Weight and Balance Record

6-10

6-4.

Weight and Balance Determination - Passenger Configuration

6-11

6-5.

Longitudinal Loading of Cargo

6-13

6-6.

Permissible Lateral Loadings

6-15

6-7.

Lateral Loading of Cargo

6-15

Figure 6-7. Fuel Station Diagram (Jet-A at 6.8 Pounds per Gallon)

(Sheet 1 of 2)

6-17

Figure 6-7. Fuel Station Diagram (Jet-B at 6.5 Pounds per Gallon)

(Sheet 2 of 2)

6-18

Table 6-2. Weights and Longitudinal Moments - Pilot, Passenger, Baggage

6-19

Table 6-3. Weights and Lateral Moments - Pilot, Passenger, Baggage

6-20

Table 6-4. Weight and Loading for 369H90035-503 Seating and Belts

for Four Installation (High Density Seating)

6-21

6-8.

Internal Loading of Cargo

6-22

Table 6-5. Cargo Weight Versus Loop Restraint

6-22

Figure 6-8. Cargo Restraint

6-23

Revision 17

6-i

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

SECTION VI

WEIGHT AND BALANCE

DATA

6-1. WEIGHT AND BALANCE CHARACTERISTICS

Weight and balance characteristics:

Maximum certified gross weight - 3000 pounds.

Minimum flying weight - 1538 pounds.

Longitudinal Reference Datum100 inches forward of rotor centerline (rotor

hub centerline is located at Station 100).

Cargo Deck Capacity - 1300 pounds (not to exceed 115 pounds per square

foot)

Utility Stowage Compartment Limited to 50 pounds

Center of Gravity Limits:

Lateral ``+'' is right of centerline; lateral ``-'' is left of centerline when look-

ing forward.

Table 6-1. Center of Gravity Limits

Longitudinal C.G. Limit

Lateral C.G. Limit

Gross Weight

(Sta-in.)

(lb)

Forward

Aft*

(+) Right, (-) Left

3000

99.0

103.0

±3.0

2500

99.0

104.5

±3.0

2000

99.0

106.0

±3.0

1538

99.0

107.4

±3.0

*NOTE: The aft longitudinal C. G. limit varies linearly from a gross weight of 3000

pounds at Station 103.0 to 1538 pounds at Station 107.4

Revision 14

6-1

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

ROTOR

STA

78.5

100.0

124.0

CG OF COPILOT

CARGO COMPARTMENT

PASSENGER

STA

15.0

174.0

+ 15.5

+ 12.2

REFERENCE

0.0

DATUM

-12.2

-13.0

CG OF PILOT

TW0 PLACE COCKPIT

LEFT HAND COMMAND

STA

73.5

105.0

ROTOR

STA

CG OF RIGHT

78.5

100.0

124.0

SIDE FWD

CARGO COMPARTMENT

PASSENGER

STA

15.0

174.0

+ 15.5

+ 12.2

REFERENCE

+0.8

DATUM

CG OF FWD

PASSENGER

-12.2

-13.0

CG OF PILOT

THREE PLACE COCKPIT

STA

WITH SINGLE CONTROLS

71.5

105.0

73.5

ROTOR

STA

78.5

100.0

124.0

CARGO COMPARTMENT

CG OF PILOT

STA

15.0

174.0

+ 15.5

+ 12.2

REFERENCE

0.0

DATUM

-12.2

-13.0

CG OF COPILOT

TWO PLACE COCKPIT

RIGHT HAND COMMAND

STA

73.5

105.0

F03-020-1

Figure 6-2. Reference Coordinates (Sheet 1 of 2)

Revision 14

6-3

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

LATERAL

``+'' CG

REFERENCE

FORWARD

CENTERLINE

STA

100.0

STA

15.00

99.0

107.4

PERMISSIBLE CG LIMITS

100

120

140

160

180

200

220

240

260

280

300

SLING POINT

OIL TANK-RH SIDE

LEVELING PLUMB

STA 92.6

FIRE WALL

JIG POINT

3°

AFT JACKING

POINT STA 197.2

STA 174.0

BHD

STA 284.0

ENGINE SECTION

BATTERY

STA

FUEL CELL

78.5

124.0

COMPARTMENT

JIG POINT

FWD JACKING POINT

STA 96.9

BL "25.6

WL 11.98

F03-020-2

Figure 6-2. Reference Coordinates (Sheet 2 of 2)

6-4

Revision 14

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

6-2. WEIGHT AND BALANCE CRITERIA

Use the delivered weight as recorded in the Weight and Balance Record in-

serted in this section to perform all weight and balance computations. Deliv-

ered weight includes oil and unusable fuel.

6-3. EQUIPMENT REMOVAL OR INSTALLATION

Removal or addition of equipment must be entered on the repair and alteration

report form, FAA 337, in accordance with Federal Air Regulations which shall

then become part of the helicopter log book file.

Record the weight and balance effects of these changes in the Weight And Bal-

ance Record inserted in this section.

Use the balance and station diagrams as an aid for weight and balance

changes.

6-6

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

WEIGHT AND BALANCE REPORT

MODEL 500

WEIGHED BY:

J. Doe

DATE 4 October 1982

MODEL

369E SERIAL NO.

REGISTRATION NO.

TARE OR

SCALE

NET

WEIGHING

CALIBRATION

ARM

MOMENT

READING

WEIGHT

POINTS

CORRECTION

(IN.)

(IN. LB)

(LBS)

LEFT MAIN

721.7

0.0

721.7

96.9

69933

RIGHT MAIN

591.7

0.0

591.7

96.9

57915

TAIL

182.0

0.0

182.0

197.2

35890

TOTAL UNADJUSTED NET WEIGHT

1495.4

109.1

163138

TOTAL WEIGHT OF SURPLUS EQUIPMENT (SEE TABLE 1)

-1.3

96.9

-126

TOTAL WEIGHT OF MISSING EQUIPMENT (SEE TABLE 1)

15.9

97.4

+1549

TOTAL BASIC WEIGHT

1510.0

109.0

164561

REFER TO THE OWNER'S MANUAL FOR C.G. LIMITS APPLICABLE FOR GROSS WEIGHT RANGE

FUEL/OIL AT TIME OF WEIGHING

EMPTY

FULL

FUEL

ENGINE OIL

MAIN GEAR BOX

TAIL GEAR BOX

Figure 6-4. Sample Weight and Balance Report (Sheet 1 of 2)

Revision 14

6-7

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

MODEL 369E SERIAL NO.

REGISTRATION NO.

DATE 7/11/91

EXAMPLES OF FORWARD, AFT, AND LATERAL LOADING

LONG.

EXAMPLE 1, FORWARD

WEIGHT

ARM

MOMENT

(LBS.)

(IN.)

(IN.-LB.)

BASIC WEIGHT

1510.0

109.0

164561

PILOT

170.0

73.5

12495

PASSENGER - FWD. R.H.

170.0

73.5

12495

CRITICAL FUEL QUANTITY

40.0

91.6

3664

GROSS WEIGHT (CRITICAL FUEL) - FWD C.G.

1890.0

102.2

193215

APPROVED FWD C.G. LIMIT FOR EXAMPLE 1 GROSS WEIGHT 99.0 INCHES.

LONG.

EXAMPLE 2, AFT

WEIGHT

ARM

MOMENT

(LBS.)

(IN.)

(IN.-LB.)

BASIC WEIGHT

1510.0

109.0

164561

PILOT

170.0

73.5

12495

PASSENGER - AFT L.H.

170.0

105.0

17850

PASSENGER - AFT R.H.

170.0

105.0

17850

BAGGAGE - UNDER AFT SEAT

50.0

110.0

5500

GROSS WEIGHT (ZERO FUEL) - AFT C.G.

2070.0

105.4

218256

APPROVED AFT C.G. LIMIT FOR EXAMPLE 2 GROSS WEIGHT 105.8 INCHES.

LATRL.

EXAMPLE 3, LATERAL

WEIGHT

ARM

MOMENT

(LBS.)

(IN.)

(IN.-LB.)

BASIC WEIGHT

1510.0

PILOT

170.0

- 13.0

- 2210

PASSENGER - AFT L.H.

170.0

- 12.2

- 2074

GROSS WEIGHT(ZERO FUEL) - LATERAL C.G.

1850

- 2.3

- 4284

APPROVED LATERAL C.G. LIMIT FOR EXAMPLE 3 GROSS WEIGHT ± 3 INCHES.

Figure 6-4. Sample Weight and Balance Report (Sheet 2 of 2)

6-8

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

TABLE 1

SURPLUS AND MISSING EQUIPMENT

Model

369E

Serial No.

Registration No.

Date

WEIGHT

ARM - INCHES

MOMENT - IN/LBS

EQUIPMENT - ITEM

LBS

LONG

LATR

LONG

LATR

SURPLUS EQUIPMENT TOTAL:

(

1.3

)

( 96.9)

(

)

(

126

)

(

)

JACK PADS (2)

1.3

96.9

126

MISSING EQUIPMENT TOTAL:

(15.9)

( 97.4 )

( - 0.0 )

(

1549

)

(

- 0

)

ONE QT ENGINE OIL

2.1

133.1

0.0

280

UNUSABLE FUEL

12.0

93.0

0.0

1116

FLIGHT MANUAL

1.8

85.0

0.0

155

Page

3 of

Figure 6-5. Sample Surplus and Missing Items

Revision 14

6-9

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

6-4. WEIGHT AND BALANCE DETERMINATION - PASSENGER

CONFIGURATION

To determine that the gross weight and longitudinal center of gravity (fore and

aft) for a given flight are within limits, proceed as follows:

Obtain aircraft delivered weight and moment from the Weight and Balance

Record inserted in this section.

Determine weights and moments of useful load items (Ref. Figure 6-2, and

Figure 6-7).

Add above items (see Example I).

Determine corresponding center of gravity for gross weight by dividing total

moment by gross weight. This computation must be done with zero fuel

gross weight and with mission fuel gross weight (see Example I).

NOTE: If loadings are not symmetrical about the aircraft centerline, determine lateral

CG’s as described in Paragraphs 6-6 and 6-7.

Weight and balance must be computed for minimum front seat

CAUTION

weight prior to loading any passengers in rear seats with only pilot

in front. Ballast, if required, must be carried.

NOTE: Ballast may be carried in the utility stowage compartment or stowed and secured

by seat belt and shoulder harness in opposite front seat. Ballast may consist of

shot, sandbags, or similar material, adequately contained and secured.

Revision 14

6-11

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

EXAMPLE I. Longitudinal CG Calculation - Passenger

Items

Weight

Moment

(lb)

(in.-lb)

Delivered Weight

1,510

164,561

Pilot

170

12,495

Passenger - Fwd Outboard

170

12,495

Passenger - Aft R/H

170

17,850

Passenger - Aft L/H

170

17,850

Utility Stowage (Station 52.9)

1058

Baggage (under seat, Station 110.0)

4,400

1. Zero Fuel Weight

2,250

230,709

Add Useable Fuel (62.1 GAL Jet a @ 6.8

422

41,229

LB/GAL)

2. Gross Weight

2,672

271,938

Calculation of Longitudinal CG

CG (Zero Fuel Weight):

Moment at Zero Fuel Weight

= 230,709

= 102.5 IN.

Zero Fuel Weight

2,250

CG (Gross Weight):

Moment at Gross Weight =

271,938

= 101.8 IN.

Gross Weight

2,672

NOTE: The CG falls within the limits specified in Table 6-1.

6-12

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

6-5. LONGITUDINAL LOADING OF CARGO

The large aft compartment of the Model 369E provides great flexibility in the

variety of cargo loads it can accommodate.

In general, the placement of cargo CG within 4 inches of the center of the

compartment will ensure that the helicopter will be within the approved CG

limits.

To determine the gross weight and center of gravity for a given flight are with-

in limits, proceed as follows.

Establish the weight of the cargo load.

Determine the location of the cargo longitudinal CG by measuring the dis-

tance to the cargo from the jacking point located on the side of the fuselage

(station 96.9).

Cargo CG = 96.9 ± measured distance (inches); ie., + if aft of mark, - if for-

ward of mark.

Obtain the cargo moment:

Cargo Moment = Cargo Weight x Cargo CG

Perform weight and balance as previously described for passenger configura-

tion.

Revision 14

6-13

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

EXAMPLE II. Longitudinal CG Calculation - Passenger and Cargo

Weight

Moment

Items

(lb)

(in.-lb)

Delivered Weight

1,510

164,561

Pilot

170

12,495

Passenger - Fwd Outboard

170

12,495

Cargo (Station 100.0)

1000

100,000

1. Zero Fuel Weight

2,850

289,551

Add Usable Fuel (22.0 GAL Jet a @ 6.8

150

14,175

LB/GAL)

2. Gross Weight

3,000

303,726

Calculation of Longitudinal CG

CG (Zero Fuel Weight):

Moment at Zero Fuel Weight

= 289,551

= 101.6 IN.

Zero Fuel Weight

2,850

CG (Gross Weight):

Moment at Gross Weight =

303,756

= 101.2 IN.

Gross Weight

3,000

NOTE: The CG falls within the limits specified in Table 6-1.

6-14

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

6-6. PERMISSIBLE LATERAL LOADINGS

Safe operation of this helicopter requires that it be flown within established

lateral as well as longitudinal center of gravity limits.

It is therefore imperative that lateral center of gravity control be exercised.

All combinations of internal and external loadings are permissible if gross

weight, longitudinal, and lateral center of gravity considerations permit.

For crew and passenger lateral center of gravity, see Figure 6-2.

6-7. LATERAL LOADING OF CARGO

To determine if the gross weight and lateral center of gravity for a given flight

are within limits. Proceed as follows:

Find weight of load.

Determine lateral location (station) of load center of gravity.

Measure load distance from aircraft centerline (lateral station zero), right

(+); left (-).

Obtain the lateral load moment as follows:

Lateral moment = weight X lateral station. (See Example III.)

Revision 14

6-15

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

EXAMPLE III. Lateral CG Calculation - Passenger and Cargo

Weight

Lateral

Lateral Moment

Items

(lb)

Arm (in)

(in.-lb)

Delivered Weight

1,510

Pilot (L/H)

170

-13.0

-2,210

Passenger - Fwd (R/H)

170

+15.5

+2,635

Cargo

1000

+2.0

+2,000

1. Zero Fuel Weight

2,850

+0.9

+2,425

Add Usable Fuel (22.0

150

GAL Jet a @ 6.8 LB/GAL)

2. Gross Weight

3,000

+0.8

+2,425

Calculation of Lateral CG

CG (Zero Fuel Weight):

Moment at Zero Fuel Weight

= +2,425

= +0.9 IN.

Zero Fuel Weight

2,850

CG (Zero Fuel Weight):

Moment at Gross Weight = +2,425

= +0.8 IN.

Gross Weight

3,000

NOTE: The CG falls within the limits specified in Table 6-1.

6-16

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

Table 6-2. Weights and Longitudinal Moments - Pilot, Passenger, Baggage

Pilot and Passenger Weights and Longitudinal Moments

Moment

Passenger

(in.-lb)

Weight (lb)

Pilot or Fwd

Center Fwd

Aft Passenger

R/H Passenger

Passenger

R/H and L/H

Station 73.5

Station 71.5

Station 105.0

120

8,820

8,580

12,600

140

10,290

10,010

14,700

160

11,760

11,440

16,800

170

12,495

12,155

17,850

180

13,230

12,870

18,900

200

14,700

14,300

21,000

220

16,170

15,730

23,100

240

17,640

17,160

25,200

Baggage Weights and Longitudinal Moments

Moment

Baggage

(in.-lb)

Weight

Utility Stowage

Under Seat

(lb)

Compartment

Fwd Bulkhead

and Center

Behind Seat

Station 52.9

Station 87

Station 110

Station 120

529

870

1,100

1,200

1,058

1,740

2,200

2,400

1,587

2,610

3,300

3,600

2,116

3,480

4,400

4,800

*50

2,645

4,350

5.500

6,000

5,220

6,600

7,200

6,090

7,700

8,400

6,960

8,800

9,600

7,830

9,900

10,800

100

8,700

11,000

12,000

*Maximum Capacity

Revision 14

6-19

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

Table 6-3. Weights and Lateral Moments - Pilot, Passenger, Baggage

Moment

Passenger

(in.-lb)

Weight

Pilot

Passenger

Aft Passenger

(lb)

L/H

R/H Fwd

Center Fwd

R/H and L/H

Station-13.0

Station+15.5

Station +0.8

Station ±12.2

120

-1,560

+1,860

+ 96

±1,464

140

-1,820

+2.170

+112

±1,708

160

-2,080

+2,480

+128

±1,952

170

-2,210

+2,635

+136

±2,074

180

-2,340

+2,790

+144

±2,196

200

-2,600

+3,100

+160

±2,440

220

-2,860

+3,410

+176

±2,684

240

-3,120

+3,720

+192

±2,928

BAGGAGE WEIGHTS AND MOMENTS

Baggage Weight (lb)

Moment

Station +12.8

(in.-lb)

+128

+256

+348

+512

+640

6-20

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Weight and Balance Data

CG OF PASSENGERS

FUEL FILLER

INLET LINE

+12.0 IN.

(+)

+5.2 IN.

FWD C

KIT WEIGHT = 17.9 LB

KIT CG = 101.4 IN. LONGITUDINAL

-12.0 IN.

(-)

-1.0 IN. LATERAL

STA

78.5

95.5

109.2

124.0

F03-024

Aft Compartment Passenger Weights and Longitudinal Moments

(High Density Seating)

Table 6-4. Weight and Loading for 369H90035-503 Seating and Belts

for Four Installation (High Density Seating)

Passenger (s)

Moment (In. lb),

Moment (in.-lb),

(lb)

Fwd position

Aft Position

(Sta 95.5)

(Sta 109.2)

150

14,300

16,400

175

16,700

19,100

200

19,100

21,800

225

21,500

24,600

250

23,900

27,300

275

26,300

30,000

300

28,700

32,800

325

31,000

35,500

350

33,400

38,200

375

35,800

41,000

400

38,200

43,700

Revision 14

6-21

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Weight and Balance Data

6-8. INTERNAL LOADING OF CARGO

The following instructions should be followed when carrying internal cargo.

Rope, cable, or equivalent must have a minimum loop strength of 1,800

pounds.

Restrain the cargo from shifting by using the correct number of restraining

loops in accordance with Table 6-5.

Position restraining loop in accordance with Figure 6-8.

Cargo deck capacity is 1300 pounds (not to exceed 115 pounds per square

foot).

View II shows typical tiedown for 500-pound cargo.

Restraint loops are to be secured as indicated and tied to the cargo to pre-

vent slippage of the loops.

Variations of the tiedown are allowable, providing total restraint require-

ments are met.

Caution should be exercised to keep the cargo from bearing against the cen-

ter slanted portion of the aft bulkhead.

Table 6-5. Cargo Weight Versus Loop Restraint

Number of Required Restraint Loops

Cargo

Forward

Aft

Vertical/Lateral

(lb)

Restraint

Up to 100

101 to 300

301 to 400

401 to 600

601 to 800

801 to 1000

1001 to 1100

1101 to 1200

1201 to 1300

*Note the 7^th and 8^th loops are to use the outboard seat belt attach

fitting (Station 124).

6-22

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling Servicing

and Maintenance

S ECTION VII

HANDLING, SERVICING

AND MAINTENANCE

TABLE OF CONTENTS

PARAGRAPH

PAGE

7-1.

Helicopter Components

7-1

7-2.

Use of External Power

7-1

7-3.

Hoisting, Jacking, and Lifting

7-1

Figure 7-1. MD 369E Helicopter - Major Components

7-2

7-4.

Ground Handling Wheels

7-3

Figure 7-2. Ground Handling Wheels

7-3

7-5.

Moving and Towing Helicopter

7-4

7-6.

Parking and Mooring

7-5

Figure 7-3. Parking and Mooring

7-6

7-7.

Servicing - General

7-7

Table 7-1. Servicing Materials (Operating Supplies)

7-7

Figure 7-4. Servicing Points (Sheet 1 of 2)

7-12

Figure 7-4. Servicing Points (Sheet 2 of 2)

7-13

7-8.

Fuel System - Servicing

7-14

7-9.

Engine Oil System - Servicing

7-15

7-10. Main Rotor and Tail Rotor Transmission - Servicing

7-15

7-11. Cleaning General

7-16

7-12. Cleaning Fuselage Interior Trim and Upholstery

7-16

7-13. Cleaning Aircraft Exterior and Rotor Blades

7-17

7-14. Cleaning - Canopy and Door Transparent Plastic

7-17

7-15. Fluid Leak Analysis

7-17

7-16. Preservation and Storage

7-18

7-17. Flyable Storage - No Time Limit

7-18

7-18. Cockpit Door Removal and Installation

7-19

Figure 7-5. Pilot and Passenger/Cargo Door Removal

7-20

7-19. Special Operational Checks and Procedures

7-21

Compressor Wash

7-21

Main Rotor Hub Balancing

7-22

Revision 18

7-i

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

SECTION VII

HANDLING SERVICING

AND MAINTENANCE

7-1. HELICOPTER COMPONENTS

The major components of the helicopter are shown in Figure 7-1.

7-2. USE OF EXTERNAL POWER

An external receptacle is located at the right side of the pilot's compartment

seat structure. The right door must be open to use the receptacle. Any source

of external 28-volt, direct-current power with sufficient amperage rating may

be used. Engine starting requirements are approximately 375 amperes, mini-

mum.

Before connecting external power, be sure that helicopter main electrical power

selector switch is OFF.

After power is connected to receptacle, power switch must be set to EXT posi-

tion to connect external power to helicopter electrical system.

7-3. HOISTING, JACKING, AND LIFTING

Hoisting, lifting, and jacking of the helicopter shall only be

CAUTION_{performed by qualified maintenance personnel with the proper}

equipment and tools as specified in the Handbook of Maintenance

Instructions. Failure to follow the specified procedures may result

in damage to aircraft components.

Revision 14

7-1

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

HORIZONTAL STABILIZER

MAIN ROTOR INSTALLATION

VERTICAL STABILIZER

TAIL ROTOR

TRANSMISSION

FLIGHT CONTROLS

INSTALLATION

TAILBOOM

AFT SECTION

INSTALLATION

TAIL ROTOR

ASSEMBLY

ENGINE

FORWARD SECTION

INSTALLATION

MAIN TRANSMISSION

AND POWER TRAIN

ENGINE ACCESS

DOOR

CARGO DOOR

PILOT DOOR

LOWER SECTION INSTALLATION

ASSEMBLY

LANDING GEAR

F30-026

Figure 7-1. MD 369E Helicopter - Major Components

7-2

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

7-4. GROUND HANDLING WHEELS

Standard ground handling wheels, available as a special tool for helicopters not

equipped with floats, are used for moving helicopter by hand and for towing

helicopter (Ref. Figure 7-2).

At regular intervals, check that wheel tire pressure is a maximum of 80 to 90

psi.

WARNING:

BE SURE LOCK SNAPS INTO

POSITION SHOWN BEFORE

RELEASING JACK HANDLE

LOCK

TOW BAR FITTING

WHEELS LOWERED AND LOCKED

(HELICOPTER RAISED)

JACK HANDLE

HANDLE LOCK PIN

GROUND HANDLING WHEELS

AND JACK ASSEMBLY

SKID TUBE

(RIGHT SIDE SHOWN)

SKID FITTING

WHEELS RAISED

F03-029

(HELICOPTER LOWERED)

Figure 7-2. Ground Handling Wheels

Revision 14

7-3

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

7-5. MOVING AND TOWING HELICOPTER

Manual moving:

Excessive lead-lag load applied to the main rotor blades during

CAUTION_{ground handling can result in damage to the elastomeric damper}

buns and failure of the damper assembly. Operators should use

extra caution to avoid lead-lag loads in excess of 35 pounds at

the tip of the main rotor blades.

Ensure all stress panels are installed on helicopter before moving.

Attach ground handling wheels (Ref. Figure 7-2) and hold tail up while low-

ering the wheels (raising helicopter).

Manually move helicopter on ground handling wheels by balancing at tail-

boom and pushing on rear fuselage portion of air frame.

Towing:

Tow helicopter on ground handling wheels by attaching suitable tow bar to

tow bar fittings. If tow bar is not equipped to keep front ends of skid tubes

from dragging, have an assistant balance helicopter at tailboom.

Ensure all stress panels are installed on helicopter before moving.

Except under extreme emergency conditions, do not tow helicopter

CAUTION

at speeds over 5 mph. Do not allow front end of skid tubes to drag

on ground. Avoid sudden stops and starts and short turns which

could cause helicopter to turn over. Allow inside wheel to turn (not

pivot) while helicopter is being turned. Safe minimum turning ra-

dius is approximately 20 feet.

7-4

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

7-6. PARKING AND MOORING

Parking (Ref. Figure 7-3):

To prevent rotor damage from blade flapping (droop stop pound-

CAUTION

ing) as a result of air turbulence from other aircraft landing, taking

off or taxiing or sudden wind gusts, rotor blades should be secured

whenever helicopter is parked.

Locate helicopter slightly more than blade clearance from nearby objects on

most level ground available.

Apply friction to lock cyclic and collective sticks so that friction control

knobs are positioned as follows: neutral for cyclic stick an full down for col-

lective stick.

Secure main rotor blades as follows.

Turn blades until one blade is directly above tailboom (Ref. Figure 7-3).

Install blade socks on all blades.

Secure blade sock tiedown cord for blade located above tailboom to tailboom.

Secure other blade sock tiedown cords to fuselage jack fittings or cabin

steps.

When securing blade sock tiedown cords, take up slack, but do not

CAUTION

apply excessive bending loads on blades.

Mooring (Ref. Figure 7-3):

Whenever severe storm conditions or wind velocities higher than 40 knots

are forecast, helicopter should be hangared or evacuated to safer area.

Park helicopter and remove main rotor blades.

Install pitot tube cover.

Fill fuel tank (if possible).

Apply friction to lock cyclic and collective sticks.

Secure helicopter to ground by attaching restraining lines (cable or rope) be-

tween jack fittings and stakes or ground anchors.

Install air inlet fairing cover on air inlet front fairing.

Install engine exhaust cover on exhaust tailpipe.

Revision 14

7-5

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

BLADE SOCK

(5 PLACES)

TIEDOWN TETHER

MOORING ANCHOR

(4 PLACES)

ENGINE EXHAUST

COVER

ZIPPER

AIR INLET

FAIRING

COVER

PITOT TUBE

COVER

DOOR

TIE CORD

ACCESS

PITOT TUBE

LATCH

FUEL CELL

COVER INSTALLATION

ACCESS DOOR

LOCKPIN

ENGINE AIR INLET

JACK FITTING

STOWAGE

FAIRING COVER

INSTALLATION

FUESELAGE

STRUCTURE

JACK FITTING

TO MOORING

ANCHOR

TO BLADE

SOCK

JACK FITTING INSTALLATION

(TYPICAL - 2 PLACES)

F03-030

Figure 7-3. Parking and Mooring.

7-6

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

7-7. SERVICING - GENERAL

Servicing helicopter includes replenishment of fuel, changing or replenishment

of oil and other such maintenance functions.

Fuels, oils, other servicing materials and capacities are listed in Table 7-1.

NOTE: Check the appropriate Rolls-Royce Operation and Maintenance Manual for

complete listing of approved lubricants.

Locations of servicing points are shown in Figure 7-4.

Table 7-1. Servicing Materials (Operating Supplies)

1. Tail Rotor Transmission - Capacity 0.5 US Pt (0.23 Liter)

Use the materials listed under Item 4 or decal on on transmission (Refer to SB369E-104).

2. Main Transmission (369D25100) - Capacity: 12.0 US Pt (5.67 liters)

Use the materials listed under Item 4 or Mobil AGL (See Footnote 4).

3. Main Transmission (369F5100) - Capacity: 14.0 US Pt (6.62 liters).

Use Mobil AGL only (See Footnote 4).

4. Engine - Capacity: 3.0 US Qt. (2.84 liters)

Ambient Temperature

Oil Type

0°C (32°F) and above

MIL-PRF-23699C or subsequent preferred

0°C (32°F) to -40°C (-40°F) MIL-PRF-23699C or subsequent preferred or

MIL-PRF-7808G or subsequent

-40°C (-40°F) and below

MIL-PRF-7808G or subsequent only

Specification

Material

Manufacturer

MIL-PRF-7808 (see Footnote 2 and 3)

American PQ Lubricant 6899

American Oil and Supply Co.

238 Wilson Ave.

Newark, NJ 07105

BP Turbo Oil 2389

BP Corporation North America Inc.

Exxon Turbo Oil 2389

1500 Valley Rd

Wayne, NJ 07470-2040

Brayco 880

Air BP Lubricants

Maple Plaza II - 1N

6 Campus Drive

Parsippany, NJ 07054

Mobil Avrex S Turbo 256

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Revision 18

7-7

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

Specification

Material

Manufacturer

MIL-PRF-7808 (Cont.) Mobil RM-201A

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Mobil RM-184A

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Stauffer Jet 1

Stauffer Chemical Co.

380 Madison Ave.

New York, NY 10017

MIL-PRF-23699 STD

AeroShell Turbine Oil 500

Shell Aviation, Ltd

Site Office

London, SE1 7NA, GBR

Royco Turbine Oil 500

Chemtura Corporation

Anderol Division

215 Merry Ln.

East Hannover, NJ 07936-3900

American PQ Lubricant 6700

American Oil and Supply Co.

238 Wilson Ave.

Newark, NJ 07105

BP Turbo Oil 2380

BP Corporation North America Inc.

Exxon Turbo Oil 2380

1500 Valley Rd

Wayne, NJ 07470-2040

Caltex RPM Jet Engine Oil 5

Caltex Petroleum Corp

380 Madison Ave.

New York, NY 10017

Castrol 5050

Castrol Industrial North America

Inc.

775 Louis Dr.

Warminster, PA 18974-2827

Chevron Jet Engine Oil 5

Chevron International Oil Co.

555 Market Street

San Francisco, CA 94105

7-8

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

Specification

Material

Manufacturer

MIL-PRF-23699 STD

Hatcol 3211

Chemtura Corporation

(Cont)

Hatco Division

1020 King Georges Post Rd.

Fords, NJ 08863-2329

Mobil Jet Oil II

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Stauffer Jet II

Stauffer Chemical Co.

380 Madison Ave.

New York, NY 10017

Turbonycoil 600 (TN 600)

SOC NYCO

66, Avenue des Champs Elysees

Paris, 75008, FRA

MIL-PRF-23699 HTS

AeroShell Turbine Oil 560

Shell U.K. Oil Products Ltd.

SSSC Glasgow

Gate 5, Oil Sites Rd.

Ellesmere Port,

Cheshire, CH65 4FS, GBR

Royco Turbine Oil 560

Chemtura Corporation

Anderol Division

215 Merry Ln.

East Hannover, NJ 07936-3900

BP Turbo Oil 2197

BP Corporation North America Inc.

1500 Valley Rd

Wayne, NJ 07470-2040

Mobil Jet 254

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Mobil Jet 291

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

Revision 18

7-9

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

Specification

Material

Manufacturer

SAE AS5780 SPC

BP Turbo Oil 2380

BP Corporation North America Inc.

Exxon Turbo Oil 2380

1500 Valley Rd

Wayne, NJ 07470-2040

Mobil Jet Oil II

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

SAE AS5780 HPC

BP Turbo Oil 2197

BP Corporation North America Inc.

1500 Valley Rd

Wayne, NJ 07470-2040

Mobil Jet 254

ExxonMobil Oil Corp.

Exxon

3225 Gallows Rd.

Fairfax, VA 22037-0001

5. Fuel Cells - Standard Nonself-sealing, Capacity: 64.0 US Gal (242 liters), 416 pounds

Optional Self-sealing, Capacity: 62.0 US Gal (234 liters), 402 pounds.

Refer to Rolls-Royce 250 Series Operations Manual for complete fuel speci-

fications.

MIL-DTL-5624 JP-4

MIL-DTL-5624 JP-5

ASTM D 1655 Jet A

ASTM D 1655 Jet A-1

ASTM D 1655 Jet B

JP-1 conforming to ASTM D

Peoples Republic of China

ASTM D 6615 Jet B

1655, Jet A or Jet A-1

RP-3.

Arctic Diesel Fuel DF-A

Diesel No. 1 conforming to

MIL-DTL-83133, grade JP-8

(W-F-800B) conforming to

ASTM D 1655, Jet A or Jet

A-1

CAUTION: At 4.4°C (40°F) and below, fuel must contain anti icing additive that meets

MIL-I-27686 requirements. For blending information and authorized fuels,

refer to the appropriate Rolls-Royce Operation and Maintenance Manual.

6. Overrunning Clutch (369A5350) - Capacity: 1.64 US Oz (45cc) Use the materials listed

under item 4 but not Mobil AGL (See Footnote 4).

7. Overrunning Clutch (369F5450) - Capacity: 3.64 US Oz. Use Mobil AGL

(See Footnote 4).7

7-10

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

8. One-Way Lock - Capacity: 0.67 US Oz (20cc)

MIL-PRF-5606

Brayco Micronic 756 and 756PH

Specialty Products Division

1001 West 31st Street

Downers Grove

Illinois 60515

Aero Shell Fluid 41

Shell Oil Co.

Royco 756

Anderol Inc

Mobil Aero HF

ExxonMobil Lubricants

Invarol FJ 13

ESSO Saf

2, rue des Martinets

92569 Rueil-Malmaison

Cedex, France

MIL-PRF-6083

Brayco Micronic 783

Castrol Industrial North America

Inc.

Royco 783

Anderol Inc.

Hydraunycoil FH-6

NYCO, S.A.

9. Battery (NiCad) - Capacity: As required

MS36300

Distilled Water

Any acceptable source

Footnotes:

(1)

Oils approved for use in main transmission and tail rotor transmission are synthetic

lubrication oils that have a certified Ryder Gear Value in excess of 2500 pounds per

inch.

(2)

Not a preferred lubricant for transmissions. Use MIL-PRF-7808 lubricating oil in

transmission only when other oils are not available.

(3)

For Model 250 Series engine oil change requirements and restrictions on mixing of oils,

refer to the Rolls-Royce Operation and Maintenance Manual.

DO NOT use Mobil AGL oil in 250 Series engines.

(4)

Do not use Mobil SHC 626 lubrication oil designated as

“NOT FOR AVIATION USE" on the label. Refer to SB369E-104.

WARNING: Only discretionary mixing of oils within an oil series is permitted without a time

penalty. Use of mixed oils from different series in an engine is limited to five hours

total running time during one overhaul period. Adequate maintenance records

must be maintained to ensure that the five hour limit is not exceeded. Failure to

comply with oil mixing restrictions can result in engine failure.

Revision 18

7-11

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

OIL FILTER BYPASS INDICATOR

(369F5100 M/R TRANSMISSION ONLY)

TRANSMISSION OIL LEVEL SIGHT GAUGE

MAIN TRANSMISSION

FILLER

BATTERY

MAIN TRANSMISSION

DRAIN VALVES

LIQUID LEVEL

SIGHT GAGE

OVERBOARD OIL

DRAIN LINE

ONE-WAY LOCK

ENGINE ACCESSORY

RESERVOIR

GEARBOX DRAIN

EXTERNAL POWER

RECEPTCLE

BREATHER FILLER

ENGNE OIL

TANK FILLER

FUEL CELL

ENGINE COMBUSTION

DRAIN VALVE

FUEL DRAIN

GROUND

RECEPTACLE

LIQUID LEVEL

FUEL SYSTEM

SIGHT GAGE

FILLER

TAIL ROTOR

TRANSMISSION DRAIN

F03-031-1

Figure 7-4. Servicing Points (Sheet 1 of 2)

7-12

Revision 18

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

7-8. FUEL SYSTEM - SERVICING

Refueling vehicle should be parked a minimum of 20 feet from helicopter dur-

ing fueling operation.

Before starting fueling operation, always ground fueling nozzle or fuel truck to

GROUND HERE receptacle (Ref. Figure 7-4) or to another bare metal location.

Comply with the following precautions when servicing the fuel system.

Turn off electrical switches and disconnect any external power from

WARNING

helicopter. Electrically ground helicopter prior to refueling or

defueling. Static discharge spark in presence of fuel vapors can

cause fire or an explosion.

Cold weather fuels:

Grade JP-4 (MIL-T-5624), grade JP-5, and grade JP-8 (MIL-T-3133A, or

later) type fuels contain anti-ice additive which conforms to MIL-1-27686

(or later). These fuels do not require additional anti-ice additive.

Cold weather fuel mixtures

To assure consistent starts at temperatures at or below 4°C (40°F), a

mixture of AVGAS and jet fuels (other than JP-4 or Jet B) may be used.

The alternate avgas-jet fuel mixture is not recommended for warm

weather operation.

Refer to Allison Operation and Maintenance Manual for additional cold

weather fuel mix and blending instructions.

Filling:

The fuel system has two fuel cells that are interconnected for simultaneous

flow and venting.

Refuel the helicopter with the proper fuel as soon after landing as possible

to prevent moisture condensation.

Keep fuel nozzle free of all foreign matter.

Fuel tank servicing is through the cell filler neck on the right side of the

fuselage. The right side fuel cell contains the gravity filler port and cap.

Check filler cap for security after refueling.

7-14

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

Fuel draining:

Fuel draining should be accomplished with helicopter as level as possible.

The fuel system may be defueled in two ways: One is to defuel through the

filler port, using a pump. The other method is to open the drain valve on

fuselage underside.

The fuel cell drain valve is spring-loaded closed and is opened by depress-

ing an internal plunger.

After defueling, be sure to check drain valve for leakage.

7-9. ENGINE OIL SYSTEM - SERVICING

The engine oil tank filler is on the right side of the helicopter (Ref.

Figure 7-4). A liquid level sight gauge for checking oil level in tank is visible

through a transparent window near the filler.

NOTE: Oil level should be checked within 15 minutes after shutdown.

Replenish with correct oil until oil level is FULL on sight gauge.

CAUTION_{DO NOT use Mobil SHC 626 oil in the engine oil system.}

Make certain that oil tank filler cap is secured after servicing.

7-10. MAIN ROTOR AND TAIL ROTOR TRANSMISSION - SERVICING

Main rotor transmission:

Check transmission oil level at liquid level sight gauge (Ref. Figure 7-4)

NOTE: Indicated oil level may be incorrect if aircraft is not level or has been ground

handled in a tail-low attitude since last flight.

Replenish with correct oil until oil level is at the dashed lines above the

ADD mark on sight gauge.

Mixing of oils within an oil series, not in the same group, is not rec-

CAUTION

ommended. If oils of different groups are mixed, flush and re-ser-

vice gearbox. Mixing of oils from different series is prohibited.

NOTE: If oil was drained from transmission cooler, ground run helicopter for 15 minutes

after replenishing with oil and recheck oil level at sight gauge. Replenish oil as

necessary. This purges air from the oil cooling system and ensures that entire

oil cooling system is full.

Fill main transmission by lifting breather-filler cap and inserting funnel

into opening. Check that spring-loaded cap closes when funnel is removed.

Revision 18

7-15

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

Tail rotor transmission:

A liquid level sight gauge for checking oil level is located on the rear of the

transmission housing.

Check oil level by viewing sight gauge.

Servicing of the tail rotor transmission should be performed by maintenance

personnel.

7-11. CLEANING GENERAL

General cleaning of oil and dirt deposits from the helicopter by using dry-

cleaning solvent, standard commercial grade kerosene or a solution of deter-

gent soap and water.

Exceptions that must be observed are specified in the following cleaning para-

graphs.

Some commercial cleaning agents, such as readily available

CAUTION_{household cleaners, contain chemicals that can cause corrosive}

action and/or leave residue that can result in corrosion. Examples

of cleaning agents that are not to be used are ‘‘Fantastic’’ and ‘‘409’’

type cleaners, or locally made strong soap cleaners.

7-12. CLEANING FUSELAGE INTERIOR TRIM AND UPHOLSTERY

Clean dirt or dust accumulations from floors and other metal surfaces with

vacuum cleaner or small hand brush.

Sponge soiled upholstery and trim panels with a mild soap and luke-warm wa-

ter solution. Avoid complete soaking of upholstery and trim panels. Wipe solu-

tion residue from upholstery with soft cloth dampened with clean water.

Remove imbedded grease or dirt from upholstery and carpeting by sponging or

wiping with an upholstery cleaning solvent recommended for the applicable

fabric (nylon, vinyl, leather, etc).

NOTE: If necessary, seat upholstery may be thoroughly dry-cleaned with solvent. When

complete dry cleaning is performed, upholstery must be re-flameproofed to

comply with Federal Aviation Regulation Part 27.

7-16

Revision 18

Helicopter MD 500E. Flight Manual (1982-2011) - page 2